EP2558728B1 - Verfahren zur adpaptierung des luftstroms eines turbinenmotors mit zentrifugalverdichter und diffuser zu seiner umsetzung - Google Patents

Verfahren zur adpaptierung des luftstroms eines turbinenmotors mit zentrifugalverdichter und diffuser zu seiner umsetzung Download PDF

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Publication number
EP2558728B1
EP2558728B1 EP11730371.9A EP11730371A EP2558728B1 EP 2558728 B1 EP2558728 B1 EP 2558728B1 EP 11730371 A EP11730371 A EP 11730371A EP 2558728 B1 EP2558728 B1 EP 2558728B1
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European Patent Office
Prior art keywords
blades
blade
diffuser
rotation
variable pitch
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EP11730371.9A
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English (en)
French (fr)
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EP2558728B2 (de
EP2558728A1 (de
Inventor
Pierre Biscay
Patrick Marconi
Hubert Hippolyte Vignau
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Safran Helicopter Engines SAS
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Safran Helicopter Engines SAS
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the invention relates to a method of adapting the air flow rate of a turbomachine comprising a centrifugal compressor, in particular from helicopter turbine engine or auxiliary power unit (abbreviated as APU) to a variable demand for flow rate or mechanical or electrical power.
  • APU auxiliary power unit
  • the invention also relates to a diffuser equipped with variable pitch blades capable of implementing this method.
  • the field of the invention is the compression of gases in turbomachinery engines and, more particularly, the adaptation of the compressed air flow to respect the performance of the engines, be they turboshaft engines or APUs, in particular its consumption. specific (abbreviated Cs) partial load.
  • a general problem is to meet the pumping margin requirements and to compensate for compression rate reductions at the intermediate turbine engine speeds, as well as variations in the demand for compressed air flow and electrical power in the engine. case of APU.
  • IGV inlet guide vanes
  • variable setting is achieved by appropriate controls in connection with a control unit according to the physical parameters involved (rotation speed, pressures, temperatures).
  • the ranges of wedges that the control system must cover require a control cylinder of high power, cause significant variations in the inlet and outlet diameters of the diffuser, which can generate high mechanical stresses between rotating parts (wheel) and static (radial variable valve) and decreases the efficiency at partial load (intermediate regime).
  • the invention aims to overcome these disadvantages, in particular by maintaining the efficiency of the compressor to substantially reduce the Cs while ensuring a sufficient pumping margin with a better efficiency of the partial load engine cycle. To do this, it proposes an optimized method of variable diffusion of the air flow in a centrifugal compressor of turbomachines.
  • the subject of the invention is a method for diffusing variable air flows in a centrifugal compressor of turbomachine engines, consisting in providing a diffusion of air through a first annular grid of variable-pitch blades radially flanged. a second annular grid of same number of fixed-pitch blades of equivalent extension, directing the diffusion in the radial direction by coupling the blades of the two blades, each blade of the first blade being rotated away from the blade.
  • Turbomachines should be understood to mean turboshaft engines, in particular helicopter turboshaft engines with a single-stage or two-stage centrifugal compressor, and APUs equipped with a centrifugal compressor of single or two-stage power.
  • the radial extension of the variable pitch blades is substantially reduced by the presence of the fixed blade comprising true blades, which limits the efforts to vary their rigging and games between the moving blade and the support flange and thus upstream / downstream recirculation, which has the effect of reducing the deterioration of the pumping line and the pressure drops.
  • the decentralized implantation of the axis of rotation of the variable-pitch blades substantially reduces the variations in radial extension of these iso-diffusion blades: the increase in closing is less, thus favoring the efficiency, partial load and decreasing opening less also, which limits the mechanical stresses due to unsteady aerodynamic fluctuations by wheel / diffuser interaction.
  • a sufficient pumping margin then allows the turbomachine to operate without pumping - offering a large acceleration capacity -, and the APU to cope with significant load variations, without using a discharge valve, while maintaining the speed of rotation of the turbomachine and its pressure rate to levels close to their nominal values and providing a sufficient level of efficiency.
  • the method applying to turbomachines equipped with a power turbine, the variable-displacement radial diffusion on a centrifugal compressor, as defined above, is coupled to a variable-pitch power turbine distributor.
  • Power production can be carried out according to several configurations: free power turbine - or linked, of axial or centripetal type, with or without downstream heat exchange.
  • the coupling between the diffuser and the variable valve distributor makes it possible to adapt the operating line to the flow reduction, which improves the efficiency of the engine cycle (by a better pressure ratio) and therefore the Cs of the helicopter turboshaft engines. and APUs.
  • the subject of the invention is also a variable-speed turbine engine diffuser capable of implementing the method defined above, as well as the turbomachine equipped with such a diffuser.
