EP3301262B1 - Aube - Google Patents

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Publication number
EP3301262B1
EP3301262B1 EP17187258.3A EP17187258A EP3301262B1 EP 3301262 B1 EP3301262 B1 EP 3301262B1 EP 17187258 A EP17187258 A EP 17187258A EP 3301262 B1 EP3301262 B1 EP 3301262B1
Authority
EP
European Patent Office
Prior art keywords
blade
trailing edge
gutter
channel
squealer
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.)
Active
Application number
EP17187258.3A
Other languages
German (de)
English (en)
Other versions
EP3301262A1 (fr
Inventor
Martin Mottram
David Hunt
Haidong LI
Shahrokh Shahpar
Stefano Caloni
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from GBGB1615573.1A external-priority patent/GB201615573D0/en
Priority claimed from GBGB1615571.5A external-priority patent/GB201615571D0/en
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP3301262A1 publication Critical patent/EP3301262A1/fr
Application granted granted Critical
Publication of EP3301262B1 publication Critical patent/EP3301262B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present disclosure relates to shroudless turbine blades having squealer tips. More particularly the invention relates to the arrangement of internal cooling channels in this region of the blade and the geometry of squealer tips which accommodate the cooling channels.
  • a compressor In a gas turbine engine, a compressor is arranged to compress air for delivery to a combustor.
  • the combustor mixes the compressed air with fuel and ignites the mixture. Gas products of this combustion are directed at a turbine blade assembly causing rotation of the blades and the production of power from the turbine assembly.
  • Combustion temperatures may exceed 1400°C and typical configurations expose the turbine blade assemblies to these high temperatures.
  • Turbine blades are made of materials capable of withstanding such high temperatures and often contain cooling systems for prolonging the life of the blades, reducing the likelihood of failure as a result of exposure to these excessive temperatures.
  • a turbine blade has a root portion at one end and an elongated portion of aerofoil shaped cross section extending from the root portion.
  • the root portion is coupled to a platform, typically a radially outer surface of a circumferential wall of a rotor disc.
  • the elongated portion extends radially outwardly and terminates in a tip.
  • the aerofoil shaped cross section has a leading edge and a trailing edge joined by a suction side and a pressure side.
  • a squealer tip is formed as a wall extending around a substantial portion of the aerofoil at the blade tip defining a gutter within. Cooling air which has passed through the elongate portion of the blade may be expelled into this gutter and dispersed into the main gas stream.
  • a main trailing edge cooling channel is provided in the elongated portion of the blade and extends from root to tip of the blade.
  • Multiple smaller diameter cooling channels (typically including effusion cooling channels) extend from the main trailing edge channel through the squealer wall in the region of the trailing edge and through the elongate portion to the thinnest parts of the trailing edge.
  • a gallery channel is provided just beneath the gutter surface of the squealer and extends from the main trailing edge cooling channel towards an apogee of the trailing edge.
  • Effusion cooling channels extend through the squealer wall to the gallery channel.
  • the main trailing edge cooling channel is typically integrally cast into the blade.
  • the gallery channel and effusion cooling channels may be added in a subsequent machining step.
  • the gallery channel is typically machined from the apogee of the trailing edge and its end at the apogee subsequently plugged or welded closed to encourage maximum flow to the effusion cooling channels.
  • FIG. 1 An example of a prior art arrangement is shown in Figure 1 .
  • the figure shows the tip of a blade from a plan view, pressure side view and trailing edge end view.
  • the tip has an aerofoil shaped cross section with a leading edge 1, a trailing edge 2, a suction side 3 and a pressure side 4.
  • a squealer comprises a squealer wall 5 which extends from the trailing edge 2 along the suction side 3, around leading edge 1 and along the pressure side 4 returning to the trailing edge 2.
  • the wall defines a gutter 6.
  • Main cooling channels extend along the elongated portion of the blade and exit into the gutter 6.
  • the main cooling channels include a main trailing edge cooling channel 7.
  • a gallery channel 8 is drilled into the trailing edge 2 from the apogee 9 of the trailing edge 2.
  • a first plurality of effusion cooling channels 10 extend from the gallery channel 8 and through the squealer wall 5. As can be seen, in the region of the tip, the apogee 9 of the trailing edge 2 is flared 12 and enlarged to accommodate the drilling of the gallery channel 8.
