WO2024194585A1 - Ensemble pour turbomachine - Google Patents
Ensemble pour turbomachine Download PDFInfo
- Publication number
- WO2024194585A1 WO2024194585A1 PCT/FR2024/050366 FR2024050366W WO2024194585A1 WO 2024194585 A1 WO2024194585 A1 WO 2024194585A1 FR 2024050366 W FR2024050366 W FR 2024050366W WO 2024194585 A1 WO2024194585 A1 WO 2024194585A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- annular
- radially
- seal
- radial
- annular wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Ceased
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
- F05D2250/611—Structure; Surface texture corrugated undulated
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
Definitions
- the present disclosure relates to an annular seal, such as a hydrostatic annular seal.
- the present document also relates to an assembly comprising such a seal as well as a turbine or turbomachine comprising such a seal.
- FIG. 1 schematically represents a turbomachine 1 with a double flow of longitudinal axis X.
- the turbomachine 1 generally comprises, from upstream AM to downstream AV according to the direction of flow of the gases within the turbomachine 1, a fan 2, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, a low-pressure turbine 7 and an exhaust system downstream of the turbomachine 1.
- the gas flow, in particular air, entering upstream of the turbomachine 1 first circulates through the fan 2 then divides, on the one hand, into an annular circulation vein called the primary vein 8, and on the other hand, into an annular circulation vein called the secondary vein 9 surrounding the primary vein 8.
- the low-pressure compressor 3, the high-pressure compressor 4, the combustion chamber 5, the high-pressure turbine 6 and the low-pressure turbine 7 are arranged in the primary vein 8.
- the terms “longitudinal”, “radial” and “circumferential” are defined relative to the longitudinal axis X of the turbomachine 1, the longitudinal axis X being the same as the axis of rotation of the low-pressure and high-pressure rotors of the turbomachine 1.
- the terms “inner” and “outer”, as well as “internal” and “external”, are then defined in the radial direction relative to the longitudinal axis X.
- the terms, upstream and downstream are defined relative to the general direction of flow of the gases in the turbomachine along the longitudinal axis X around which the turbomachine extends.
- FIG. 2A schematically representing a partial view of a low-pressure turbine 7 with a longitudinal axis which comprises an alternation of annular rows of moving blades 9 arranged longitudinally in alternation with annular rows of stator blades 10.
- FIG. 2 only two annular rows of rotor blades 9 and one annular row of stator blades 10 are shown.
- the annular rows of rotor blades 9 or moving blades 9 are connected to each other by a cylindrical shell 11.
- Each of the annular rows of stator blades 10 comprises a radially inner annular platform 12 and a radially outer annular platform (not shown) between which a plurality of blades 13 extend.
- the radially outer annular platform is fixed to a casing of the turbine.
- the management of the seal between the end of the stator blades 10 and the shell 11 of the rotor is important to limit gas leaks between the rotor and the stator 10 and to control the pressure and temperature conditions on either side of said seal and also radially below the seal.
- the annular row of stator blades 10 carries an annular clearance control seal 15 arranged radially inside the annular row of stator blades 10 and radially outside the cylindrical shroud 11, the annular clearance control seal 22 cooperating in a contactless seal with the cylindrical shroud 11 in order to limit the circulation from upstream of the annular row of stator blades 10 to downstream in the annular space between the seal 15 and the cylindrical shroud 11.
- such a clearance control seal 15 operates with a low and controlled annular clearance between the latter and the shell 11 when the turbine is in operation. Furthermore, this type of seal aims to achieve an adaptation of the clearance in operation.
- the use of the hydrostatic seal 15 then offers the advantage of limiting the leakage flow at the level of the seal, and thus makes it possible to improve the performance of the turbomachine and to reduce the requirements in terms of thermal and mechanical stresses when sizing the various components of the turbine 7.
- the hydrostatic annular seal 15 may be formed of two concentric annular walls 16, 17, and a plurality of elastically deformable members arranged circumferentially next to each other and extending between the two walls 16, 17 and including in particular elastically deformable blades 18 extending circumferentially.
- document WO 2009/148787 describes such a seal. This configuration makes it possible to improve the control of the radial deformation of the seal 15, and therefore the control of the clearance between the seal 15 and the ferrule 11 cooperating with the sealing gasket 15 so as to limit the passage of air.
- An assembly is thus proposed for an aircraft turbomachine with a longitudinal axis comprising a distributor which has a crown of stator blades comprising a foot at the radially internal end of the distributor carrying a seal, the seal being annular and configured to cooperate in a contactless sealing manner with a cylindrical shroud of a rotor of the turbomachine arranged radially inside the distributor, the seal comprising a plurality of seal sectors distributed circumferentially around the longitudinal axis, each seal sector comprising a radially external annular wall sector and a radially internal annular wall sector connected to each other.
- the seal support comprises radial notches in each of which are inserted radial tabs of the radially external annular wall sectors of the seal, the upstream annular tab and the downstream annular tab forming a U.
- the annular part allows free expansion in the radial direction when exposed to heat. In fact, under the effect of heat, expansions of the annular row of stator blades opposite the annular part occur.
- the U-shape produced by the connection between the upstream annular tab and the downstream annular tab acts as a shock absorber. This U-shape expands radially under the effect of thermal expansion and its self-centering guarantees that forces are not transmitted to the parts interfacing with the annular wall.
- the seal support comprises an upstream annular leg, a downstream annular leg which extend radially and a base which axially connects the upstream annular leg and the downstream annular leg, the upstream annular leg and the downstream annular leg forming a U-shape with the base.
- Each radially outer annular wall sector may be secured to a seal support, the seal support being annular and being mounted so as to slide radially relative to the foot.
- the radially outer annular wall may be secured by bolting the tabs to the seal bracket.
- the foot has oblong openings opening radially inwards and crossed by the bolts.
- binding screws can be mounted in order to replace the bolted connection. This makes it possible to limit the axial size and to drown the heads in order to avoid protuberances which would disturb the flow in the upstream and downstream cavities.
- a sheet metal may be engaged between the foot and the seal support.
- the sheet metal may have a general U shape comprising two radial annular branches connected to each other, the free end of each of the annular branches of the sheet metal being curved and cooperating, preferably by form connection, with a radial face of one of the upstream and downstream annular legs of the sealing gasket support.
- pins may be mounted on the seal support and the radially outer annular wall is engaged on these pins. This allows the correct position and orientation of the support before tightening.
- spacers can be mounted on the seal support, between the upstream annular tab and the downstream annular tab and allow the passage of the screw. This makes it possible to avoid axial deformation of these tabs during the passage of the tightening cut.
- the radially outer annular wall sectors may form a monolithic outer shell and wherein the radially inner annular wall sectors are arranged circumferentially end-to-end.
- the elastically deformable members may comprise radial legs, each radially inner annular wall sector being monolithic with a radial leg and a radially outer annular wall sector, the circumferentially adjacent joint sectors being elastically connected two by two, to each other via a radial leg arranged at the junction between two radially outer annular wall sectors.
- the document also relates to a turbine for an aircraft turbomachine, the turbine comprising a casing, an assembly described above, and a rotor which comprises a cylindrical shroud driven in rotation about the longitudinal axis and, the distributor being mounted in the casing and the cylindrical shroud being arranged radially under the distributor.
- This document also relates to a turbomachine, such as an aircraft turbojet or turboprop, comprising an assembly or turbine.
- a turbomachine such as an aircraft turbojet or turboprop, comprising an assembly or turbine.
- FIG. 1 schematically illustrates a cross-sectional view of an example of a turbomachine
- FIG. 2 schematically illustrates a partial view of part of a turbine, for example low pressure, Figure 2B being an enlargement of the seal illustrated in Figure 2A;
- FIG.3 schematically illustrates an annular sealing gasket
- FIG. 4 schematically illustrates a portion of an annular row of stator blades and a seal according to this document;
- FIG. 5 is an enlarged view of the seal of Figure 4.
