WO2005054632A1 - Sliding joint between combustor wall and nozzle platform - Google Patents

Sliding joint between combustor wall and nozzle platform Download PDF

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Publication number
WO2005054632A1
WO2005054632A1 PCT/CA2004/001016 CA2004001016W WO2005054632A1 WO 2005054632 A1 WO2005054632 A1 WO 2005054632A1 CA 2004001016 W CA2004001016 W CA 2004001016W WO 2005054632 A1 WO2005054632 A1 WO 2005054632A1
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WO
WIPO (PCT)
Prior art keywords
combustor
assembly
platform
vane
flange portion
Prior art date
Application number
PCT/CA2004/001016
Other languages
French (fr)
Inventor
Lorin Markarian
Dany Blais
Original Assignee
Pratt & Whitney Canada Corp.
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
Application filed by Pratt & Whitney Canada Corp. filed Critical Pratt & Whitney Canada Corp.
Priority to EP04761568A priority Critical patent/EP1706594B1/en
Priority to CA2549162A priority patent/CA2549162C/en
Priority to JP2006541763A priority patent/JP2007513281A/en
Publication of WO2005054632A1 publication Critical patent/WO2005054632A1/en

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates generally to gas turbine engines, and more particularly to a joint between a high pressure turbine vane platform and a combustor flange therein .
  • an assembly for a gas turbine engine comprising a combustor and a vane assembly downstream from the combustor, the vane assembly " including at least one airfoil radially extending between an inner and outer platform defining an annular gas path therebetween, wherein at least the outer platform forms a first sliding joint connection with an adjacent outer combustor wall such that radial sealing between the outer platform and the outer combustor wall is provided at engine operating temperature while permitting relative axial displacement therebetween.
  • an assembly for a gas turbine engine comprising: a combustor having a combustor. wall circumscribing a gas path therewithin and an exit duct end, the exit duct end having an outer flange portion radially spaced from the combustor wall in a direction away from the gas path to form an annular slot; a vane assembly disposed downstream of the combustor, the vane assembly including at least one airfoil extending between an inner and an outer platform; and a portion of at least the outer platform extending in the annular slot defined between the combustor wall and the outer flange portion, the portion being retained by the combustor wall and the outer flange portion such that the vane assembly is mounted to the combustor and sealed therewith.
  • a method of sealing a joint in an assembly for a gas turbine engine comprising a combustor and a vane assembly
  • the method comprising: providing a vane assembly mounted to an exit duct of the combustor, the vane assembly having at least one airfoil extending between an inner and an outer platform, at least the outer platform engaging a flange portion of the combustor exit duct; determining an amount of thermal growth differential exhibited between the flange portion and the at least the outer platform over an engine operating temperature range; and forming a joint between the flange portion and the at least the outer platform such that a spacing distance therebetween at ambient temperature is less than the determined amount of thermal growth differential over the engine operating temperature range, such that the spacing distance closes over the engine operating temperature range to provide a seal between the vane assembly and the combustor.
  • a combustor for a gas turbine engine comprising a combustor body having at least an annular exit end adapted to communicate with a vane assembly, the exit end defined by an inner exit lip and an outer exit lip, the inner and outer exit lips each having a pair of spaced-apart members, each pair of said members adapted to slidingly engage therebetween one of a pair of spaced-apart platforms of the vane assembly, one of said members being an innermost member relative to the combustor and one of said members being an outermost member relative to the combustor, wherein the spaced-apart members .are adapted such that said sliding engagement secures the vane assembly to the combustor independent of other retention means when the combustor is assembled with said vane assembly, and wherein at least one of the outermost and innermost members is flexible to thereby permit, in use, said spaced-apart vane platforms to expand apart from one another .
  • a combustor-to-vane joint assembly for a gas turbine engine, the combustor including an annular exit end for mating with an annular vane ring assembly, the vane ring assembly defined by inner and outer platform rings, the joint comprising: inner and outer female retaining members integral with and defining a downstream end of the annular exit, the female retaining members each including spaced-apart annular portions; and inner and outer male insertion members integral with and defining an upstream end of the vane assembly platform rings; wherein the vane assembly is mounted to the combustor solely by insertion of the inner and outer male insertion members between the spaced-apart . portions of the respective inner and outer female retaining members .