  • the diffuser comprises a first annular grid of variable pitch blades radially bordered by a second annular grid of fixed pitch blades of equivalent extension, forming successive diffusion channels by coupling the blades of the two grids in radial extension.
  • each blade of the first gate is driven by control means capable of exerting a proper rotation of each blade off-center with respect to its axis of rotation.
  • upstream and downstream refer to the flow direction of the air flow in a turbine engine.
  • the centrifugal compressor 10 of a turbomachine such as a turbine engine, turbojet engine, turboprop engine or an APU, comprises a casing 12 coupled to a radial cover 14 of the wheel 16, the centrifugal last stage of the compressor, rotatably mounted on the motor shaft 18 along the axis Y'Y.
  • the air flow F flows from the impeller 16 to the annular diffuser 19, in a converging inlet vein by radial shrinkage.
  • the diffuser 19 is defined between two upstream and downstream flanges 20 and 22.
  • the cover 14 is held by a fastener 23 fixed to the casing and to the upstream flange 20.
  • the blades 24, forming a first annular grid, are mounted in the diffuser 19.
  • Centerings 25 and 26, formed opposite in the flanges 20 and 22, accommodate the cups 17 and 27 on which the blades 24 are mounted off-center.
  • the cups are centered in the flanges 20 and 22 with appropriate clearances, from 0.03 to 0.05 mm in the example illustrated, on a washer 9 inserted in the centering 25 (see below with reference to FIG. figure 5 ).
  • Blades 28 secured to the flange 22, forming a second annular grid bordering the outside of the first grid, are mounted on the annular flange 20 by through screws 29 housed in holes 29t. These screws also allow the passage of structural forces.
  • the control of the variable blades 24 is achieved by means of rods 30 integrally extending the upstream cup 17.
  • rods 30 of X'X axis are mounted in a cylindrical bore 32 of the upstream flange 20 and centered with a virtually zero clearance by joints 30j mounted in grooves 30g.
  • each rod 30 has a flat portion 31 articulated on a drive lever 33 clamped by two screws 35 on this flat portion 31.
  • the positions of the ends 31 of the rods 30 are adjusted with appropriate play tolerances.
  • the rod 30 also has a hole 30t in which a pin 36 is inserted which makes it possible to lock a washer 30u - for adjusting the axial position of the cups 17 and 27 - in a locking ring 12a formed in the casing 12.
  • the pin 36 secures the rod 30 and the locking ring 12a.
  • the lever 33 is driven by a control ring 34 forming a cylindrical hole 38 for housing the spherical ball 37 of the lever 33 with an adapted axial position tolerance and a contact on a generatrix of the ball joint.
  • the control ring 34 is centered on sectors having needle bearings 39.
  • the control ring 34 rotated about the motor axis Y'Y by a rod (not shown), rotates the levers 33 which slide in the cylindrical housing 38 thanks to their ball joint 37.
  • the depth of the housing 38 is a function of the stroke of the levers 33, itself a function of the rotation interval of the blades 24.
  • This architecture is particularly suitable for a rotation of the blades up to + 12 ° with a closing of 50% of section, and up to -5 ° with an opening of section of 20%.
  • a movable blade 24 is shown between the parallel cups 17, 27 and joined by welding 21 to them, so that the blade extends parallel to the axis X'X cups facing.
  • the leading edge 24c of the blade 24 is flush with the outer circumferences 17c and 27c of the cups, the thickness of the blade 24 being relatively thin, 2 mm in the illustrated example.
  • the distance between the blade 24 and the axis X'X of the rod 30 is equal to about 80% of the radius of the cups in the illustrated example. This confers on the blade 24 a strong off-centering with respect to the axis X'X of the rod which coincides with the axis of rotation of the assembly.
  • the rod 30 also has the cylindrical centering grooves 30g and the locking hole 30t of the adjusting washer of the axial position of the cups 17 and 27. Its flat portion 31 is traversed by holes 30a for receiving the mounting screws 35. to the control lever.
  • the overall view of the figure 3 illustrates the upstream annular flange 20 equipped with annular gates G1 and G2, mounted respectively mobile and fixed and composed of blades 24 and 28.
  • the blades 28 have a substantially thicker profile at the leading edge Ba than that of the blades 24, respectively 0.5 and 2.5 mm, in order to preserve good resistance to variations in incidence during the rotation of the movable blades 24.
  • the law of skeleton angle of the blades 28 between the leading edges BA and Leakage BF is scalable, making it possible to optimize the aerodynamic efficiency of the fixed gate by a maximum recovery of static pressure.
  • the blades 28 of the fixed gate have a maximum thickness of 7 mm in the example shown, for fixing the flange 20 of the diffuser by screws housed in the holes 29t, while allowing the passage of structural forces .
  • the air flow F circulates along a fixed blade 28 in radial extension of a movable blade 24 and between two adjacent blades of the same nature, mobile or fixed. Thanks to the off-centering of the mobile blades 24 with respect to the axes of rotation X'X of their cups 17, the variations of the radial extensions formed by these movable blades 24 are limited compared to variations of extensions that should be made of centered blades. This limitation makes it possible to improve the performance of a centrifugal compressor: it makes it possible to move the operating line away from the pumping line, by shifting towards lower flow rates, and to raise this operating line close to the yield maxima. higher diets.