- FIG. 17] to [Fig. 20] schematically illustrate alternative embodiments of the connecting tabs between a radially external annular wall and the radially internal annular walls for a seal;
- FIG. 21 is a three-dimensional schematic view of a sector of an annular row of stator or distributor blades according to the present document
- FIG. 23 is a schematic perspective view of the legs of a hydrostatic annular seal
- FIG. 24] and FIG. 25] are schematic perspective views of the radial sliding means between the hydrostatic annular seal and the annular row of stator blades;
- FIG. 27] to [Fig. 33] are schematic perspective views of an assembly comprising a hydrostatic annular seal according to the present document;
- FIG. 34 and [Fig. 35] including schematic perspective views of an assembly according to the present document and comprising a hydrostatic annular seal connected by form cooperation with radial sliding connection means on an annular row of stator blades;
- FIG. 36 is a schematic perspective view of a circumferential edge of an annular seal as described herein;
- FIG. 37 is a schematic illustration of an annular seal according to this document, the annular seal having a housing on its radially inner face;
- FIG. 38 schematically illustrates a partial view of an example of an assembly according to the present document, this assembly comprising an annular seal;
- FIG. 39 schematically illustrates an enlarged partial view of an example assembly according to Figure 38;
- FIG. 40 schematically illustrates an enlarged partial view of another example of an assembly according to Figure 38;
- FIG. 41 schematically illustrates respectively a partial view of an example assembly according to the present document, and two enlarged partial views of the example assembly in two different configurations;
- FIG. 42 schematically illustrates a partial view of an example of a hydrostatic annular seal
- FIG. 43 schematically illustrates a partial sectional view of an exemplary assembly according to the present document
- FIG. 44 schematically illustrates a partial sectional view of another example of an assembly according to the present document.
- FIG. 45 schematically illustrates a partial sectional view of another example of an assembly according to the present document.
- FIG. 46 schematically illustrates a partial sectional view of another example of an assembly according to this document.
- This document relates to an annular sealing gasket such as a hydrostatic annular sealing gasket used in a turbomachine. It includes in particular different embodiments and integration forms of such a hydrostatic annular sealing gasket.
- FIG. 3 schematically representing a partial view of a hydrostatic annular seal 51 according to the present document.
- this hydrostatic annular seal 51 is integrated into an assembly 52 for a turbomachine with a longitudinal axis X.
- Such an assembly is implemented in a turbine, in particular a low-pressure turbine, of a turbomachine.
- the present document also relates to any type of turbomachine comprising such a turbine, for example a turboprop or a turbojet for aircraft.
- the assembly 52 comprises a cylindrical shell 53 intended to be driven in rotation about the longitudinal axis X and an annular row of stator blades.
- the assembly may also comprise two annular rows of moving blades arranged longitudinally on either side of the annular row of stator blades 54 and connected to each other by the cylindrical shell 53.
- the annular row of stator blades 54 carries the hydrostatic annular seal 51.
- This hydrostatic annular seal 51 is arranged radially inside the annular row of stator blades 54 and radially outside the cylindrical shell 53, the hydrostatic annular seal 51 cooperating in a contactless sealing manner with the cylindrical shell 53.
- the hydrostatic annular seal 51 preferably comprises a radially external annular wall 55, a radially internal annular wall 56 and a plurality of elastically deformable members or elements 57, in particular distributed circumferentially around the longitudinal axis X.
- the hydrostatic annular seal 51 can deform radially thanks to the flexibility offered by the elastically deformable member 57 connecting together the radially internal annular wall 56 and the radially external annular wall 55.
- the radially internal 56 and external 55 annular walls and the elastically deformable element 57 are in particular dimensioned to control the radial deformation of the hydrostatic annular seal 51, and therefore control a clearance J2 between the hydrostatic annular seal 51 and the cylindrical shell 53.
- the seal may comprise a plurality of seal sectors distributed circumferentially around the longitudinal axis, each seal sector comprising a radially inner annular wall sector 56 and a radially outer annular wall sector 55 connected to each other by an elastically deformable member 57.
- the radially outer annular wall sectors may form a monolithic outer shell, i.e. a single piece, and the radially inner annular wall sectors are distinct and arranged circumferentially end to end.
- a turbine is a system that expands air, starting from a high pressure upstream to a low pressure downstream. It is necessary for there to be a maximum of air that passes through the turbine and does not escape from the vein.
- a layer of air coming from the annular cavity located upstream of the seal 51 passes between the cylindrical shell 53 and the seal 51 whose differences in radial dimensions form the clearance J2.
- the hydrostatic annular seal 51 thus provides a seal. It is the pressure differential between the annular cavity upstream of the hydrostatic annular seal 51 and the annular cavity immediately downstream of this hydrostatic annular seal 51 which controls the resultant of the radial pressure forces applied to the radially internal annular wall 56 of the hydrostatic seal 51.
- the hydrostatic annular seal 51 comprises an internal surface 59 arranged radially opposite the cylindrical shell 53.
- This internal surface 59 comprises a first substantially cylindrical surface portion 60, a second concave curved surface portion 61 with a concavity curved radially outwards so as to form an annular cavity opposite the cylindrical shell 53, a third substantially cylindrical surface portion 62 and a fourth truncated surface portion 63 with a section increasing downstream.
- the clearances j1 and j2 are such that the clearance j1 is greater than j2.
- This difference in clearances between j1 and j2 generates a restriction.
- This restriction allows the air to be accelerated and causes static pressure to be lost in the event of a high clearance j1 (>0.6 mm for example).
- the hydrostatic annular seal 51 deforms under the resultant of the mechanical forces exerted on the internal surface 59 and the external surface 63 of the sectorized pad 58.
- This specific configuration allows a low clearance to be maintained and therefore efficient sealing, without risking contact between the sectorized pad 58 and the ferrule 53.
- the annular row of stator blades 54 comprises a radial annular partition 64 carrying the hydrostatic annular seal 51.
- the hydrostatic annular seal 51 may comprise radial sliding means 65 in the direction of the annular row of stator blades 54.
- the radially external annular wall 55 is connected to an annular part 71 comprising an upstream annular tab 66 and a downstream annular tab 67 each comprising longitudinally facing orifices 68 in which pins 69 are mounted.
- the external annular wall 55 and the annular part 71 may be formed from a single piece.
- the pins 69 are mounted shrink-fitted in the orifices 68 of one of the upstream 66 and downstream 67 annular tabs only so as to allow insertion into the other of the upstream 66 and downstream 67 annular tabs.
- the shrink-fitting is carried out on the upstream annular tab 66.
- the radial annular partition 64 of the annular row of stator blades 54 comprises a plurality of preferably oblong openings 70 in which are mounted an intermediate part of the pins 69. Alternatively, the openings can be rectangular.
- This assembly allows a degree of freedom in the radial direction of the hydrostatic annular seal 51 relative to the annular row of stator blades 54. Other means of radial displacement could be envisaged.
- the radial sliding of the hydrostatic annular seal 51 can be carried out as in FIGS. 21 to 26, but also as in FIGS. 27 to 33.
- FIGS 4 and 5 show the hydrostatic annular seal 51 provided with the secondary seal 72 and fixed to the annular row of stator blades 54.
- This hydrostatic annular seal 51 is intended to be arranged longitudinally between two annular rows of rotor blades 73 arranged on either side of an annular row of stator blades 54.
- the hydrostatic annular seal 51 comprises a radially internal annular wall 56, a radially external annular wall 55 connected to each other by the elastically deformable members 57.
- An annular flange is arranged opposite the upstream faces 74 of the elastically deformable members 57. This flange is carried by the radially external annular wall 55.
- a first annular row of first sheet metal sectors 77 is arranged circumferentially end to end and applied to an upstream face 78 of the crown 75.
- a second annular row of second sheet metal sectors 79 is applied to upstream faces 80 of the first annular row of first sheet metal sectors 77.
- the sheet metal sectors 77, 79 have a thickness of between 0.1 and 0.6 mm.
- the second sheet metal sectors 79 may be arranged circumferentially by being offset relative to the first sheet metal sectors 77 so that a second sheet metal sector 79 is arranged facing longitudinally two circumferentially adjacent first sheet metal sectors.
