EP2859189B1 - Dispositif d'assemblage pour un ensemble aube de stator - Google Patents

Dispositif d'assemblage pour un ensemble aube de stator Download PDF

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Publication number
EP2859189B1
EP2859189B1 EP13796412.8A EP13796412A EP2859189B1 EP 2859189 B1 EP2859189 B1 EP 2859189B1 EP 13796412 A EP13796412 A EP 13796412A EP 2859189 B1 EP2859189 B1 EP 2859189B1
Authority
EP
European Patent Office
Prior art keywords
fixture
locating
pin
vanes
plane
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
EP13796412.8A
Other languages
German (de)
English (en)
Other versions
EP2859189A1 (fr
EP2859189A4 (fr
Inventor
Michael E. Mcmahon
Steven J. Feigleson
Dennis R. Tremblay
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.)
RTX Corp
Original Assignee
United Technologies Corp
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Publication date
Priority claimed from US13/483,501 external-priority patent/US8966755B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2859189A1 publication Critical patent/EP2859189A1/fr
Publication of EP2859189A4 publication Critical patent/EP2859189A4/fr
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Publication of EP2859189B1 publication Critical patent/EP2859189B1/fr
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures

Definitions

  • a gas turbine engine typically includes a fan section, and a core engine section including a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section.
  • the compressor section typically includes low and high pressure compressors, and the turbine section includes low and high pressure turbines.
  • the high pressure turbine drives the high pressure compressor through an outer shaft to form a high spool
  • the low pressure turbine drives the low pressure compressor through an inner shaft to form a low spool
  • a direct drive gas turbine engine includes a fan section driven by the low spool such that the low pressure compressor, low pressure turbine and fan section rotate at a common speed in a common direction.
  • a speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine.
  • Some front architectures support the stator vanes relative to inner and outer fairings using rubber potting. Because there are no fixed features or fasteners used to secure vanes within the fairings, assembly can be difficult and time consuming.
  • EP 2, 312, 186 A1 and CA 2, 682, 818 A1 disclose a method of manufacturing a fairing with an integrated seal.
  • EP 2, 447, 475 A2 discloses a fixture for assembling a stator vane assembly for a gas turbine engine including an inner and outer fairing.
  • An embodiment of any of the foregoing methods including positioning each of the multiple vanes by defining a first plane with at least three contact points on the fixture, a second plane with at least two contact points on the fixture and a third plane with at least one contact point defined on the fixture.
  • a further embodiment of any of the foregoing methods including defining the first plane with an outer locator pin on an outer locating ring of the fixture, an inner locator pin on an inner locating ring and a clamp disposed between the inner and outer locating rings.
  • a further embodiment of any of the foregoing methods including a single clamp for holding each of the vanes in position.
  • the single clamp is disposed between the inner locating pin and the outer locating pin and includes a clamp portion supported on a clamp pin with the vane being clamped between the clamp portion and the clamp pin.
  • a further embodiment of any of the foregoing methods including defining the second plane with a surface of an outer locating ring and an inner locating ring.
  • a further embodiment of any of the foregoing methods including defining the third plane with a radial locating pin supported radially inward of the inner fairing.
  • a fixture for assembling a stator vane assembly for a gas turbine engine according to claim 9.
  • the fixture defines a first plane with at least three contact points, a second plane with at least two contact points and a third plane with at least one contact point.
  • clamp portion is supported on the clamp pin and is configured to hold the vane against the clamp pin, the inner locating pin and the outer locating pin.
  • a further embodiment of any of the foregoing fixtures including a fastener for applying a desired pressure to a corresponding one of the plurality of vanes for holding the vane within the defined first, second and third planes.
  • outer locating pin extends transversely from an outer locating surface and the inner locating pin extends transversely from an inner locating surface and the second plane is defined by the outer and inner locating surfaces adjacent the corresponding inner and outer locating pins.
  • FIG. 1 schematically illustrates an example gas turbine engine 20 that includes a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmenter section (not shown) among other systems or features.
  • the fan section 22 drives air along a bypass flow path B while the compressor section 24 draws air in along a core flow path C where air is compressed and communicated to a combustor section 26.
  • air is mixed with fuel and ignited to generate a high pressure exhaust gas stream that expands through the turbine section 28 where energy is extracted and utilized to drive the fan section 22 and the compressor section 24.
  • turbofan gas turbine engine depicts a turbofan gas turbine engine