  • the radial extensions of the mobile blades 24 with respect to the fixed blades 28 are illustrated by the diagrams of the Figures 4a to 4c , on which also appear, in dotted lines, the cups 17, 27 of the blades.
  • the nominal setting of 0 ° corresponds to a flow of the reference air flow F for which the adjustment of the movable blades 24 relative to the fixed blades 28 is adapted to stable intermediate speeds.
  • the pitch of the mobile blades 24 can rise up to + 12 °, this wedging corresponding to a passage section at the entrance of the collar Sa, between the blades 24 and 28, closed by 50% relative to at the nominal setting corresponding to a section at the neck Sb.
  • the figure 4a illustrates the case of a closure of 25% associated with a wedge of 6 °, the cross-section then being worth 75% of the section Sb.
  • the calibration setting can also go down to -5 °.
  • the figure 4c illustrates the case of an opening of 2.5 °, the section at the neck Sc then having a relative value of 110%.
  • the fixed blades 28 are wedged in azimuth with respect to the blades 24 of the first movable gate G1 so as to resume the wake on the extrados Ex of the blades of this first gate G1.
  • the values of the clearances remain less than or equal to 0.02 mm (for J1 or J2), 0.10 mm (for J3) and 0.25 mm (for J4).
  • the clearance (set J1 and J2) of the blade 24 on the washer 9 remains about 0.03 mm or slightly higher.
  • the invention is not limited to the examples described and shown. It is for example possible to set the pitch of the mobile blades by only mechanical adjustment, individual or centralized, or by electrical, electronic control with or without digital control.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Verfahren zur Adaptierung eines Luftstroms in einem Zentrifugalverdichter (10) eines Turbinenmotors, das darin besteht, eine Diffusion der Luft durch eine erste ringförmige Beschaufelung (G1) von Schaufeln mit variabler Feststellposition (24), die radial durch eine zweite ringförmige Beschaufelung (G2) mit derselben Anzahl von Schaufeln mit feststehender Feststellposition (28) mit äquivalenter Ausdehnung umrandet ist, die die Diffusion in radialer Ausdehnung durch Koppeln der Schaufeln (24, 28) der beiden Beschaufelungen ausrichtet, wobei dieses Verfahren dadurch gekennzeichnet ist, dass jede Schaufel (24) der ersten Beschaufelung (G1) in Achsdrehung (X'X) auf Abstand zu der Schaufel (24) versetzt wird.
  2. Verfahren zur Adaptierung nach Anspruch 1, wobei die radiale Diffusion mit variabler Feststellposition auf dem Zentrifugalverdichter an eine Leistungsverteilung mit variabler Feststellposition gekoppelt ist, wobei die Leistungsverteilung frei mit stromabwärtigem Austausch oder axial oder zentripetal verbunden ist, mit oder ohne stromabwärtigem Austausch.
  3. Turbinenmotordiffuser mit variabler Feststellposition, der imstande ist, das Verfahren nach Anspruch 1 oder 2 umzusetzen, ein erstes ringförmiges Gitter (G1) von Schaufeln mit variabler Feststellposition (24), die radial durch ein zweites ringförmiges Gitter (G2) mit Schaufeln mit feststehender Feststellposition (28) mit äquivalenter Ausdehnung und derselben Anzahl an Schaufeln umrandet ist, die durch Koppeln der Schaufeln (24, 28) der beiden Gitter (G1, G2) in radialer Ausdehnung aufeinanderfolgende Diffusionskanäle bilden, dadurch gekennzeichnet, dass jede Schaufel (24) des ersten Gitters (G1) durch Antriebsmittel (30, 33, 34) angetrieben wird, die imstande sind, eine im Verhältnis zu ihrer Drehachse (X'X) exzentrische Schaufeleigendrehung (24) auszuüben.
  4. Diffuser nach dem vorstehenden Anspruch, wobei sich jede Schaufel mit variabler Feststellposition (24) zwischen zwei Manschetten (17, 27) gegenüber und parallel und exzentrisch im Verhältnis zur gemeinsamen Achse der Manschetten, die mit der Drehachse (X'X) zusammenfällt, erstreckt.
  5. Diffuser nach einem der Ansprüche 3 oder 4, wobei jede Schaufel (24) an eine Antriebsstange (30) gekoppelt ist, die mindestens eine Öffnung (30t) aufweist, in welche ein Blockierstift (36) einer Scheibe (30u) zum Einstellen der axialen Position der Manschetten (17, 27) eingeführt wird.
  6. Diffuser nach dem vorstehenden Anspruch, wobei die Stange (30) fest mit einem Hebel (33) verbunden ist, der ein kugelförmiges Gelenk (37) aufweist, das in einer zylindrischen Aufnahme (38) eines Steuerkranzes (34) aufgenommen ist, der imstande ist, den Hebel (33) um die Motorachse (X'X) in Drehung zu versetzen, der imstande ist, in der zylindrischen Aufnahme 38 zu gleiten.
  7. Diffuser nach dem vorstehenden Anspruch, wobei die Tiefe der zylindrischen Aufnahmen (38) von dem Weg der Hebel (33) abhängig ist, der selbst von dem vorbestimmten Drehintervall der Schaufeln (24) abhängig ist.
  8. Diffuser nach einem der Ansprüche 4 bis 7, wobei sich die Angriffskante (24c) einer jeden Schaufel mit variabler Feststellposition (24) in der Nähe der Peripherien (17c, 27c) der Manschetten (17, 27) befindet, wobei der Abstand der Schaufel (24) zu der Drehachse (X'X) größer oder gleich einem halben Radius ist.
  9. Diffuser nach einem der Ansprüche 3 bis 8, wobei die feststehenden Schaufeln (28) des zweiten Gitters (G2) ein Angriffskantenprofil (Ba) aufweisen, das stärker als jenes (24c) der Schaufeln (24) des ersten Gitters (G1) ist.
  10. Diffuser nach einem der Ansprüche 3 bis 9, wobei die Feststellwinkel der beweglichen Schaufeln (24) zwischen +12 und -5° enthalten sind, einem Halsabschnitt (Sa, Sc) jeweils von 50 % und von 120 % im Verhältnis zu dem entsprechenden Abschnitt mit Nennfeststellposition entsprechend.
EP11730371.9A 2010-04-14 2011-04-13 Verfahren zur adpaptierung des luftstroms eines turbinenmotors mit zentrifugalverdichter und diffuser zu seiner umsetzung Active EP2558728B2 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL11730371.9T PL2558728T5 (pl) 2010-04-14 2011-04-13 Sposób dostosowywania natężenia przepływu powietrza w maszynie wirowej zawierającej sprężarkę odśrodkową i dyfuzor do realizacji tego sposobu