- the inner edges 81 of the second sheet metal sectors 79 are aligned longitudinally with the inner edges 82 of the first sheet metal sectors 77.
- the outer edges 83 of the second sheet metal sectors 79 are aligned longitudinally with the outer edges 84 of the first sheet metal sectors 77.
- the circumferential edges 85, 86 of the first sheet metal sectors 77 are misaligned with the circumferential edges 87, 88 of the second sheet metal sectors 79.
- the misalignment of the circumferential edges 85, 86, 87, 88 of the first 77 and second sheet metal sectors 79 makes it possible to avoid a leak linked to the annular clearance.
- the radially internal ends 89 of the first sheet metal sectors 77 bear on a radial face 90 of the radially internal annular wall 56.
- the flange 75 comprises an internal annular rim 91a which extends upstream.
- An upstream face 92 of the crown 75 is formed at the upstream end of the internal annular rim 91a of the flange 75.
- the first annular row of the first sheet metal sectors 77 is arranged circumferentially end to end and applied to the upstream face 92 of the crown 75.
- the material of the first sheet metal sectors and that of the flange is determined so as to facilitate sliding between these two parts.
- the flange 75 also includes an annular flange 91 b extending downstream and formed at its radially outer end. As can be seen in FIG. 5, the annular flange 91 b radially covers the upstream ends of the radially outer annular wall sectors.
- the sheet metal sectors 77, 79 are fixed to the ring 75 by fixing elements 93 passing through openings 94 on the sheet metal sectors 77, 79.
- These fixing elements 93 fix the first 77 and second sheet metal sectors 79 together to the ring 75, itself carried by the radially external annular wall 66.
- the fixing elements may be pins.
- the openings 94 are such that there is play and that the sheet metal sectors 77, 79 are able to move slightly.
- FIG. 8 represents a hydrostatic annular seal 150 intended to provide sealing between an annular stator row to which it is connected and a cylindrical shell as described with reference to FIG. 2.
- the annular seal 150 which is of a known type comprises an internal annular wall 151 formed of sectors 152 arranged circumferentially end to end.
- It also comprises an external annular wall 153 from which at least one annular tab or wall 154 can extend comprising at least one orifice 155 for the insertion of an axis preferably materialized by a pin, or by the smooth shaft of a screw, or a spacer as an alternative, intended to cooperate with an oblong opening of a radial annular partition carried by the internal annular platform of the annular row of stator blades.
- Each radially internal annular wall sector 152 is connected to the external annular wall 153 by an elastically deformable member 156.
- each radially internal annular wall sector is associated with an elastically deformable member 156.
- Each elastically deformable member 156 comprises two elastic strips 159 extending circumferentially and parallel to each other. First ends of the strips 159 are connected to a first radial tab 158 carried by a radially internal annular wall sector and second ends of the strips 159 are connected to a second radial tab 157 carried by the radially external annular wall 153. If this type of embodiment proves effective, it does not make it possible to achieve the best compromise between radial flexibility and resistance to torsion for a given thickness of strips as mentioned with reference to the prior art at the beginning of the description.
- a hydrostatic annular seal 100 is provided formed from a plurality of circumferentially distributed sealing gasket sectors, only one being shown in FIG. 9.
- Each sealing gasket sector 102a, 102b comprises a radially external annular wall sector 106a, 106b and a radially internal annular wall sector 110a, 110b connected to each other by an elastically deformable member 105a, 105b, in which the circumferentially adjacent sealing gasket sectors 102a, 102b two-by-two have their respective elastically deformable member 105a, 105b produced monolithically in a common deformable elastic member 105, the common deformable elastic member 105 connecting together two annular wall sectors 110a, 110b.
- each common elastic member 105 is elastically connected to at least two sectors of radially internal annular walls 110a, 110b, here exactly two, which are circumferentially adjacent and to two sectors 106a, 106b of radially external annular wall 106.
- the sectors of radially internal annular walls 110a, 110b successively form the radially internal annular wall of the hydrostatic annular seal 100.
- each elastically deformable member 105 is connected to two circumferentially adjacent internal sectors 110a, 110b, one 110a being named as being a primary sector and the other 110b being named secondary sector.
- each common elastic member 105 comprises at least one first elastically deformable circumferential blade 112a, 112b and at least one second elastically deformable circumferential blade 114a, 114b connected by first circumferential ends facing each other to the external annular wall and of which second ends 122 circumferentially opposite one another relative to the first ends are each connected to the primary sector 110a and to the secondary sector 110b.
- Said first end 116 of said at least one first blade 112a, 112b and said first end 116 of said at least one second blade 114a, 114b are arranged in a circumferential screw.
- said at least one first blade 112a, 112b and said at least one second blade 114a, 114b comprise two blades which are radially spaced from one another.
- the first blades 112a, 112b and/or the second blades 114a, 114b may be substantially parallel to one another as shown in Figure 9.
- the first blades 112a, 112b and/or the second blades 114a, 114b may also form an angle between them.
- a first blade 112b is a first inner blade 112b and the other 112a is a first outer blade.
- a second blade 112b is a second inner blade and the other 112a is a second outer blade.
- the first ends 116 of the first and second elastic blades may be connected, as shown in FIG. 9, to the same first leg 118 which may extend substantially radially.
- the first internal blade 111 b and/or the second internal blade 114 b may be connected to the radially internal end of the first leg 118.
- the first external blade 112 a and/or the second external blade 114 a may be connected in the vicinity of the radially external end of the first leg 118, this radially external end of the first leg 118 being connected to the radially external annular wall.
- the radially internal end of the first leg 118 is devoid of direct connection to one of the two circumferentially adjacent primary 10a and secondary 110b sectors, the connection of the first leg 118 with the sectors 110a, 110b being achieved indirectly by the first 112a, 112b and second blades 114a, 114b and the second legs 120a, 12ab, the latter being described in the following paragraphs.
- the legs are sized so as not to be deformable, the deformation taking place at the level of the blades.
- the second ends 122 of the first and second elastic blades may be connected, as shown in FIG. 9, to a second leg 120a, 120b which may extend substantially radially. It is observed that there are two second legs 120a, 120b which are arranged on either side circumferentially of the first leg 118 and which may be positioned circumferentially in a manner substantially symmetrical to each other relative to the position of the first leg 118.
- a second leg called the second primary leg 120a is connected to the second ends of the first blades 112a, 112b and a second leg called the second secondary leg 120b is connected to the second ends of the second blades 114a, 114b.
- the common elastically deformable member thus has a first circumferential end radial tab 120a connected to a circumferential end of the internal annular wall sector 110a of a first seal sector 102a and a second circumferential end radial tab 120b connected to a circumferential end of the internal annular wall sector 110b of a second seal sector 102b, each circumferential end radial tab 120a, 120b being connected to a common radial tab 118 by a first blade 112a, 112b and a second blade 114a, 114b which each extend circumferentially to connect each circumferential end radial tab 120a, 120b to a common radial tab 118.
- the term “primary” and the term “secondary” only allow a distinction to be made between the two second legs 120a, 120b and their connection to the primary 110a and secondary 110b sectors.
- the first outer blade 112a and/or the second outer blade 114a may be connected to the radially outer end of the second primary 120a and secondary 120b legs.
- the first inner blade 112b and/or the second inner blade 114b may be connected in the vicinity of the radially inner end of a second leg 120a, 120b, this radially inner end of a second leg 120a, 120b being connected to a shoe 110a, 110b.
- the radially inner end of the second primary leg 120a is connected to the primary sector 110a and for example in the vicinity of a circumferential end thereof.
- the radially internal end of the second secondary leg 120b is connected to the secondary pad 110b and for example in the vicinity of a circumferential end thereof. Said two ends of the primary 110a and secondary 110b sectors are opposite their ends which are circumferentially opposite.
- the annular seal 100 could comprise means allowing radial sliding of the hydrostatic annular seal relative to the radial annular partition of the annular row of stator blades. These means could be, for example, of the type described with reference to FIGS. 21 to 25 or with reference to FIGS. 27 to 33.