  • a second plurality of effusion cooling channels 11 extends from the main trailing edge cooling channel into the thinnest region of the trailing edge exiting on the pressure side 4 adjacent the apogee 9 of the trailing edge 2.
  • the large overhang 12 of the squealer results in a larger wetted area and hence increased heat flux into the tip during engine operation. This increases the cooling requirement for this region.
  • Other disadvantages of the arrangement include sub-optimal aerodynamic performance at the trailing edge resulting in efficiency losses and a weight penalty.
  • the preamble of claim 1 is disclosed in US 8 435 004 B1 or in EP 3 064 713 A1 .
  • the present disclosure seeks to provide an improved cooling arrangement and associated squealer tip design which contributes to the mitigation of the problems identified above.
  • a blade comprising a root portion and an elongate portion extending from the root portion to a tip, the elongate portion having an aerofoil-shaped cross section having a leading edge, a trailing edge, a suction side and pressure side, the tip including a squealer defining a gutter at the tip wherein the squealer comprises a wall extending from the trailing edge along the entirety of a first of the suction side and pressure side, around the leading edge and partly along a second of the suction side and pressure side leaving a gap between the trailing edge and an end of the wall on the second side, a main trailing edge cooling channel extending within the elongate portion in a direction from root to tip adjacent the trailing edge and exiting into the gutter, wherein the main trailing edge cooling channel includes a bend just upstream of the exit such that the exit is displaced from a camber line of the blade elongated portion towards the gap
  • the first side is the pressure side. In other embodiments the first side is the suction side.
  • the end of the squealer wall on the second side may be curved.
  • the gutter in the region of the trailing edge is inclined from the first side towards the second side whereby to maintain a surface which is substantially orthogonal to the walls of the main trailing edge cooling channel where they meet the gutter surface.
  • the depth of the squealer wall may vary from a first depth at the leading edge to a second and greater depth at the trailing edge.
  • the width of the squealer wall may reduce from a maximum width at a first end of the squealer wall to a minimum width at a second end of the squealer wall.
  • the squealer wall may be locally thinned or thickened to accommodate internal passages within the wall or to satisfy manufacturing requirements.
  • the squealer wall may include a locally extended portion adjacent the trailing edge on the first side, the extended portion extending in a widthwise direction with respect to the squealer wall and away from the gutter.
  • the extended portion may accommodate a gallery channel and associated effusion cooling channels for cooling the trailing edge at the tip.
  • the gutter may be shallower adjacent the leading edge than it is at the trailing edge. Variation in gutter depth may be achieved by providing an inclined surface to the tip within the gutter. Alternatively, variation in gutter depth is achieved by varying the height of the wall of the squealer between the trailing edge and the leading edge. Gutter depth may vary gradually along an incline, alternatively or in addition, gutter depth may vary due to one or more steps within the gutter.
  • the gallery channel may be shaped to follow variations in the depth of the gutter. For example, the gallery channel may include a stepped section to accommodate a step in the gutter.
  • a gallery channel may be integrally cast into the blade using an adapted core which defines both the main trailing edge cooling channel and has an extension defining the gallery channel.
  • the gallery channel may be provided in a shape which minimises flow restriction in the gallery channel.
  • the gallery channel is conically tapered from its open end to its closed end.
  • the cross sectional shape of the gallery channel may be varied in a manner designed to tune coolant flow to suit cooling requirements in different regions of the blade tip and squealer.
  • the gallery channel is shaped to encourage optimum flow rates to the film cooling holes in accordance with cooling requirements at the exits of the film cooling holes.
  • the gallery may be configured to bias cooling towards one of the suction side and pressure side.
  • the film cooling channels may comprise effusion cooling channels. Axes of the effusion cooling channels may be inclined to a surface of the squealer wall.
  • the effusion cooling channels may have a varying cross section, for example the effusion cooling channels may include a fanned portion adjacent the exit to a squealer wall surface.
  • Film cooling channels may be introduced after a blade has been cast. For example, the film cooling channels may be drilled using an EDM process.
  • the blade may be configured for use in a gas turbine engine, for example the blade may be configured for use in a compressor section or turbine section of a gas turbine engine.
  • One useful application of the design of the invention is in blades of a high pressure turbine stage in a gas turbine engine.
  • FIG. 2 shows a core suited to defining a main trailing edge cooling channel in an embodiment of a blade in accordance with the invention.