  • an assembly for a gas turbine engine comprising a combustor having a wall and an exit end, and an exit vane assembly mounted to the exit end on an inner side and an outer side relative to the combustor, the vane assembly including at least an inner platform and an outer platform, wherein the combustor exit end includes a finger element mounted to the combustor and spaced apart from the combustor wall,- and wherein the vane assembly outer platform is held between the finger element and combustor wall to thereby mount the vane assembly to the combustor.
  • Fig. 1 is a schematic cross-section of a gas turbine engine having a combustor joint in accordance with the present invention
  • Fig. 2 is a cross-section of a combustor and high pressure turbine of the prior art
  • FIG. 3 is a cross-section of a joint between a combustor flange and a high pressure turbine in accordance with the present invention.
  • FIG. 1 schematically illustrates a gas turbine engine 10 (a turbofan preferably adapted for use on an aircraft in subsonic flight in this case, though the invention may be practised in almost any gas turbine engine) generally comprising, in serial flow communication, a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed ⁇ air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
  • the turbine section 18 further comprises at least a first, or high pressure (HP) , turbine stage 17 which is immediately downstream from the combustor 16.
  • HP high pressure
  • the high pressure turbine stage 17 includes a turbine rotor 20 with a plurality of radially extending turbine blades 21, and a high pressure turbine (HPT) vane assembly 22 immediately upstream therefrom.
  • HPT high pressure turbine
  • a reverse flow combustor 916 provides hot combustion gases to a downstream HPT stage 917 of the gas turbine engine's turbine ' section 918.
  • the HPT stage 917 comprises generally an HPT vane assembly 922 and an HPT rotor assembly 920.
  • the HPT vane assembly 922 includes an airfoil 924 extending between an inner platform 926 and an outer platform 928, which define an annular passage 923 therebetween for directing the hot gases. therethrough.
  • the radially inner platform 926 of the PHT vane assembly 922 is engaged to a first, or radially inner, wall 930 of the combustor 916 by an inner joint 934.
  • the radially outer platform 928 is engaged to a second, or radially outer, wall 932 of the combustor.
  • the inner joint 934 is a sliding-type joint, wherein axial movement of the inner platform 926 relative to the combustor inner wall 930 is possible.
  • the outer joint 936 is much more complex, typically employing fastening members such as rivets or bolts to fasten the inner platform 928 of the HPT vane assembly 922 to the outer wall 932 of the combustor. Such an outer joint 936 therefore securely fixes the . outer platform 928 in place on the combustor outer wall 932 such that an adequate seal therebetween is ensured. A tight seal therebetween is required to prevent high pressure air, typically fed to the regions 940 around the combustor 916, from leaking into the lower pressure gas path flowing through the turbine section 918.
  • the HPT vane assembly 22 is located immediately downstream from the combustor 16, and is accordingly engaged thereto at the combustor exit.
  • the vane inner platform 26 of the HPT vane assembly 22 is engaged to a first, or radially inner, wall 30 of the combustor 16 by an inner joint assembly 34
  • the vane outer platform 28 is engaged to a second, or radially outer, wall 32 of the combustor 16 by an outer joint assembly 36.
  • An integral upstream lug portion 44 of the vane inner platform 26 extends upstream ' from the leading edge of the. vane airfoil 24, and projects into an annular slot defined between an outer flange portion 31 and an inner flange portion 29 of the combustor inner wall 30.
  • the inner joint assembly 34 accordingly formed, permits the upstream lug portion 44 of the vane inner platform 26 to be relatively displaceable within the flange portions of the combustor inner wall 30.
  • the inner joint assembly 34 is a sliding-type joint, which permits the upstream lug portion 44 of the vane inner platform 26 to axially slide within the flange portions of the combustor inner wall 30 in a direction substantially parallel to the direction 25 of the hot gas flow.
  • the inner joint assembly 34 also permits a small amount of radial displacement of the upstream lug portion 44 relative to the inner and outer flange portions 29 and 31 of the combustor inner wall 30.
  • an upstream lug portion 42 of the vane outer platform 28 projects upstream from the leading edge of the vane airfoil 24, for engagement with the outer wall 32 of the combustor 16.