- FIGS 10 to 16 schematically illustrate a third hydrostatic annular seal 201 as well as variations thereof.
- Figure 10 shows a hydrostatic annular seal 201 comprising a radially inner annular wall 202, an elastically deformable member 203 and a radially outer annular wall 204.
- the radially inner annular wall 202 is formed of a plurality of sectorized pads 205.
- the sectorized pad 205 shown is connected to the radially outer annular wall 204 by the elastically deformable member 203.
- This elastically deformable member 203 comprises an inner tab 206 and an outer tab 207. Each tab 206,207 is substantially planar.
- the inner tab 206 has a radially inner end 208 to which said sectored pad 205 is fixed.
- the outer tab 207 has a radially outer end 209 to which the radially outer annular wall 204 is fixed.
- the inner tab 206 has a radially outer end 210 connected to a radially inner end 211 of the outer tab 207 by a connecting wall 215.
- the inner tab 206 and the outer tab 207 extend radially such that the radially inner end 211 of the outer leg 207 is arranged radially inside the radially outer end 210 of the inner leg 206.
- the hydrostatic annular seal 201 shown in FIG. 11 comprises an elastically deformable member 203 formed of several elastically deformable members. It thus comprises a first elastically deformable member 212 and a second elastically deformable member 213.
- the first 212 and second 213 elastically deformable members are arranged such that the internal tab 206, respectively the external tab 207, of the first member 212 is axially adjacent to the external tab 207, respectively the internal tab 206, of the second member 212.
- the hydrostatic annular seal 201 shown in FIG. 12 comprises an elastically deformable member 203 formed of three elastically deformable members, a first member 212, a second member 213 and a third member 214.
- the first 212 and second 213 members are arranged so that the internal tab 206, respectively the external tab 207, of the first member 212 is axially adjacent to the external tab 207, respectively the internal tab 206, of the second member 213.
- the third member 214 is arranged so that its external tab 207, respectively its internal tab 206, is axially adjacent to the internal tab 206, respectively the external tab 207, of the second member 212.
- the outer tab 207 may be inclined relative to a tangent to the radially outer annular wall 204 at the connection point between the outer tab 207 and the radially outer annular wall 204.
- the inner tab 206 may be inclined relative to a tangent to the radially inner annular wall 202 at the connection point between the inner tab 206 and the radially inner annular wall 202. This angle may be between 10° and 150°. It is thus understood that the inner tab 206 and the outer tab 207 may have different inclinations as clearly appears in FIG. 13. Other embodiments are of course possible.
- the inclination of the tabs 207, 206 relative to the radial direction makes it possible to restrict the movement of the elastically deformable member in the longitudinal direction.
- Each connecting wall 215 may comprise a thickness, defined by the radial dimension of the connecting wall 215, of between 0.5 and 10 mm and/or a width, defined by the longitudinal dimension of the connecting wall 215, of between 2 and 30 mm.
- Each leg 206, 207 may comprise at least one of the following parameters:
- a dimension perpendicular to the direction of extension of the leg between 0.5 and 10 mm.
- the hydrostatic annular seal 201 comprises first 212 and second 213 members.
- the connecting wall 215 makes it possible to restrict the upstream/downstream tilting movements due to its resistance to torsion.
- the internal and external legs 206, 207 which are also deformable allow a predominantly radial movement by bending of the elastically deformable member.
- the inclination of the legs 206 and 207 relative to the internal annular wall 202 and external 204 makes it possible to limit the movement of the shoe 205 along the longitudinal axis
- the hydrostatic annular seal 201 may comprise a first 212 and a second 213 elastically deformable members.
- the connecting wall 215 of the first member 212 comprises a radially internal surface formed successively by a concave surface 216 then a convex surface 217.
- the connecting wall 215 of the second member 213 comprises a radially internal surface formed successively by a convex surface 217 then a concave surface 216.
- the hydrostatic annular seal 201 shown in FIG. 16 comprises an elastically deformable member 203 comprising a first 212 and a second 213 member.
- the connection between the radially external end 210 of the internal tab 206 and the connecting wall 215 of each member is at a right angle.
- the connection between the radially internal end 211 of the external tab 207 and the connecting wall 215 of each member is also at a right angle.
- FIG. 16 illustrates the oblique inclination of the members 212, 213.
- FIGS 17 to 20 schematically illustrate alternative embodiments of the connecting tabs of the connecting walls 215 to the radially internal annular walls 202 and external 204 for a hydrostatic annular seal 201. Only an external tab 207 is illustrated but the description also applies to an internal tab 206.
- Figure 17 shows a tab 207 with a substantially constant section between its internal and external ends.
- Figure 18 illustrates a leg 207 with a section which evolves radially and which increases in the particular case of figure 18.
- the general shape here is triangular.
- Figure 19 shows a leg 207 having a circumferential surface facing the other leg which is concave and an opposite circumferential surface which is substantially planar.
- Figure 20 also shows a tab 207 having concave and planar circumferential surfaces as in Figure 19. However, in this embodiment, the radially inner end of the tab has a smaller dimension than the radially outer end.
- the hydrostatic annular seal 201 comprises at least one material or a combination of materials from the following list: steel, titanium, aluminum alloy, cobalt-based alloy, nickel-based alloy and/or any composite material.
- FIG. 21 there is shown a sector 310 of an annular row or crown of stator blades which is here a distributor. Such sectors are arranged circumferentially end to end to form the crown of stator blades.
- This crown carries a hydrostatic annular seal 300 which is shown in Figure 26. It could be of any type as described in the present description, for example those described with reference to Figures 9 or Figures 10 to 20.
- All of the distributor crown sectors 310 are identical so that the following description, which relates to one sector of FIG. 21, applies to each of the other distributor sectors 310.
- the sector comprises an internal platform 312, an external platform 314 and blades 316.
- the blades 316 are each connected on the one hand to the internal platform 312 and on the other hand to the external platform 314 so as to extend radially through a primary air stream, which is radially delimited by these platforms 312, 314.
- the blades of the sector 310 are circumferentially spaced from each other.
- the external platform 314 is configured to be fixed on a casing of the turbomachine 1.
- the sector 310 comprises a radial partition 305 forming the foot of the distributor 310 and which is connected to the internal platform 312 so as to extend radially inwards from the internal platform 312, towards a cylindrical shell 11 of the rotor, the cylindrical shell being shown in FIG. 2 or FIG. 38 or FIG. 41.
- the radial partition 305 is configured to cooperate with a hydrostatic annular seal 300 (FIG. 26).
- the hydrostatic annular seal 300 comprises a sectorized radial annular wall 320, formed of a plurality of rapidly internal annular wall sectors arranged circumferentially end to end. The latter are connected by elastically deformable members 322 to a radially external annular wall 325 fixed to the seal support 324 which comprises a radially external annular wall 323 and radially outwardly at least one radial annular tab 326, preferably two radial annular tabs as illustrated in FIG. 22.
- Figure 22 shows only a circumferential section of the seal support 324.
- the radial annular legs 326 or flanges are substantially parallel and longitudinally spaced from each other so as to form a U-shaped section defining a space into which the radial partition 305305 of each of the sectors 310310 can be inserted.
- the longitudinal distance between the legs 326 is chosen so as to allow adequate longitudinal positioning and maintenance in longitudinal position of the sectors 310, while allowing its mobility by radial sliding of the partition 305 between the legs 326 (see below).
- an axial or longitudinal clearance J1, J2 is left during assembly between the legs 326 and the partition 305 to allow this radial movement.
- the clearance J1 extends between the upstream leg 326 and the partition 305, and the clearance J2 extends between the partition 305 and the downstream leg 326.
- the partition 305 is mounted with a radial clearance J3 relative to the bottom of the space defined by the legs 326.
- the radially external annular wall 324 is formed in a single piece with the elastically deformable members 322, with the radially internal annular wall 320 and with at least one of the annular legs 326.
- Figure 23 shows two orifices 328 made respectively in the upstream tab 326 and the downstream tab 326.
- the orifices 328 have a common axis A2 and are designed to receive a pin 330 such as that shown in the figure.