  • the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines; for example a turbine engine including a three-spool architecture in which three spools concentrically rotate about a common axis and where a low spool enables a low pressure turbine to drive a fan via a gearbox, an intermediate spool that enables an intermediate pressure turbine to drive a first compressor of the compressor section, and a high spool that enables a high pressure turbine to drive a high pressure compressor of the compressor section.
  • the example engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided.
  • the low speed spool 30 generally includes an inner shaft 40 that connects a fan 42 and a low pressure (or first) compressor section 44 to a low pressure (or first) turbine section 46.
  • the inner shaft 40 drives the fan 42 through a speed change device, such as a geared architecture 48, to drive the fan 42 at a lower speed than the low speed spool 30.
  • the high-speed spool 32 includes an outer shaft 50 that interconnects a high pressure (or second) compressor section 52 and a high pressure (or second) turbine section 54.
  • the inner shaft 40 and the outer shaft 50 are concentric and rotate via the bearing systems 38 about the engine central longitudinal axis A.
  • the example gas turbine engine 20 includes a front architecture 62 that includes a plurality of stator vanes 64.
  • the plurality of stator vanes 64 are disposed aft of the fan section 22 and fan blades 42 at the inlet for core air flow C.
  • the plurality of stator vanes 64 are disposed forward of a plurality of inlet guide vanes 66 that are disposed prior to a low pressure compressor 44.
  • the plurality of stator vanes 64 are arranged circumferentially about the engine axis A within the inlet for core engine flow C.
  • stator vanes 64 are part of a stator vane assembly 68 that includes an outer fairing 70 and an inner fairing 72.
  • the plurality of stator vanes 64 extend between the inner fairing 72 and the outer fairing 70.
  • stator vanes 64 are supported within openings or slots 74 defined within each of the inner and outer fairings 72, 70.
  • Each of the stator vanes 64 includes an inner end 80, an outer end 82, a leading edge 84 and a trailing edge 86.
  • Each of the stator vanes 64 are supported within the openings 74 by a sealant 76.
  • the example sealant 76 is a curable material that remains flexible once cured.
  • the stator vanes 64 are mounted within the openings 74 by way of the curable sealant material 76.
  • the sealant 76 provides a bonded joint between the inner and outer fairings 70, 72 and is injected into the openings and within gaps between each of the vanes 64 and the corresponding slot 74 to vibrationally isolate the outer and inner fairings 70, 72 from the stator vanes 64.
  • Each of the stator vanes 64 include tabs 78 that secured the vane 64 within the outer fairing 70 and prevents it from sliding through the opening 74. However, it is the sealant 76 that provides the joint that maintains each of the vanes 64 in a desired position relative to the other vanes 64 and each of the outer and inner fairings 70, 72.
  • Assembly of the stator vane assembly 68 requires specific positioning of each of the vanes 64 within corresponding openings 74. Positioning within the openings 74 is provided such that the vanes 64 themselves do not engage the outer and inner fairings 70, 72.
  • An assembly fixture is utilized to define and maintain a relative position between the plurality of stator vanes 64 and the outer and inner fairings 70, 72 while the sealant 76 is applied and cured to form the completed stator vane assembly 68.
  • an example disclosed assembly fixture 88 includes a base 90 that supports the outer fairing 70 and the inner fairing 72 along with the plurality of stator vanes 64 in a desired position for assembly including the application and curing of the sealant 76 ( Figures 4 and 5 ).
  • the example assembly fixture 88 defines the specific datum planes and points required to properly align each of the plurality of vanes 64 relative to adjacent vanes and the outer and inner and fairings 70, 72.
  • the example fixture assembly 88 includes the base 90 that holds clamps 114 that are provided to hold the outer fairing 70 in place.
  • the base 90 also includes pins 124 that align with openings within the fairing 70 to align the outer fairing 70.
  • An outer locating ring 92 includes a plurality of locating pins 94 disposed radially inward of the mounted outer fairing 70.
  • An inner locating ring 96 is disposed radially inward of the outer locating ring 92 and includes inner locating pin 98.
  • a clamp section 104 is disposed between the inner and outer locating rings 96, 92 and includes a clamp portion 106 supported on a clamp pin 108.
  • the inner fairing 72 is supported on an inner portion of the base 90 and held in place by inner clamps 116. Similarly, the outer fairing 70 is held in place by outer clamps 114.
  • the inner locating ring 96 and the outer locating ring 92 includes surfaces 100, 102 that support the vane 64 within the openings 74.
  • Figures 8a and 8b are schematic representations illustrating the planes utilized to align the vanes 64 relative to the fairings 70, 72.
  • a first plane 118 is defined along a surface of the vane 64 that is transverse to a surface of the base 90.
  • a second plane 120 ( Figure 8B ) is defined along the base 90 and along the surfaces 100 and 102 of the inner and outer locating rings 96, 92.
  • a third datum plane 122 is defined at the radially inner most position and sets a radial position of the vane 64.