  • the core 20 has a main trailing edge cooling channel section 21 which is elongate and proportioned to extend in a root to tip direction within a mould which defines the elongate portion of a blade to be cast in the mould.
  • the main trailing edge cooling channel section 21 Towards the tip end, the main trailing edge cooling channel section 21 has an inclined portion 22 as compared to the remainder of the main trailing edge cooling channel section 21.
  • the main trailing edge cooling channel section 21 sits substantially in alignment with a camber line of the blade mould.
  • the inclined portion 22 results in an exit of the main trailing edge cooling channel section 21 being positioned to one side of the camber line.
  • the core further includes a gallery channel portion 23.
  • the gallery channel portion 23 extends in a leading edge to trailing edge direction within the blade mould.
  • the gallery channel portion 23 has a substantially flat upper wall 24 which defines a wall of the gallery channel in a blade which is substantially in parallel with a surface of a gutter in the tip of the blade.
  • a lower surface 25 of the gallery channel 23 is curved to form a spout shaped gallery channel portion 23.
  • Figure 3 shows a wireframe view of the core of Figure 2 arranged behind a pressure surface side 36 of a blade 30 in accordance with the invention.
  • the main trailing edge cooling channel core 31, 32 has an elongate section 31 and inclined section 32.
  • the elongate section 31 extends in a root to tip direction through the blade 30 passing through a camber line of the blade.
  • the inclined section 32 tilts the channel away from the camber line and towards a suction surface side (not shown) of the blade 30.
  • a spout shaped gallery channel portion 33 extends from the elongate section 31 towards an apogee 39 of the trailing edge of the blade 30.
  • a closed end of the gallery channel portion 33a sits behind the apogee 39.
  • a top surface 33b of the gallery channel portion 33 is planar and extends in parallel with a surface of a gutter 38 which is bordered by a squealer wall 37.
  • the gallery channel portion 33 extends beneath the surface of the gutter 38.
  • the inclined portion 32 exits into the gutter 38 towards the suction surface side of the camber line.
  • FIG. 4 shows a wireframe view of an alternative core arranged behind a pressure surface side 46 of a blade 40 in accordance with the invention.
  • the main trailing edge cooling channel core 41, 42 has an elongate section 41 and inclined section 42.
  • the elongate section 41 extends in a root to tip direction through the blade 40 passing through a camber line of the blade.
  • the inclined section 42 tilts the channel away from the camber line and towards a suction surface side (not shown) of the blade 40 and exits through gutter 48 at a position to the suction surface side of the camber line.
  • a gallery channel may be added after casting by drilling from the apogee 49 side through to the elongate section 41. In such a case the end of the gallery channel at the apogee 49 may be plugged or welded to close the gallery channel.
  • Figure 5 shows the tip end of a blade having an aerofoil-shaped cross section.
  • the blade has a suction side 51 and a pressure side 52 which meet to form a leading edge 53 and a trailing edge 54.
  • the elongate portion of the blade terminating in the tip extends from a root portion 55.
  • Around a perimeter of the tip is provide a squealer wall 56 which extends from a first end 56a at the trailing edge 54 to a second end 56b midway along the suction side 51 leaving a gap along the remainder of the suction side 51 to the trailing edge 54.
  • the wall 56 defines a gutter 57 in the tip.
  • a plurality of cooling channels 58a, 58b, 58c, 58d, 58e exit the elongate portion of the blade in the gutter 57. Exits to cooling channels 58b, 58c, 58d and 58e sit along a camber line C-C of the blade.
  • Cooling channel 58a is the main trailing edge cooling channel which includes the inclined portion as discussed in accordance with the invention. As can be seen, this channel 58a has an exit which is positioned towards the suction side 51 of the camber line C-C.
  • the cooling channels 58a, 58b, 58c, 58d and 58e may be blocked at the blade tip by weld caps, each weld cap having a small diameter hole through it (typically 0.5mm) to allow egress of dust from the internal passages.
  • Film cooling channels may be provided through the suction side and/or pressure side walls to connect with the channels. Capping at the tip encourages greater flow to these film cooling channels.
  • the gutter 57 includes a step 59 which results in the gutter 57 being deeper towards the trailing edge 54 end of the gutter than the leading edge 53 end of the gutter 57 and also provides an incline from the suction side towards the pressure side. This incline is selected to ensure that the surface of the gutter 57 around the exit of channel 58a is approximately orthogonal to walls of the channel 58a at the exit.