- the pin 330 is a cylindrical part with axis A2 having two shoulders which define an upstream part 332, an intermediate part 334 and a downstream part 336.
- the intermediate portion 334 has a diameter smaller than the diameter of the upstream portion 332 and the downstream portion 336.
- the diameter of the upstream portion is furthermore smaller than that of the downstream portion.
- the orifice 328 of the upstream tab 326 of the hydrostatic annular seal 300 is sized to receive the upstream portion 332 of the pin 330 so as to form a tight fit.
- the orifice 328 of the downstream tab 326 of the hydrostatic annular seal 300 is sized to receive the downstream portion 336 of the pin so as to form a tight or sliding fit.
- the pin 330 is thus carried by the upstream 332 and downstream 436 legs, forming a complete connection with it.
- the pin 330 is configured to cooperate with the distributor, in particular with the radial partition 305 of the sector 310.
- the partition 310 of each of the sectors comprises for this purpose an opening 338 which has an oblong shape of the groove type extending radially.
- the opening 338 opens radially towards the inside of the crown sector 310. It could not open radially. This would require different geometric arrangements of the pin and different assembly steps than those presented here.
- the opening 338 has a width, or circumferential dimension, allowing it to be crossed by the intermediate part 334 of the pin 330, that is to say a width greater than the diameter of the intermediate part 334 of the pin 330.
- the width of the opening 338 is also less than the diameter of the upstream part 332 and the downstream part 336 of the pin 330.
- the assembly of this stator element comprises a pre-insertion of the pin 330 into the upstream and downstream legs 326 by passing the upstream part 332 of the pin 330 through the orifice 328 of the downstream leg 326.
- the pin 330 is then fixed to the legs by forced insertion of its upstream part 332 into the orifice 328 of the upstream leg 326 and, simultaneously, of its downstream part 336 into the orifice 328 of the downstream leg 326.
- the sector 310 is then moved radially inwards so as to introduce the partition 305 axially between the legs 326 and to insert the intermediate part 334 of the pin 330 into the opening 338 of the partition 305.
- the pin 330 forms on the one hand a circumferential stop for the crown sector 310, preventing a displacement of the hydrostatic annular seal 300 and the crown sector 310 relative to each other in rotation around the axis of the sector 310 and making it possible to center the hydrostatic annular seal 300 relative to this axis A1.
- the assembly allows a radial displacement of the hydrostatic annular seal 300 relative to the sector 310.
- each of the sectors 310 of the distributor can cooperate with several pawns similar to pawn 330.
- the invention makes it possible to connect the hydrostatic annular seal 300 and the distributor 310 to each other according to a connection defining a radial degree of freedom or radial sliding capable of compensating for differential thermal expansions within the turbine 9.
- the hydrostatic annular seal 419 thus comprises a radially internal annular wall 420 which is sectorized and a radially external annular wall which is also sectorized 401.
- the seal support 402 comprises longitudinal and circumferential projections 415 defining between them radial notches in which are engaged radial tabs 416 formed in radially outward projection from the radially external annular wall sectors 401 of the hydrostatic annular seal. This form cooperation makes it possible to lock the annular seal in rotation on the seal support 402
- a sheet metal 414 may be interposed longitudinally between the radial annular partition 403 and the seal support 402.
- the sheet metal 414 comprises two radial annular branches connected to each other by a substantially cylindrical base.
- the branches comprise free end portions which are curved radially inwards so as to form a curved portion which cooperates by form connection with a lateral outgrowth of the annular legs 404, 402 of the annular seal support.
- Each elastically deformable member 407 may be elastically connected to at least two circumferentially adjacent radially inner annular wall sectors 408a, 408b. In the embodiment shown in FIGS. 28, 29 and 32, each elastically deformable member 407 is connected to two circumferentially adjacent radially inner annular wall sectors, one being referred to as a primary sector and the other being referred to as a secondary sector.
- each elastically deformable member 407 comprises at least one first blade
- said at least one first blade 408 and said at least one second blade 409 comprise two blades which are radially spaced from each other.
- the first blades and/or the second blades may be substantially parallel to each other as shown in Figures 28, 29 and 32.
- the first blades and/or the second blades may further form an angle between them.
- a first blade 408 is a first inner blade 408 and the other is a first outer blade 408.
- a second blade 409 is a second inner blade 409 and the other is a second outer blade 409.
- first ends of the first and second elastic blades may be connected, as shown in FIGS. 28, 29 and 32, to the same first leg 410 which may extend substantially radially.
- the first internal blade 408 and/or the second internal blade 409 may be connected to the radially internal end of the first leg 410.
- the radially inner end of the first leg 410 is devoid of direct connection to one of the two circumferentially adjacent pads, the connection of the first leg 410 with the radially annular wall internal being achieved indirectly by the first and second blades and the second legs, the latter being described in the following paragraphs.
- Said second ends of the first and second elastic blades can be connected, as shown in FIGS. 28, 29 and 32, to a second leg 411 which can extend substantially radially. It is observed that there are two second legs 411 which are arranged on either side circumferentially of the first leg 410 and which can be positioned circumferentially in a manner substantially symmetrical to each other relative to the position of the first leg 410.
- a second leg 411 called the second primary leg 411 is connected to the second ends of the first blades and a second leg 411 called the second secondary leg 411 is connected to the second ends of the second blades.
- the first external blade 408 and/or the second external blade 409 may be connected to the radially external end of the second primary and secondary legs.
- the first internal blade 408 and/or the second internal blade 409 may be connected in the vicinity of the radially internal end of a second leg 411, this radially internal end of a second leg 411 being connected to a pad. More precisely, the radially internal end of the second primary leg 411 is connected to the primary pad and for example in the vicinity of a circumferential end thereof.
- the radially internal end of the second secondary leg 411 is connected to the secondary pad and for example in the vicinity of a circumferential end thereof. Said two ends of the primary and secondary pads are opposite their ends which are circumferentially opposite.
- a ring or spacer 413 acts as an axis for the free expansion of the seal support 402.
- the radially external annular wall 401 is formed by a radial ring 417.
- This hydrostatic annular seal 501 comprises a sectored radially external annular wall 502, a sectored radially internal annular wall 503 and an elastically deformable member 504 arranged between said two internal and external walls.
- the radially outer annular wall 502 is fixed in a seal support 505.
- Each sector of the radially outer annular wall 502 carries a coupling member 506 engaged circumferentially and retained radially in a circumferential groove of the seal support 505.
- the coupling member 506 has a dovetail shape extending circumferentially.
- the seal support 505 comprises an upstream wall 507 extending radially inward and formed opposite the upstream face of the hydrostatic annular seal 501 so as to participate in sealing the member elastically deformable 504.
- the annular part 505 comprises an upstream annular tab 508 and a downstream annular tab 509.
- the upstream annular tab 508 and the downstream annular tab 509 form a U capable of sliding radially on a radial annular partition of an annular row of stator blades as illustrated in FIG. 21.
- the radial annular partition may comprise oblong or rectangular openings opening radially inwards and in which are engaged fixing means passing through the upstream and downstream tabs of the seal support 505.
- the fixing means may comprise pins as described with reference to FIGS. 24 and 25.
- Figure 34B illustrates the presence of a blocking member of the radially external annular wall sector on the joint support 505.
- the blocking is here achieved by a pin 513 engaged and shrunk through the support and the coupling member 506 of the joint 501.
- the seal support may be a 360° part which includes a lateral opening 509 opening into the circumferential groove of the seal support.
- the circumferential groove is made accessible to allow mounting by longitudinal translation of each sealing gasket in the lateral opening and then by rotation.
- the annular seal could be of any type.
- it may be of the type described with reference to FIG. 9 and comprise two radially internal annular wall sectors 510a, 510b each formed monolithically with a radial tab 515.
- Each radial tab 515 is connected to the same tab 514 arranged circumferentially between the two tabs 515. Details of the production of the seal can be read with reference to FIG. 9.
- the coupling of the seal support 505 and the seal 401 can be produced with other seals of the present document such as the seal described with reference to FIGS. 10 to 15.