  • the first plane 118 is defined by the inner locating pin 98, the outer locating pin 94 and a clamp post 108.
  • Each of the inner pin 98, the outer pin 94, and the clamp post 108 defines a point along the first plane 118.
  • the inner locating pin 98 defines a point 128.
  • the outer locating pin 94 defines another point 130 between the pin 94 and the vane 64.
  • the clamp post 108 defines a third locating point 132 between the post 108 and the vane 64.
  • the second plane 120 ( Figure 8b ) is defined by the surface 100 of the outer locating ring 92 and the surface 102 of the inner locating ring 92.
  • the surfaces 100 and 102 are disposed adjacent the corresponding locating pin 94, 98.
  • the radial position defined as plane 122 is defined by the radial pin 140 that abuts the inner end 80 of the vane 64.
  • the example fixture 88 includes the inner locating ring 96 that includes the surface 102 and the locating pin 98.
  • the surface 102 defines the locating point 134 for the second plane 120.
  • the locating pin 98 defines the first point 128 along the plane 118.
  • the vane 64 is abutted against the pin 98 and the bottom surface 102 to set one point along the first plane 118 and the second plane 120.
  • the outer locating ring 92 includes the surface 100 and the locating pin 94.
  • the vane 64 is abutted against the surface 100 and the pin 94.
  • the pin 94 defines the locating point 130 that is a second point along the plane 118.
  • the outer ring surface 100 defines another point 136 that defines a second point along the plane 120.
  • a third point along the plane 118 is defined by the clamp post 108.
  • the example clamp section 104 includes the clamp post 108 that extends upwardly from the base 90.
  • the example clamp post 108 includes a point 132 onto which the vane 64 comes into contact.
  • the example point 132 defines a third point along the plane 118.
  • the example vane 64 abuts the outer locating pin 94, the inner locating pin 98, and the clamp pin 108 to define the first plane 118.
  • the first plane 118 includes a specific orientation of the vane 64 that corresponds with the aerodynamic shape of the vane 64.
  • the clamp section 104 holds and defines an angular orientation of each of the plurality of vanes 64 relative to each of the outer and inner fairings70, 72.
  • the clamp post 108 that supports a surface of the vane 64 and also a clamp portion 106 including a clamp surface 112 that engages an opposite end of the vane 64 and is utilized to hold the vane 64 in contact with the clamp post 108 and the locating pins 94 and 98.
  • each of the vanes 64 is defined by radial locating pins 140 within the radial positioning section 142.
  • An inner end 80 of each of the vanes 64 engages the surface of each of the corresponding radial locator pins 140 to define and set a desired radial position of each of the vanes 64 in relation to the corresponding outer and inner fairings 70, 72.
  • Figure 12 further shows a top view of the clamp section 104 where the clamp portions 106 are held to a corresponding clamp post 108 by a clamp fastener 110.
  • Each of the clamp fasteners 110 provides for securement of the corresponding vane 64 independent of the other vanes 64.
  • the example fixture 88 is utilized to define the relative position between the outer and inner fairings 70, 72 prior to application of the sealant 76.
  • the individual vanes 64 are inserted into the fixture 88 after the corresponding outer and inner fairings 70, 72 are mounted to the base plate 90.
  • the outer and inner and outer fairings 70, 72 are aligned on the base plate 90 utilizing the locating pins 124 and 126.
  • each of the plurality of vanes 64 is inserted into the fixture 88.
  • the vanes 64 are inserted through the opening 74 within the outer fairing 70 radially inward until abutting the radial locating pin 40.
  • the clamp portion 106 of the clamp section 104 is secured to bias and hold the vane 64 against the locating pins 98 and 94 on corresponding inner and outer locating rings 92, 96.
  • the clamp portion 106 also secures and holds the vane assembly 64 against the corresponding inner locating ring surface 100 and outer locating surface 102.
  • the sealant 76 can be applied to the gaps between each of the vanes 64 and the corresponding fairings 70. 72.
  • the sealant 76 is applied within the gap to secure the vane 64 within the outer and inner fairings 70, 72 and also to eliminate vibratory transmission between parts.
  • the example fixture 88 is comprised of a material compatible with the conditions utilized for curing the sealant 76 within the openings 74. Once the sealant 76 has properly cured the stator vane assembly 68 can be removed from the fixture 88. Removal of the vane assembly from the fixture includes removal of the clamp portions 106 from the clamp section 104. Once the clamp portions 106 are removed, the outer clamps 114 and the inner clamps 116 can be removed to allow the completed stator vane assembly 68 to be lifted upwardly off of the base plate 90.
  • the example fixture 88 provides for the specific positioning of each of a plurality of vanes 64 relative to the outer and inner fairings 70, 72 such that sealant 76 can be applied to hold each of the vanes 64 within the assembly. Further, the example fixture 88 defines the specific datum points and planes that are utilized to align each of the vanes 64 relative to adjacent vanes 64 and the outer and inner fairings 70, 72.