  • the combustor 's outer wall 32 comprises an inner flange portion 33 which is preferably integrally formed with the main wall of the combustor, and an outer flange portion, or finger portion, 35 which define annular space- apart portions of the exit of the combustor.
  • the inner flange portion 33 and the outer flange portion 35 define a radial gap or slot 39 therebetween.
  • the upstream lug portion 42 of the vane outer platform 28 freely extends within the radial slot 39, such that relatively displacement between the upstream lug portion 42 and the combustor outer wall 32 is possible.
  • the upstream lug portion 42 is able to ' axially slide therewithin.
  • the outer joint assembly 36 is also a sliding-type joint, .and provides a sealing joint which is able to accommodate thermal deflection of the parts without requiring any locating fasteners such as rivets or bolts.
  • Each upstream lug portion 42 of the vane outer platforms 28 has an outer sliding surface 43, which is adapted to abut the outer flange portion 35 of the combustor outer wall 32 when the gas turbine engine is in operation, thereby forming a "pinching" effect which ensures a seal formed therewith.
  • a tight seal is required to prevent the high pressure air fed to the region 40 around the combustor 16 from leaking into the lower pressure gas path flowing through the HPT stage 17 of the turbine section 18.
  • the hot combustion gases flowing through the annular passage 23 tend to cause thermal growth of the HPT vane assembly 22, and therefore the outer platform 28 thereof, generally in the radial direction 50 as indicated in Fig. 3.
  • the outer flange portion 35 of the combustor outer wall 32 generally does not expand as much, as it is not in direct contact with the hot combustion gases and is exposed to the cooler high pressure air fed to the region 40 surrounding the combustor 16. Accordingly, the outer flange portion 35 experiences lower thermal growth in a radially outward direction than does the upstream lug portion 42. This resulting thermal growth differential causes a radial pinching effect in the sliding outer joint assembly 36, particularly between the outer flange portion 25 of the combustor outer wall 32 and the upstream lug portion 42 of the vane outer platform 28, which helps seal the connection between the HPT vane assembly 22 and the combustor 16.
  • outer flange portion 35 of the combustor outer wall 32 is preferably composed of sheet metal, where as at least the outer platform 28 of the vane assembly 22 is cast. This further contributes to the thermal growth differential between the two parts, permitting the outer flange portion 35 to stay relatively cool while the vane assembly radially expands. [0023]
  • the outer and inner joint assemblies 34,36 of the present invention, and particularly the outer joint assembly 36 comprise fewer parts, require no permanent fasteners such as rivets or bolts, and provide improved sealing as a result of the thermal growth differential between the vane outer platform 28 and the cooler combustor outer flange portion 35.
  • weight and cost considerations are of prime importance. Accordingly, reducing the number of parts and simplifying their design is a constant goal of all aerospace designers and engineers .
  • the combustor sliding joint assemblies 34,36 of the present invention achieve this by providing sealing connections which have fewer, less complex parts, thereby greatly simplifying the connection between the HPT vane assembly 22 and the combustor 16, particularly at the outer joint assembly 36 between the vane outer platform 28 and the combustor outer wall 32.
  • known combustors joints are concerned primarily with providing adequate sealing, however typically offer little in the way of structural support for mounting of the HPT vane assemblies. Therefore, separate structures are often provided to handle each of these requirements.
  • combustor joints 34,36 of the present invention provide by sealing and some structural mounting benefits, significant reductions in the complexity and overall weight are provided over known prior art combustor- vane assemblies.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

An assembly for a gas turbine engine (10), the assembly comprising a combustor (16) and a vane assembly (22) downstream from the combustor (16). The vane assembly (22) includes at least one airfoil (24) radially extending between an inner and outer platform (26,28) defining an annular gas path (23) therebetween. At least the outer platform (28) forms a first sliding joint connection (36) with an adjacent outer combustor wall (32) such that radial sealing between the outer platform (28) and the outer combustor wall (32) is provided at engine operating temperature, while permitting relative axial displacement there between.

Description

SLIDING JOINT BETWEEN COMBUSTOR WALL AND NOZZLE PLATFORM
TECHNICAL FIELD
[0001] The present invention relates generally to gas turbine engines, and more particularly to a joint between a high pressure turbine vane platform and a combustor flange therein .