- annular flange 519 is mounted on the downstream face of the seal in order to block the lateral opening.
- the flange thus comprises protrusions 517 bolted to the seal support 505.
- Figure 36 illustrates a particular embodiment of a hydrostatic sealing annular seal 600.
- a hydrostatic annular seal 600 comprises a radially inner annular wall and a radially outer annular wall between which elastically deformable members are formed.
- the present description in relation to FIG. 36 is applicable to any of the annular seals described with reference to the figures.
- the elastically deformable seal could be of the type described with reference to FIG. 9, or one of FIGS. 10 to 15.
- a radial tab 618 and an elastically deformable blade 620 or strip can be seen.
- the radially inner annular wall is sectorized and comprises a plurality of sectors 610 arranged circumferentially end to end.
- Each sector 610 comprises a first circumferential edge 612 and a second circumferential edge (not shown) circumferentially opposite the first edge 612.
- the first circumferential edge 612 of a sector 610 is placed circumferentially end-to-end with a second circumferential edge of a circumferentially adjacent sector 610.
- a slot 614 is formed in the thickness of the sector 610 and in the first circumferential edge 612 thereof.
- This slot 614 opens out circumferentially and may have a substantially rectangular shape in section.
- the same slot 614 is formed in the second circumferential edge of each sector pad.
- a tab 616 is mounted partly in a slot 614 of a first circumferential edge 612 and in a circumferentially facing slot 614 of a second circumferential edge of a circumferentially adjacent pad 610.
- each internal sector 610 may comprise a radially internal surface comprising a first portion 610a of substantially cylindrical surface, a second portion 610b of surface formed by a recess, a third portion 610c of substantially cylindrical surface and preferably a fourth portion 610d of frustoconical surface with a section increasing downstream.
- the recess extends from one circumferential end to the other of the sector 610 and has a concave curved shape which may be formed of a longitudinal succession of flat surfaces.
- a housing as mentioned in FIG. 37 could also be formed in the recess.
- the slot 614 is formed substantially radially outside the recess such that a plane perpendicular to the longitudinal axis intercepts both the slot 614 and the recess.
- the slot extends to the third part 610c.
- the slot is open circumferentially and axially upstream.
- the upstream opening is closed by a sealing part (not shown) which prevents air circulation at the upstream outlet. Sealing such as that described with reference to FIGS. 5 to 7 can be used.
- FIG. 37 showing a hydrostatic annular seal 700 comprising a radially external annular wall 710 and a radially internal annular wall 712 which is sectorized and formed of a plurality of sectors 714 arranged circumferentially end to end. Elastically deformable members 716 are arranged radially between the internal 712 and external 710 walls.
- This seal 700 can be mounted at the radially internal end of an annular row of stator blades of a turbomachine. It could be mounted at any other location where it could perform the same function, for example at a radially external end of an annular row of stator blades or at the interface between any rotating and fixed part in a turbomachine.
- each elastically deformable member 716 may comprise two substantially radial legs 718, 720, a first 720 of which is connected to the sector 714 and a second 718 of which is connected to the external annular wall 710. The two legs 718, 720 are connected to each other by elastic blades 722.
- a housing 724 on the radially internal face of each sector 714, this housing 724 opening radially inwards, this housing 724 having upstream and downstream faces 724a, circumferential faces 724b formed in the thickness of the sector 714.
- the housing also comprises a bottom wall 724c connecting the radially external ends of the circumferential walls 724b, upstream and downstream 724a.
- Parts A, B, C and D of FIG. 37 represent different orientations of the seal and in section for part B, part C and part D.
- the housing 724 may have a substantially parallelepiped shape, that is to say, the side or circumferential walls 724b, upstream and downstream 714a and bottom 724c are substantially flat, if we disregard the connecting radii of said walls between them.
- the housing 724 may be substantially centered circumferentially on the circumferential extent of the sector 714.
- the housing 724 thus produced does not open circumferentially or longitudinally since the circumferential faces 724b facing each other and the upstream and downstream faces 724a facing each other are formed in the thickness of the sector 714.
- the housing 724 may extend circumferentially for a distance less than 80% of the circumferential extent of the sector. Also, the housing 724 may extend longitudinally for a distance less than 50% of the longitudinal extent of the sector 714.
- each housing 724 has a depth of at least 50% of the maximum radial dimension of the sector 714.
- the radially internal surface of the sector 714 comprises a first substantially cylindrical surface portion 726a, a second surface portion 716b forming a recess, a third substantially cylindrical surface portion 726c and a fourth frustoconical surface portion 726d with a section increasing downstream.
- the housing 724 is formed in the annular recess 726b.
- the recess 726 may have a concave curved shape. Here it is composed of a succession of conical surfaces.
- the elastic members 716 could have the shape of those described with reference to FIGS. 9 to 12.
- the primary sector and the secondary sector are each provided with a housing 724 formed in the thickness thereof.
- the integration of a housing 724 as described with reference to FIG. 37 could be achieved on any of the annular seals and assemblies described herein.
- the annular seal 700 could further comprise slots formed in the circumferential edges of each sector for receiving a sealing tab as described with reference to FIG. 36.
- FIG 38 schematically representing a partial view of an assembly 800 for a longitudinal axis turbomachine according to the present document.
- an assembly is implemented in a turbine, in particular a low pressure turbine, of a turbomachine as previously described with reference to Figure 1.
- the present document also relates to any type of turbomachine comprising such a turbine, for example a turboprop or a turbojet for an aircraft.
- the assembly 800 comprises a cylindrical shell 811 intended to be driven in rotation about the longitudinal axis and an annular row of stator blades 820.
- the assembly 800 may also comprise two annular rows of moving blades 810 arranged longitudinally on either side of the annular row of stator blades 820 and connected to each other by the cylindrical shell 811.
- the annular row of stator blades 820 carries an annular hydrostatic seal 822 arranged radially inside the annular row of stator blades 820 and radially outside the cylindrical shell 811, the annular hydrostatic seal 822 cooperating in a contactless seal with the cylindrical shell 811.
- the cylindrical shell 811 comprises an annular layer 812 facing the hydrostatic annular seal 822 which is made of a first material having a hardness greater than a hardness of a material of a radially internal end 823 of the hydrostatic annular seal 822 facing the annular layer 812.
- the cylindrical shell 811 has in particular a circular section of constant radius along the longitudinal axis on at least one longitudinal portion of the cylindrical shell. This shape allows for better control of the clearance between the hydrostatic annular seal and the cylindrical shell. In particular, the cylindrical shell 811 is devoid of lip seals.
- the hydrostatic annular seal preferably comprises a radially outer annular wall, a radially inner annular wall and a plurality of elastically deformable members, in particular distributed circumferentially around the longitudinal axis.
- Each of the plurality of elastically deformable members comprises a first substantially radial leg connected to the radially outer annular wall, a second substantially radial leg connected to the radially inner annular wall and at least one elastically deformable blade extending circumferentially. Said at least one blade is connected to the first leg at a circumferential end and to the second leg at an opposite circumferential end.
- the first tab provides the connection between one of the circumferential ends of said at least one blade and the radially outer annular wall
- the second tab provides the connection between the other of the circumferential ends of said at least one blade and the radially inner annular wall.
- the hydrostatic annular seal can thus deform radially thanks to the flexibility offered by said at least one blade connecting together the radially inner annular wall and the radially outer annular wall.
- the radially inner and outer annular walls, the tabs and the blades are in particular dimensioned to allow the radial deformation of the hydrostatic annular seal to be controlled, and therefore to control a clearance between the hydrostatic annular seal and the cylindrical shell.
- Such a deformable member is illustrated in FIG. 8.
- the elastically deformable member could also be of the type described with reference to Figures 9 to 12.
- the first material must then have a hardness greater than that of the skate material.
- the pad made of a material with greater abradability than the coating of the ferrule, ensures that wear during contact between the ferrule and the pad of the hydrostatic seal occurs only on the pad and not on the ferrule.