  • the second end 56b of the squealer wall 56 is gently curved to discourage turbulent flow of cooling air which exits into the gutter 57 from the channels 58a-58e and flows towards the trailing edge 54 to join a main flow of hot air delivered from the combustor to generate work from a turbine assembly of which the blade forms a part.
  • FIG. 6 shows the tip end of a blade in accordance with invention.
  • the blade has a suction side 61, a pressure side 62, a leading edge 63 and a trailing edge 64.
  • a squealer wall 66 extends from a first end 66a along the pressure side 62, around the leading edge 63 and part way along the suctions side 61 to a second end 66b.
  • the second end 66b is smoothly curved.
  • the wall 66 defines a gutter 67 which has a first depth d 1 at the trailing edge 64 and a second depth d 2 at the leading edge 63.
  • the first depth d 1 is greater than the second depth d 2 .
  • the wall has a first width w 1 adjacent the trailing edge 64 on the pressure side 62 and a second width w 2 adjacent second end 66b on the suction side 61.
  • the first width w 1 is greater than the second width w 2 and smoothly varies from suction side to the pressure side In other embodiments, the variation may be reversed with width w 2 being greater than width w 1 , the wall 66 being generally thinner along the pressure side.
  • the first width w 1 is increased by the inclusion of an extension 68 adjacent the first end 66a which extends from the trailing edge 64 a short distance along the pressure side 62.
  • the squealer wall 76 extends from a first end 76a at the trailing edge 74 entirely along the suction side 71, around the leading edge 73 and terminates at a second end 76b part way along the pressure side 72.
  • the wall defines a gutter 77 which may include a gradual incline (not shown) from the leading edge 73 to the trailing edge 74.
  • the wall has an extension 78 on the suction side 71 adjacent the trailing edge which serves to increase the wall width w 1 at this location such that it is wider than a wall width w 2 near the second end 76b on the pressure side 72.
  • a gas turbine engine is generally indicated at 600, having a principal and rotational axis 611.
  • the engine 600 comprises, in axial flow series, an air intake 612, a propulsive fan 613, a high-pressure compressor 614, combustion equipment 615, a high-pressure turbine 616, a low-pressure turbine 617 and an exhaust nozzle 618.
  • a nacelle 620 generally surrounds the engine 600 and defines the intake 612.
  • the gas turbine engine 600 works in the conventional manner so that air entering the intake 612 is accelerated by the fan 613 to produce two air flows: a first air flow into the high-pressure compressor 614 and a second air flow which passes through a bypass duct 621 to provide propulsive thrust.
  • the high-pressure compressor 614 compresses the air flow directed into it before delivering that air to the combustion equipment 615.
  • the air flow is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive the high and low-pressure turbines 616, 617 before being exhausted through the nozzle 618 to provide additional propulsive thrust.
  • the high 616 and low 617 pressure turbines drive respectively the high pressure compressor 614 and the fan 613, each by suitable interconnecting shaft.
  • blades of the high and low pressure turbines 616, 617 may be configured in accordance with blades of the invention described herein.
  • gas turbine engines to which the present disclosure may be applied may have alternative configurations.
  • such engines may have an alternative number of interconnecting shafts (e.g. three) and/or an alternative number of compressors and/or turbines.
  • the engine may comprise a gearbox provided in the drive train from a turbine to a compressor and/or fan.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (16)

  1. Aube comprenant une partie pied et une partie allongée s'étendant depuis la partie pied jusqu'à une pointe, la partie allongée présentant une section transversale à profil aérodynamique qui comporte un bord d'attaque (53), un bord de fuite (54), un côté aspiration (51) et un côté refoulement (52), la pointe comprenant un bout aminci définissant une goulotte (57) au niveau de la pointe, ledit bout aminci comprenant une paroi (56) s'étendant depuis le bord de fuite (54) le long de l'intégralité d'un premier côté parmi le côté aspiration (51) et le côté refoulement (52), autour du bord d'attaque (53) et en partie le long d'un second côté parmi le côté aspiration (51) et le côté refoulement (52) en laissant un espace entre le bord de fuite (54) et une extrémité de la paroi (56b) sur le second côté, un canal de refroidissement de bord de fuite principal (58a) s'étendant au sein de la partie allongée suivant une direction allant du pied à la pointe adjacente au bord de fuite (54) et sortant dans la goulotte (57), caractérisée en ce que le canal de refroidissement de bord de fuite principal (58a) comprend une courbure juste en amont de la sortie de sorte que la sortie soit déplacée de la ligne de cambrure (C-C) de la partie allongée de l'aube en direction du second côté.