BACKGROUND OF THE INVENTION
[0002] Secure and well sealed inter-engagement of the combustor and the high pressure turbine (HPT) stage immediately downstream therefrom is vital in a gas turbine engine. This portion of the engine experiences the highest temperatures, and therefore the joint formed between the combustor and the HPT vane assembly must be able to accommodate thermal deflections of the two structures due to the high temperatures. Thermal growth mismatch between the combustor walls and the platforms of the HPT vane may occur for a variety of reasons, such as a result of differences in materials, structure, surface temperatures and gas flow patterns for example. Accordingly, the joints linking these two structures must be able to accommodate these deflections, without reducing sealing effectiveness. A tight seal therebetween is required to prevent high pressure air, typically fed to the regions around the combustor, from leaking into the lower pressure gas path flowing through the turbine section.
[0003] Known joints between the combustor walls and the downstream HPT vane platforms, and especially the radially outer joints between the outer combustor wall and the outer HPT vane platform, are often excessively complex, typically having a plurality of parts and employing permanent fastening means such as rivets or bolts . SUMMARY OF THE INVENTION [0004] It is accordingly an object of the present invention to provide an improved combustor joint in a gas turbine engine .
[0005] It is another object of the present invention to provide an improved joint between a high pressure turbine vane outer platform and a combustor outer flange in a gas turbine engine .
[0006] Therefore, in accordance with the present invention, there is provided an assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly downstream from the combustor, the vane assembly "including at least one airfoil radially extending between an inner and outer platform defining an annular gas path therebetween, wherein at least the outer platform forms a first sliding joint connection with an adjacent outer combustor wall such that radial sealing between the outer platform and the outer combustor wall is provided at engine operating temperature while permitting relative axial displacement therebetween.
■ [0007] There is also provided, in accordance with the present invention, an assembly for a gas turbine engine, the assembly comprising: a combustor having a combustor. wall circumscribing a gas path therewithin and an exit duct end, the exit duct end having an outer flange portion radially spaced from the combustor wall in a direction away from the gas path to form an annular slot; a vane assembly disposed downstream of the combustor, the vane assembly including at least one airfoil extending between an inner and an outer platform; and a portion of at least the outer platform extending in the annular slot defined between the combustor wall and the outer flange portion, the portion being retained by the combustor wall and the outer flange portion such that the vane assembly is mounted to the combustor and sealed therewith.
[0008] There is also provided, in accordance with the present, invention, a method of sealing a joint in an assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly, the method comprising: providing a vane assembly mounted to an exit duct of the combustor, the vane assembly having at least one airfoil extending between an inner and an outer platform, at least the outer platform engaging a flange portion of the combustor exit duct; determining an amount of thermal growth differential exhibited between the flange portion and the at least the outer platform over an engine operating temperature range; and forming a joint between the flange portion and the at least the outer platform such that a spacing distance therebetween at ambient temperature is less than the determined amount of thermal growth differential over the engine operating temperature range, such that the spacing distance closes over the engine operating temperature range to provide a seal between the vane assembly and the combustor.
[0009] There is further provided, in accordance with the present invention a combustor for a gas turbine engine, the combustor comprising a combustor body having at least an annular exit end adapted to communicate with a vane assembly, the exit end defined by an inner exit lip and an outer exit lip, the inner and outer exit lips each having a pair of spaced-apart members, each pair of said members adapted to slidingly engage therebetween one of a pair of spaced-apart platforms of the vane assembly, one of said members being an innermost member relative to the combustor and one of said members being an outermost member relative to the combustor, wherein the spaced-apart members .are adapted such that said sliding engagement secures the vane assembly to the combustor independent of other retention means when the combustor is assembled with said vane assembly, and wherein at least one of the outermost and innermost members is flexible to thereby permit, in use, said spaced-apart vane platforms to expand apart from one another .