- the shoe may in particular have an aeraulic shape. This allows, by phenomena of depression and overpressure on either side of the shoe, the increase of a clearance between the cylindrical shell and the hydrostatic annular seal when they approach each other, and conversely, the reduction of the clearance between the cylindrical shell and the hydrostatic annular seal when they move away from each other.
- the hydrostatic annular seal is preferably made of a metallic material.
- the first material may also have an abrasion resistance greater than the abrasion resistance of the material of the radially inner end 823 of the hydrostatic annular seal 822 opposite the annular layer 812.
- a portion 814 of the cylindrical shell 811 extending longitudinally from one to the other of the two annular rows of moving blades 810 is in particular made of a first material having a hardness greater than the hardness of the second material.
- the portion 814 of the cylindrical shell 811 made of the second material connects the two annular rows of moving blades.
- the second material may in particular be adapted to ensure the mechanical transmission of a torque between the two annular rows of moving blades 810.
- the second material may have an abrasion resistance lower than the abrasion resistance of the first material.
- the second material may in particular be steel, a nickel-based alloy or a cobalt-based alloy.
- the first material and the second material have in particular mechanical resistance and temperature resistance characteristics consistent with the thermomechanical operating conditions of the turbomachine.
- the annular layer 812 may have a longitudinal dimension L1 greater than a longitudinal dimension L2 of the hydrostatic annular seal 822 along the longitudinal axis X. Such a feature makes it possible to ensure that the hydrostatic annular seal 822 can be radially opposite the annular layer 812 even in the event of relative longitudinal movement between the cylindrical shell 811 and the annular row of stator blades 820. This relative longitudinal movement is commonly referred to as slewing. Slewing may occur in different operating phases of the turbomachine.
- the cylindrical shell 811 may have an annular recess 813 intended to receive the annular layer 812.
- the annular recess 813 and the annular layer 812 may be of the same thickness. In other words, the annular layer 812 may not add any excess thickness to the cylindrical shell 811.
- the annular layer 812 may form a projection relative to a first radially external surface 815 of the cylindrical shell 811.
- the first radially external surface 815 of the cylindrical shell 811 may in particular correspond to a surface that is the most radially inside of a radially external periphery of the cylindrical shell 811.
- the annular layer 812 may form a ring, i.e. extend over 360°.
- the layer could be partially housed in the shell and partially formed as a projection relative to the external surface of the shell.
- the annular layer 812 may have a radial thickness h so as to provide sufficient mechanical resistance to the annular layer in the event of contact between the cylindrical shell and the hydrostatic annular seal.
- the method then makes it possible to ensure that the annular layer 812 complies with the dimensional constraints, geometric tolerances, and surface condition of the cylindrical shell 811.
- FIG 41 schematically representing a partial section of an assembly 900 for a longitudinal axis turbomachine according to the present document, and two enlarged views of the assembly.
- an assembly is implemented in a turbine, in particular a low pressure turbine, of a turbomachine such as previously described with reference to Figure 1.
- the present document also relates to any type of turbomachine comprising such a turbine, for example a turboprop or a turbojet for an aircraft.
- the assembly 900 comprises a ferrule 931 intended to be driven in rotation around the longitudinal axis X and a stator stage 920 extending around the longitudinal axis X and radially outside the ferrule 931.
- the ferrule 931 may in particular have a cylindrical shape, at least over a portion longitudinal of the shell.
- the shell 931 is in particular devoid of lickers.
- the assembly 900 can also comprise two annular rows of moving blades 930 intended to be driven in rotation about the longitudinal axis X, the two annular rows of moving blades 930 being arranged longitudinally on either side of the annular row of stator blades 920 and connected to each other by the shell 931.
- the stator stage 920 comprises an annular row of stator blades 921. More specifically, the annular row of stator blades 921 comprises a radially outer annular platform and a radially inner annular platform 922 between which a plurality of blades extend. The annular row of stator blades 921 comprises a radial partition 923 which extends radially inward from the radially inner annular platform 922.
- the stator assembly 920 also comprises a hydrostatic annular seal 950 carried by the annular row of stator blades 921 and radially opposite the shroud 931, the hydrostatic annular seal 950 being configured to cooperate in a contactless seal with the shroud 931.
- stator stage 920 and more particularly the annular seal comprises a stop system capable of coming into direct or indirect contact with the ferrule 931 and making it possible to limit the radial displacement of the seal.
- the hydrostatic annular seal may come into contact with the shroud, under the effect of a radial expansion of the latter at overspeed.
- the stop system advantageously makes it possible to reinforce the contact between the stator stage 920 and the shroud 931 to contribute to braking the rotor in the event of overspeed.
- Such an assembly 910 thus makes it possible to passively brake the rotor. The assembly thus makes it possible to protect the mechanical integrity of the rotor in the event of overspeed.
- the hydrostatic annular seal 950 comprises a radially external annular wall 951, a radially internal annular wall 952 and a plurality of elastically deformable members, in particular distributed circumferentially around the longitudinal axis.
- the hydrostatic annular seal 950 preferably comprises a ring 959 extending radially outwards from the radially external annular wall 951.
- the ring may have a U-shaped section, the two branches of the U being arranged on either side of the radial partition. The two branches of the U and the radial partition may be placed in position via centering pins.
- the radially inner annular wall 952 and the radially outer annular wall 951 may in particular be formed respectively of a plurality of inner wall sectors arranged circumferentially end to end and of a plurality of outer wall sectors arranged circumferentially end to end. Each of the inner wall and outer wall sectors are in particular connected to an elastically deformable member of the plurality of elastically deformable members.
- each of the plurality of elastically deformable members 953 comprises a first substantially radial leg 955 connected to the radially external annular wall 951, a second substantially radial leg 956 connected to the radially inner annular wall 952 and at least one elastically deformable blade 954 extending circumferentially. As such, only the blades 954 are capable of deforming, the legs 955, 956 are non-deformable.
- Said at least one blade 954 is connected to the first leg 955 at a circumferential end and to the second leg 956 at an opposite circumferential end.
- the first leg 955 provides the connection between one of the circumferential ends of said at least one blade 954 and the radially external annular wall 951
- the second leg 956 provides the connection between the other of the circumferential ends of said at least one blade 954 and the radially internal annular wall 952.
- the hydrostatic annular seal can thus deform radially thanks to the flexibility offered by said at least one blade connecting together the radially internal annular wall and the radially external annular wall.
- a first clearance J1 (shown in FIG. 41) is defined between the hydrostatic annular seal 950 and the shell 931, corresponding to a nominal clearance in operation between the hydrostatic annular seal and the shell.
- the first clearance can be defined as a cold clearance of the turbine.
- the first leg 955 comprises a radially outer end directly connected to a radially inner face of the radially outer annular wall and a radially inner end which is devoid of direct connection to the radially inner annular wall.
- the second leg 956 comprises a radially inner end directly connected to a radially outer face of the radially inner annular wall and a radially outer end which is devoid of direct connection to the radially outer annular wall.
- first leg 955 and the second leg 956 are particularly adapted to not deform radially. Only the leg 956 is able to move radially with the radially internal annular wall and to move closer to (or further away from) the radially external annular wall.
- Each of the plurality of elastically deformable members 953 may in particular comprise a plurality of radially spaced blades 954, for example two blades.
- the blades are in particular substantially parallel to each other.
- the radially internal annular wall can carry an abradable pad 958 arranged radially opposite the ferrule 931 and capable of wearing in the event of contact with the ferrule 931.
- the abradable pad 958 may in particular have an aeraulic shape. This allows, by phenomena of depression and overpressure on either side of the pad, the increase of a clearance between the ferrule and the hydrostatic annular seal when they approach each other, and conversely, the reduction of the clearance between the ferrule and the hydrostatic annular seal when they move away from each other.
- the stop system 940 comprises at least a first radial stop element 941 carried by the radially external annular wall 951 facing radially the second leg 956 of one of the plurality of elastically deformable members 953.
- the stop elements are here radial protrusions.
- Said at least first radial stop element 941 can also be carried by the radially internal annular wall 952 radially opposite the first leg 955 of one of the plurality of elastically deformable members 953.