  2. Aube selon la revendication 1, ledit premier côté étant le côté refoulement (52) et ledit canal de refroidissement de bord de fuite principal (58a) étant courbé en direction du côté aspiration (51).
  3. Aube selon la revendication 1, ledit premier côté étant le côté aspiration (51) et ledit canal de refroidissement de bord de fuite principal (58a) étant courbé en direction du côté refoulement (52).
  4. Aube selon l'une quelconque des revendications précédentes, ladite goulotte (57) étant moins profonde adjacente au bord d'attaque (53) qu'elle ne l'est au niveau du bord de fuite (54).
  5. Aube selon l'une quelconque des revendications précédentes, ladite goulotte (57) dans la région du bord de fuite (54) étant inclinée depuis le premier côté (51, 52) en direction du second côté (51, 52) et conservant une surface qui est sensiblement orthogonale aux parois du canal de refroidissement de bord de fuite principal (58a) où elles rencontrent la goulotte (57).
  6. Aube selon l'une quelconque des revendications précédentes comprenant en outre un canal galerie moulé d'une seule pièce dans l'aube (30) en utilisant une âme adaptée qui à la fois définit le canal de refroidissement de bord de fuite principal (31, 32) et comporte une extension qui définit le canal galerie (33).
  7. Aube selon la revendication 6, ledit canal galerie étant fourni sous une forme qui minimise la restriction d'écoulement dans le canal galerie.
  8. Aube selon la revendication 6, ledit canal galerie étant en forme de bec verseur en présentant un diamètre plus grand au niveau de l'extrémité ouverte où il croise le canal de refroidissement de bord de fuite principal et un diamètre plus petit au niveau de l'extrémité fermée (33a) qui se trouve juste derrière le sommet (39) du bord de fuite.
  9. Aube selon l'une quelconque des revendications 6 à 8, une surface (24), faisant face à la pointe, du canal galerie étant profilée pour compléter et s'étendre parallèlement à la surface de la goulotte (38) dans la région de bord de fuite.
  10. Aube selon l'une quelconque des revendications 6 à 9, ledit canal galerie étant façonné pour suivre les variations de la profondeur de la goulotte.
  11. Aube selon l'une quelconque des revendications 6 à 10 comprenant en outre un réseau de canaux de refroidissement de film s'étendant depuis le canal galerie (33) et à travers la paroi (37) du bout aminci.
  12. Aube selon l'une quelconque des revendications précédentes, ladite profondeur de la paroi du bout aminci variant d'une première profondeur au niveau du bord d'attaque à une seconde et plus grande profondeur au niveau du bord de fuite.
  13. Aube selon l'une quelconque des revendications précédentes, la largeur de la paroi du bout aminci étant variable.
  14. Aube selon la revendication 13, ladite largeur de la paroi (56) du bout aminci décroissant d'une largeur maximal au niveau d'une première extrémité (56a) de la paroi du bout aminci à une largeur minimale au niveau d'une seconde extrémité (56b) de la paroi du bout aminci.
  15. Aube selon l'une quelconque des revendications précédentes, ladite paroi du bout aminci comprenant une partie localement allongée adjacente au bord de fuite sur le premier côté, la partie allongée s'étendant dans le sens de la largeur par rapport à la paroi du bout aminci et en s'éloignant de la goulotte.
  16. Aube selon l'une quelconque des revendications précédentes conçue pour être utilisée dans un moteur à turbine à gaz.
EP17187258.3A 2016-09-14 2017-08-22 Aube Active EP3301262B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB1615573.1A GB201615573D0 (en) 2016-09-14 2016-09-14 Turbine blade with squealer tip
GBGB1615571.5A GB201615571D0 (en) 2016-09-14 2016-09-14 Turbine blade cooling

Publications (2)

Publication Number Publication Date
EP3301262A1 EP3301262A1 (fr) 2018-04-04
EP3301262B1 true EP3301262B1 (fr) 2019-08-14

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EP17187258.3A Active EP3301262B1 (fr) 2016-09-14 2017-08-22 Aube

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US (1) US20180073370A1 (fr)
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