[0010] In accordance with the present invention, there is additionally provided a combustor-to-vane joint assembly for a gas turbine engine, the combustor including an annular exit end for mating with an annular vane ring assembly, the vane ring assembly defined by inner and outer platform rings, the joint comprising: inner and outer female retaining members integral with and defining a downstream end of the annular exit, the female retaining members each including spaced-apart annular portions; and inner and outer male insertion members integral with and defining an upstream end of the vane assembly platform rings; wherein the vane assembly is mounted to the combustor solely by insertion of the inner and outer male insertion members between the spaced-apart . portions of the respective inner and outer female retaining members .
[0011] There is additionally provided, in accordance with the present invention, an assembly for a gas turbine engine, the assembly comprising a combustor having a wall and an exit end, and an exit vane assembly mounted to the exit end on an inner side and an outer side relative to the combustor, the vane assembly including at least an inner platform and an outer platform, wherein the combustor exit end includes a finger element mounted to the combustor and spaced apart from the combustor wall,- and wherein the vane assembly outer platform is held between the finger element and combustor wall to thereby mount the vane assembly to the combustor.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Further features and advantages of the present invention will become apparent from the following detailed description, taken in combination with the appended drawings, in which:
[0013] Fig. 1 is a schematic cross-section of a gas turbine engine having a combustor joint in accordance with the present invention; i [0014] Fig. 2 is a cross-section of a combustor and high pressure turbine of the prior art; and
[0015] Fig. 3 is a cross-section of a joint between a combustor flange and a high pressure turbine in accordance with the present invention.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT [0016] Fig. 1 schematically illustrates a gas turbine engine 10 (a turbofan preferably adapted for use on an aircraft in subsonic flight in this case, though the invention may be practised in almost any gas turbine engine) generally comprising, in serial flow communication, a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed ■ air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases. [0017] The turbine section 18 further comprises at least a first, or high pressure (HP) , turbine stage 17 which is immediately downstream from the combustor 16. As seen in Fig. 3, the high pressure turbine stage 17 includes a turbine rotor 20 with a plurality of radially extending turbine blades 21, and a high pressure turbine (HPT) vane assembly 22 immediately upstream therefrom. The joint between the HPT vane assembly 22 and the combustor 16 of the present invention is described in detail below with reference to Fig. 3.
[0018] In a prior art gas turbine engine of the prior art as shown in Fig. 2, a reverse flow combustor 916 provides hot combustion gases to a downstream HPT stage 917 of the gas turbine engine's turbine ' section 918. The HPT stage 917 comprises generally an HPT vane assembly 922 and an HPT rotor assembly 920. The HPT vane assembly 922 includes an airfoil 924 extending between an inner platform 926 and an outer platform 928, which define an annular passage 923 therebetween for directing the hot gases. therethrough. The radially inner platform 926 of the PHT vane assembly 922 is engaged to a first, or radially inner, wall 930 of the combustor 916 by an inner joint 934. The radially outer platform 928 is engaged to a second, or radially outer, wall 932 of the combustor. The inner joint 934 is a sliding-type joint, wherein axial movement of the inner platform 926 relative to the combustor inner wall 930 is possible. The outer joint 936 is much more complex, typically employing fastening members such as rivets or bolts to fasten the inner platform 928 of the HPT vane assembly 922 to the outer wall 932 of the combustor. Such an outer joint 936 therefore securely fixes the . outer platform 928 in place on the combustor outer wall 932 such that an adequate seal therebetween is ensured. A tight seal therebetween is required to prevent high pressure air, typically fed to the regions 940 around the combustor 916, from leaking into the lower pressure gas path flowing through the turbine section 918.
[0019] Referring now to Fig. 3, the inter-engagement between the combustor 16 and the HPT vane assembly 22 of the present invention is clearly seen. The HPT vane assembly
22 comprises a plurality of airfoils 24 radially extending between inner platforms 26 and outer platforms 28, which are circumferentially disposed about a central longitudinal axis of the gas turbine engine to define an annular passage
23 therebetween, within which the hot combustion gases are channelled in direction 25. The HPT vane assembly 22 is located immediately downstream from the combustor 16, and is accordingly engaged thereto at the combustor exit. Generally, the vane inner platform 26 of the HPT vane assembly 22 is engaged to a first, or radially inner, wall 30 of the combustor 16 by an inner joint assembly 34, and the vane outer platform 28 is engaged to a second, or radially outer, wall 32 of the combustor 16 by an outer joint assembly 36.