Claims (14)

  1. Procédé d'assemblage de l'architecture avant d'un moteur à turbine à gaz (20) comprenant les étapes consistant à :
    fixer les carénages interne et externe (72, 70) à l'intérieur d'une pièce fixe (88) l'un par rapport à l'autre ;
    positionner chacune des multiples aubes (64) à l'intérieur d'une ouverture (74) de chacun des carénages interne et externe (72, 70), de sorte que les multiples aubes (64) n'entrent pas en prise avec les carénages interne et externe (72, 70) ;
    fixer les multiples aubes (64) entre les carénages interne et externe (72, 70) à l'intérieur de la pièce fixe ;
    appliquer un matériau durcissable à une interface entre chacune des multiples aubes (64) et les carénages interne et externe (72, 70) ;
    durcir le matériau durcissable toute en maintenant une position relative entre les multiples aubes (64) et les carénages interne et externe (72 ; 70) ; dans lequel le matériau durcissable reste flexible une fois durci ;
    et libérer les multiples aubes (64) et les carénages interne et externe (72 ; 70) de la pièce fixe (88).
  2. Procédé selon la revendication 1, comprenant le positionnement de chacune des multiples aubes (64) en définissant un premier plan (118) à l'aide d'au moins trois points de contact (128, 130, 132) sur la pièce fixe (88), un deuxième plan (120) à l'aide d'au moins deux points de contact (134, 136) sur la pièce fixe et un troisième plan (122) à l'aide d'au moins un point de contact défini sur la pièce fixe (88).
  3. Procédé selon la revendication 2, comprenant la définition du premier plan (118) à l'aide d'une goupille de positionnement externe (94) sur une bague de positionnement externe (92) de la pièce fixe, une goupille de positionnement interne (98) sur une bague de positionnement interne (96) et une pièce de serrage (104) disposée entre les bagues de positionnement interne et externe (96, 92).
  4. Procédé selon la revendication 3, comprenant une pièce de serrage unique (104) destinée à maintenir chacune des aubes (64) en position.
  5. Procédé selon la revendication 4, dans lequel la pièce de serrage unique (104) est disposée entre la goupille de positionnement interne (98) et la goupille de positionnement externe (94) et comprend une partie de serrage (106) supportée sur une goupille de serrage (108), l'aube (64) étant fixée entre la partie de serrage (106) et la goupille de serrage (108).
  6. Procédé selon l'une quelconque des revendications 2 à 5, comprenant la définition du deuxième plan (120) à l'aide d'une surface (102, 100) d'une bague de positionnement externe (92) et d'une bague de positionnement interne (96).
  7. Procédé selon l'une quelconque des revendications 2 à 6, comprenant la définition du troisième plan (122) à l'aide d'une goupille de positionnement radial (140) supportée radialement vers l'intérieur du carénage interne (72).
  8. Procédé selon une quelconque revendication précédente, dans lequel la pluralité d'aubes (64) sont maintenues à l'intérieur de la pièce fixe (88) pendant le durcissement du matériau durcissable.
  9. Pièce fixe (88) permettant d'assembler un ensemble aube de stator (68) pour un moteur à turbine à gaz (20) comprenant :
    un carénage externe (70) ; et
    un carénage interne (72) ; caractérisée par
    une bague de positionnement externe (92) comprenant une pluralité de goupilles de positionnement externes (94) définissant une position pour chaque aube parmi une pluralité d'aubes (64) par rapport au carénage externe (70) ;
    une bague de positionnement interne (96) comprenant une pluralité de goupilles de positionnement internes (98) définissant une position de chaque aube parmi la pluralité d'aubes (64) par rapport au carénage interne (72) ;
    une section de serrage (104) comprenant une partie de serrage (106) et une goupille de serrage (108) définissant une orientation angulaire de chaque aube parmi la pluralité d'aubes (64) par rapport à chaque carénage parmi les carénages interne et externe (72, 70) ; et