- the first radial stop element can come into abutment against the first leg.
- Said at least first radial stop element 941 can also be carried by the second leg 956 of one of the plurality of elastically deformable members 953 radially facing the radially external annular wall 951, or carried by the first leg 955 of one of the plurality of elastically deformable members 953 radially facing the radially internal annular wall 952.
- the first radial stop element 941 can come into abutment against the radially internal annular wall when it is carried by the first leg, or against the radially external annular wall when it is carried by the second leg.
- the stop system 940 may also comprise at least two first radial stop elements 941, one being carried by the second tab 956 radially opposite the radially external annular wall 951 or vice versa, and the other being carried by the first tab 955 radially opposite the radially internal annular wall 952 or vice versa.
- Said at least one first radial stop element 941 makes it possible to reinforce the radial contact between the hydrostatic annular seal and the ferrule, and thus to improve the braking of the ferrule in the event of overspeed.
- the first radial stop element is then advantageously directly integrated into the hydrostatic annular seal, making it easier to implement from the point of view of manufacturing the assembly.
- the first radial stop element 941 can be formed in the mass of the hydrostatic annular seal.
- the first radial stop element 941 may form a radial protrusion.
- the first radial stop element 941 may have a first stop surface 945 substantially parallel to a face against which the first stop surface is capable of coming into abutment.
- a second clearance J2 between the first abutment surface 945 and the face against which the first abutment surface is capable of abutting must be less than or equal to the first clearance J1.
- a second clearance J2 between the first abutment surface 945 and the face against which the first abutment surface is capable of abutting may be 0.2 mm or more.
- the stop system 940 preferably comprises a plurality of first radial stop elements 941.
- each of the plurality of elastically deformable members may comprise one of the plurality of first radial stop elements 941.
- Figures 44 and 45 show exemplary embodiments of the assembly according to the present document.
- the assembly may comprise at least one second radial stop element 942, 943 forming a finger extending radially inward from the annular row of stator blades.
- Said at least one second radial stop element 942, 943 is capable of radially abutting the radially inner annular wall 952 (as shown in Figure 45) and/or the second tab 956 of one of the plurality of elastically deformable members 953 (as shown in Figure 44).
- the second radial stop element 942, 943 may be connected to the radial partition 923 at a first end.
- the second radial stop element 942, 943 may comprise a second end opposite the first end facing the radially outer face of the radially inner annular wall 952 or the radially outer end of the second leg 956 of one of the plurality of elastically deformable members.
- the second radial stop element 942, 943 may in particular extend over part or all of the longitudinal dimension of the radial partition 923.
- the second radial stop element can radially pass through at least one opening 957a, 957b, 957b’ provided in the hydrostatic annular seal.
- the second radial stop element 942 is capable of coming into radial abutment with the second tab 956.
- a first opening 957a is notably provided in the radially external annular wall 951, the first opening 957a being opposite the radially external end of the second tab 56.
- the second radial stop element 942 passes through the first opening 957a.
- the second radial stop element 943 is capable of radially abutting the radially inner annular wall 952, in particular the radially outer face of the radially inner annular wall 952.
- the second radial stop element 943 passes through a first opening 957a provided in the radially outer annular wall 951, and a second opening 957b, 957b’ provided in each blade of said at least one blade 954.
- the second radial stop element 943 may in particular be circumferentially positioned between the first tab 955 and the second tab 956, in particular substantially in the middle of the first tab 955 and the second tab 956.
- the second radial stop element 942, 943 may have a second stop surface 946 substantially parallel to a face against which the second stop surface is capable of coming into abutment.
- a third clearance between the second abutment surface and the face against which the second abutment surface is capable of coming into abutment may preferably be of the same order of magnitude as the first clearance.
- the assembly may include a plurality of second radial stop members 942, 943.
- each of the plurality of elastically deformable members may include one of the plurality of second radial stop members.
- At least one third longitudinal stop element 944 of the stop system 940 can advantageously extend longitudinally from the hydrostatic annular seal 950.
- Said at least one third longitudinal stop element 944 is capable of coming into longitudinal abutment with a radial portion 932 of the annular ferrule 931 facing longitudinally.
- Such a feature makes it possible to ensure contact between the ferrule and the hydrostatic annular seal in the event of relative longitudinal movement between the ferrule and the stator stage, and in particular in the event of breakage of the rotor shaft.
- said at least one third longitudinal stop element can advantageously contribute to braking the rotor in the event of overspeed.
- Said at least one third longitudinal stop element 944 may preferably have an annular shape.
- stop elements have been presented individually in a non-limiting manner in the preceding description, the assembly being able to comprise a combination of said at least one first radial stop element, said at least one second radial stop element and said at least one third longitudinal stop element.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202480021162.5A CN120981642A (zh) | 2023-03-23 | 2024-03-22 | 涡轮发动机的组件 |
| EP24722049.4A EP4684109A1 (fr) | 2023-03-23 | 2024-03-22 | Ensemble pour turbomachine |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR2302786A FR3146939A1 (fr) | 2023-03-23 | 2023-03-23 | Ensemble pour turbomachine |
| FR2302786 | 2023-03-23 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2024194585A1 true WO2024194585A1 (fr) | 2024-09-26 |
Family
ID=87889745
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/FR2024/050366 Ceased WO2024194585A1 (fr) | 2023-03-23 | 2024-03-22 | Ensemble pour turbomachine |
Country Status (4)
| Country | Link |
|---|---|
| EP (1) | EP4684109A1 (fr) |
| CN (1) | CN120981642A (fr) |
| FR (1) | FR3146939A1 (fr) |
| WO (1) | WO2024194585A1 (fr) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0421596B1 (fr) * | 1989-10-04 | 1994-05-25 | ROLLS-ROYCE plc | Support pour garniture d'étanchéité à labyrinthe |
| WO2009148787A1 (fr) | 2008-06-04 | 2009-12-10 | Justak John F | Joint d'étanchéité sans contact pour turbine à gaz |
| US20170226861A1 (en) * | 2014-10-15 | 2017-08-10 | Safran Aircraft Engines | Rotary assembly for a turbine engine comprising a self-supported rotor collar |
| US20200149543A1 (en) * | 2018-11-13 | 2020-05-14 | United Technologies Corporation | Seal disassembly aid |
| US20210040891A1 (en) * | 2019-08-08 | 2021-02-11 | United Technologies Corporation | Hydrostatic seal with extended carrier arm |
| FR3120649A1 (fr) * | 2021-03-12 | 2022-09-16 | Safran Aircraft Engines | Ensemble statorique de turbine |
-
2023
- 2023-03-23 FR FR2302786A patent/FR3146939A1/fr active Pending
-
2024
- 2024-03-22 EP EP24722049.4A patent/EP4684109A1/fr active Pending
- 2024-03-22 WO PCT/FR2024/050366 patent/WO2024194585A1/fr not_active Ceased
- 2024-03-22 CN CN202480021162.5A patent/CN120981642A/zh active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0421596B1 (fr) * | 1989-10-04 | 1994-05-25 | ROLLS-ROYCE plc | Support pour garniture d'étanchéité à labyrinthe |
| WO2009148787A1 (fr) | 2008-06-04 | 2009-12-10 | Justak John F | Joint d'étanchéité sans contact pour turbine à gaz |
| US20170226861A1 (en) * | 2014-10-15 | 2017-08-10 | Safran Aircraft Engines | Rotary assembly for a turbine engine comprising a self-supported rotor collar |
| US20200149543A1 (en) * | 2018-11-13 | 2020-05-14 | United Technologies Corporation | Seal disassembly aid |
| US20210040891A1 (en) * | 2019-08-08 | 2021-02-11 | United Technologies Corporation | Hydrostatic seal with extended carrier arm |
| FR3120649A1 (fr) * | 2021-03-12 | 2022-09-16 | Safran Aircraft Engines | Ensemble statorique de turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN120981642A (zh) | 2025-11-18 |
| FR3146939A1 (fr) | 2024-09-27 |
| EP4684109A1 (fr) | 2026-01-28 |
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