[0020] An integral upstream lug portion 44 of the vane inner platform 26 extends upstream ' from the leading edge of the. vane airfoil 24, and projects into an annular slot defined between an outer flange portion 31 and an inner flange portion 29 of the combustor inner wall 30. The inner joint assembly 34 accordingly formed, permits the upstream lug portion 44 of the vane inner platform 26 to be relatively displaceable within the flange portions of the combustor inner wall 30. Particularly, the inner joint assembly 34 is a sliding-type joint, which permits the upstream lug portion 44 of the vane inner platform 26 to axially slide within the flange portions of the combustor inner wall 30 in a direction substantially parallel to the direction 25 of the hot gas flow. The inner joint assembly 34 also permits a small amount of radial displacement of the upstream lug portion 44 relative to the inner and outer flange portions 29 and 31 of the combustor inner wall 30.
[0021] Referring now to the outer joint assembly 36 between the HPT vane assembly 22 and the upstream combustor 16, an upstream lug portion 42 of the vane outer platform 28 projects upstream from the leading edge of the vane airfoil 24, for engagement with the outer wall 32 of the combustor 16. The combustor 's outer wall 32 comprises an inner flange portion 33 which is preferably integrally formed with the main wall of the combustor, and an outer flange portion, or finger portion, 35 which define annular space- apart portions of the exit of the combustor. The inner flange portion 33 and the outer flange portion 35 define a radial gap or slot 39 therebetween. The upstream lug portion 42 of the vane outer platform 28 freely extends within the radial slot 39, such that relatively displacement between the upstream lug portion 42 and the combustor outer wall 32 is possible. Particularly, the upstream lug portion 42 is able to 'axially slide therewithin. Accordingly, the outer joint assembly 36 is also a sliding-type joint, .and provides a sealing joint which is able to accommodate thermal deflection of the parts without requiring any locating fasteners such as rivets or bolts.
[0022] Each upstream lug portion 42 of the vane outer platforms 28 has an outer sliding surface 43, which is adapted to abut the outer flange portion 35 of the combustor outer wall 32 when the gas turbine engine is in operation, thereby forming a "pinching" effect which ensures a seal formed therewith. A tight seal is required to prevent the high pressure air fed to the region 40 around the combustor 16 from leaking into the lower pressure gas path flowing through the HPT stage 17 of the turbine section 18. Particularly, during operation of the gas turbine engine 10, the hot combustion gases flowing through the annular passage 23 tend to cause thermal growth of the HPT vane assembly 22, and therefore the outer platform 28 thereof, generally in the radial direction 50 as indicated in Fig. 3. While one would typically expect corresponding thermal growth of the combustor walls, the outer flange portion 35 of the combustor outer wall 32 generally does not expand as much, as it is not in direct contact with the hot combustion gases and is exposed to the cooler high pressure air fed to the region 40 surrounding the combustor 16. Accordingly, the outer flange portion 35 experiences lower thermal growth in a radially outward direction than does the upstream lug portion 42. This resulting thermal growth differential causes a radial pinching effect in the sliding outer joint assembly 36, particularly between the outer flange portion 25 of the combustor outer wall 32 and the upstream lug portion 42 of the vane outer platform 28, which helps seal the connection between the HPT vane assembly 22 and the combustor 16. Additionally, the outer flange portion 35 of the combustor outer wall 32 is preferably composed of sheet metal, where as at least the outer platform 28 of the vane assembly 22 is cast. This further contributes to the thermal growth differential between the two parts, permitting the outer flange portion 35 to stay relatively cool while the vane assembly radially expands. [0023] Such sliding joint connections between both the vane outer and inner platforms 28,26 and the corresponding combustor walls 32,30, significantly improve the engagement between the HPT vane assembly 22 and the combustor 16 at engine operating temperature. In comparison with typical prior art combustor-HPT vane joints, the outer and inner joint assemblies 34,36 of the present invention, and particularly the outer joint assembly 36, comprise fewer parts, require no permanent fasteners such as rivets or bolts, and provide improved sealing as a result of the thermal growth differential between the vane outer platform 28 and the cooler combustor outer flange portion 35. In all gas turbine engines, and particularly those intended for aerospace applications, weight and cost considerations are of prime importance. Accordingly, reducing the number of parts and simplifying their design is a constant goal of all aerospace designers and engineers . The combustor sliding joint assemblies 34,36 of the present invention achieve this by providing sealing connections which have fewer, less complex parts, thereby greatly simplifying the connection between the HPT vane assembly 22 and the combustor 16, particularly at the outer joint assembly 36 between the vane outer platform 28 and the combustor outer wall 32.