    une section de positionnement interne (142) supportant une pluralité de goupilles de positionnement radial (140) définissant une position radiale de chaque aube parmi la pluralité d'aubes (64) par rapport aux carénages interne et externe (72, 70).
  10. Pièce fixe selon la revendication 9, dans laquelle la pièce fixe définit un premier plan (118) à l'aide d'au moins trois points de contact (128, 130, 132), un deuxième plan (120) à l'aide d'au moins deux points de contact (134, 136) et un troisième plan (122) à l'aide d'au moins un point de contact.
  11. Pièce fixe selon la revendication 10, dans laquelle la goupille de positionnement externe (94) sur la bague de positionnement externe (92) de la pièce fixe, la goupille de positionnement interne (98) sur la bague de positionnement interne (96) et la goupille de serrage (108) définissent le premier plan (118).
  12. Pièce fixe selon la revendication 10 ou 11, dans laquelle la partie de serrage (104) est supportée sur la goupille de serrage (108) et est conçue pour maintenir l'aube (64) contre la goupille de serrage (108), la goupille de positionnement interne (98) et la goupille de positionnement externe (94), et éventuellement dans laquelle la pièce fixe comprend un élément de fixation (110) permettant d'appliquer une pression souhaitée sur une aube correspondante parmi la pluralité d'aubes (64) pour maintenir l'aube (64) à l'intérieur des premier, deuxième et troisième plans définis (118, 120, 122).
  13. Pièce fixe selon la revendication 11 ou 12, dans laquelle la goupille de positionnement externe (94) s'étend transversalement à partir d'une surface de positionnement externe (102) et la goupille de positionnement interne (98) s'étend transversalement à partir d'une surface de positionnement interne (100) et le deuxième plan (120) est défini par les surfaces de positionnement externe et interne (102, 100) adjacentes aux goupilles de positionnement interne et externe correspondantes (98, 94).
  14. Pièce fixe selon l'une quelconque des revendications 10 à 13, dans laquelle les goupilles de positionnement radial (140) comprennent une surface de positionnement transversale par rapport au premier plan (118).
EP13796412.8A 2012-05-30 2013-05-08 Dispositif d'assemblage pour un ensemble aube de stator Active EP2859189B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/483,501 US8966755B2 (en) 2011-01-20 2012-05-30 Assembly fixture for a stator vane assembly
PCT/US2013/040042 WO2013180916A1 (fr) 2012-05-30 2013-05-08 Dispositif d'assemblage pour un ensemble aube de stator

Publications (3)

Publication Number Publication Date
EP2859189A1 EP2859189A1 (fr) 2015-04-15
EP2859189A4 EP2859189A4 (fr) 2016-08-24
EP2859189B1 true EP2859189B1 (fr) 2017-12-27

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Application Number Title Priority Date Filing Date
EP13796412.8A Active EP2859189B1 (fr) 2012-05-30 2013-05-08 Dispositif d'assemblage pour un ensemble aube de stator

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EP (1) EP2859189B1 (fr)
WO (1) WO2013180916A1 (fr)

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US6164903A (en) * 1998-12-22 2000-12-26 United Technologies Corporation Turbine vane mounting arrangement
US6343912B1 (en) * 1999-12-07 2002-02-05 General Electric Company Gas turbine or jet engine stator vane frame
GB2427900B (en) * 2005-07-02 2007-10-10 Rolls Royce Plc Vane support in a gas turbine engine
US7178255B1 (en) * 2005-09-09 2007-02-20 General Electric Company Methods and apparatus for manufacturing components
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Publication number Publication date
EP2859189A1 (fr) 2015-04-15
EP2859189A4 (fr) 2016-08-24
WO2013180916A1 (fr) 2013-12-05

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