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1052827A FR2958967B1 (fr) 2010-04-14 2010-04-14 Procede d'adaptation de debit d'air de turbomachine a compresseur centrifuge et diffuseur de mise en oeuvre
PCT/FR2011/050846 WO2011128587A1 (fr) 2010-04-14 2011-04-13 Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre

Publications (3)

Publication Number Publication Date
EP2558728A1 EP2558728A1 (de) 2013-02-20
EP2558728B1 true EP2558728B1 (de) 2019-07-24
EP2558728B2 EP2558728B2 (de) 2022-10-12

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EP11730371.9A Active EP2558728B2 (de) 2010-04-14 2011-04-13 Verfahren zur adpaptierung des luftstroms eines turbinenmotors mit zentrifugalverdichter und diffuser zu seiner umsetzung

Country Status (10)

Country Link
US (1) US20130034425A1 (de)
EP (1) EP2558728B2 (de)
JP (2) JP2013524099A (de)
KR (1) KR20130079326A (de)
CN (1) CN102834622B (de)
CA (1) CA2794825C (de)
FR (1) FR2958967B1 (de)
PL (1) PL2558728T5 (de)
RU (1) RU2564158C2 (de)
WO (1) WO2011128587A1 (de)

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Publication number Publication date
EP2558728B2 (de) 2022-10-12
JP2017061936A (ja) 2017-03-30
CA2794825A1 (fr) 2011-10-20
RU2012148378A (ru) 2014-05-20
FR2958967A1 (fr) 2011-10-21
US20130034425A1 (en) 2013-02-07
JP2013524099A (ja) 2013-06-17
CN102834622B (zh) 2016-02-10
CN102834622A (zh) 2012-12-19
EP2558728A1 (de) 2013-02-20
FR2958967B1 (fr) 2013-03-15
JP6483074B2 (ja) 2019-03-13
RU2564158C2 (ru) 2015-09-27
KR20130079326A (ko) 2013-07-10
CA2794825C (fr) 2018-06-12
WO2011128587A1 (fr) 2011-10-20
PL2558728T3 (pl) 2019-10-31
PL2558728T5 (pl) 2023-02-06

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