[0024] Further, known combustors joints are concerned primarily with providing adequate sealing, however typically offer little in the way of structural support for mounting of the HPT vane assemblies. Therefore, separate structures are often provided to handle each of these requirements. As the combustor joints 34,36 of the present invention provide by sealing and some structural mounting benefits, significant reductions in the complexity and overall weight are provided over known prior art combustor- vane assemblies.
[0025] The embodiments of the invention described above are intended to be exemplary. Still other modifications are available, and those skilled in the art will therefore appreciate that the forgoing description is illustrative only, and that various alternatives and modifications can be devised without departing from the spirit of the present invention. Accordingly, the present invention is intended to embrace all such alternatives, modifications and variances which fall within the scope of the appended claims .

Claims

CLAIMS :
An assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly downstream from the combustor, the vane assembly including at least one airfoil radially extending between an inner and outer platform defining an annular gas path therebetween, wherein at least the outer platform forms a first sliding joint connection with an adjacent outer combustor wall such that radial sealing between the outer platform and the outer combustor wall is provided at engine operating temperature while permitting relative axial displacement therebetween..
The assembly as defined in claim 1, wherein the inner platform forms a second sliding joint connection with an adjacent inner combustor wall, the second sliding joint connection permitting relative axial displacement between the inner platform and the inner combustor wall.
The assembly as defined in claim 2, wherein the outer platform and the inner platform include upstream ends which respectively mate with the outer and inner combustor walls to form the first and second sliding joint connections.
The assembly as defined in claim 3, wherein the upstream ends of the outer platform and the inner platform project upstream from a leading edge of the airfoil .
5. The assembly as defined in claim 4, wherein the outer and inner combustor walls comprise a bifurcated flange at an exit of the combustor, the bifurcated flange having a first flange portion and a second flange portion radially spaced apart from the first flange portion in a direction away from the annular gas path, thereby defining an annular gap between the first flange portion and the second flange portion.
6. The assembly as defined in claim 5, wherein the upstream ends of the outer platform and the inner platform are receivable within the annular gap.
7. The assembly as defined in claim 6, wherein the upstream end of at least the outer platform includes a sliding surface facing radially outward, the sliding surface being adapted for pressed abutment with the second flange portion at engine operating temperature such that a seal therebetween is formed.
8. An assembly for a gas turbine engine, the assembly comprising: a combustor having a combustor wall circumscribing a gas path therewithin and an exit duct end, the exit duct end having an outer flange portion radially spaced from the combustor wall in a direction away from the gas path to form an annular slot; a vane assembly disposed downstream of the combustor, the vane assembly including at least one airfoil extending between an inner and an outer platform; and a portion of at least the outer platform extending in the annular slot defined between the combustor wall and the outer flange portion, the portion being retained by the combustor. wall and the outer flange portion such that the vane assembly is mounted to the combustor and sealed therewith.
9. The assembly as defined in claim 8, wherein a sliding joint connection is provided between the outer platform of the vane assembly and the combustor.
-10. The assembly as defined in claim 9, wherein the sliding joint connection extends axially, thereby permitting relative axial displacement between the vane assembly and the combustor.
11. The assembly as defined in claim 10, wherein the sliding joint connection includes the portion of at least the outer platform, the portion of at least the outer platform being an upstream end thereof having a sliding surface, the sliding surface being adapted for pressed abutment with the outer flange portion at engine operating temperature such that a radial seal therebetween is formed.
12. The assembly as defined in claim 8, wherein the outer flange portion circumscribes the combustor exit duct end, and a portion of the inner platform of the vane assembly extends between the combustor wall and the outer flange portion.
13. The assembly as defined in claim 12, wherein a second sliding joint connection is provided between the inner platform and the combustor exit duct end.
14. The assembly as defined in claim 8, wherein the outer flange portion comprises a first thermal expansion coefficient and the outer platform comprises a second thermal expansion coefficient, the second thermal expansion coefficient being greater than the first thermal expansion coefficient.
15. The assembly as defined in claim 8, wherein the outer flange portion is in contact with cool air relative to the gas path to which the outer platform is exposed such that a thermal growth differential exits between the outer flange portion and the outer platform, thereby causing the outer platform to expand sufficiently more than the outer flange portion to form a seal therebetween.
16. A method of sealing a joint in an assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly, the method comprising: providing a vane assembly mounted to an exit duct of the combustor, the vane assembly having at least one airfoil extending between an inner and an outer platform, at least the outer platform engaging a flange portion of the combustor exit duct; determining an amount of thermal growth differential exhibited between the flange portion and the at least the outer platform over an engine operating temperature range; and forming a joint between the flange portion and the at least the outer platform such that a spacing distance therebetween at ambient temperature is less than the determined amount of thermal growth differential over the ; engine operating temperature range, such that the spacing distance closes over the engine operating temperature range to provide a seal between the vane assembly and the combustor.
17. A combustor for a gas turbine engine, the combustor comprising a combustor body having at least an annular exit end adapted to communicate with a vane assembly, the exit end defined by an inner exit lip and an outer exit lip, the inner and outer exit lips each having a pair of spaced-apart members, each pair of said members adapted to slidingly engage therebetween one of a pair of spaced-apart platforms of the vane assembly, one of said members being an innermost member relative to the combustor and one of said members being an outermost member relative to the combustor, wherein the spaced-apart members are adapted such that said sliding engagement secures the vane assembly to the combustor independent of other retention means when the combustor is assembled with said vane assembly, and wherein at least one of the outermost and innermost members is flexible to thereby permit, in use, said spaced-apart vane platforms to expand apart from one another. 8'. A combustor-to-vane joint assembly for a gas turbine engine, the combustor including an annular exit end for mating with an annular vane ring assembly, the vane ring assembly defined by inner and outer platform rings, the joint comprising: inner and outer female retaining members integral with and defining a downstream end of the • annular exit, the female retaining members each including spaced-apart annular portions; and inner and outer male insertion members integral with and _ defining an upstream end of the vane assembly platform rings; wherein the vane assembly is mounted to the combustor solely by insertion of the inner and outer male insertion members between the spaced-apart portions of the respective inner and outer female retaining members .
19. The combustor-to-vane joint assembly of claim 18 wherein there is an interference fit between the male insertion members and at least an innermost annular portion and an outermost annular portion of the spaced-apart annular portions of the female retaining members .
20. An assembly fo'r a gas turbine engine,, the assembly comprising a combustor having a wall and an exit end, and an exit vane assembly mounted to the exit end on an inner side and an outer side relative to the combustor, the vane assembly including at least an inner platform and an outer platform, wherein the combustor exit end includes a finger element mounted to the combustor and spaced apart from the combustor wall, and wherein the vane assembly outer platform is held between the finger element and combustor wall to thereby mount the vane assembly to the combustor.
PCT/CA2004/001016 2003-12-03 2004-07-19 Sliding joint between combustor wall and nozzle platform WO2005054632A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP04761568A EP1706594B1 (en) 2003-12-03 2004-07-19 Sliding joint between combustor wall and nozzle platform
CA2549162A CA2549162C (en) 2003-12-03 2004-07-19 Sliding joint between combustor wall and nozzle platform
JP2006541763A JP2007513281A (en) 2003-12-03 2004-07-19 Peristaltic joint between combustor wall and nozzle platform

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/725,578 US7000406B2 (en) 2003-12-03 2003-12-03 Gas turbine combustor sliding joint
US10/725,578 2003-12-03

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WO2005054632A1 true WO2005054632A1 (en) 2005-06-16

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EP (1) EP1706594B1 (en)
JP (1) JP2007513281A (en)
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CA2549162C (en) 2012-09-18
JP2007513281A (en) 2007-05-24
US20050120718A1 (en) 2005-06-09
US7000406B2 (en) 2006-02-21
CA2549162A1 (en) 2005-06-16
EP1706594B1 (en) 2011-11-09
EP1706594A1 (en) 2006-10-04

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