EP2859189B1 - Assembly fixture for a stator vane assembly - Google Patents
Assembly fixture for a stator vane assembly Download PDFInfo
- 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.)
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Links
- 238000000034 method Methods 0.000 claims description 17
- 239000000463 material Substances 0.000 claims description 7
- 239000000565 sealant Substances 0.000 description 12
- 239000000446 fuel Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004382 potting Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 239000012812 sealant material Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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.
Description
- 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, and 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.
- Accordingly, it is desirable to design and develop assembly techniques and devices that simplify and speed assembly.
-
EP 2, 312, 186 A1 andCA 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. - According to a first aspect of the present invention, there is provided a method of assembling a gas turbine engine front architecture according claim 1.
- 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.
- A further embodiment of any of the foregoing methods, wherein 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 further embodiment of any of the foregoing methods, wherein the plurality of vanes are held within the fixture during curing of the curable material.
- According to a second aspect of the present invention, there is provided a fixture for assembling a stator vane assembly for a gas turbine engine according to
claim 9. - An embodiment of the foregoing fixture, wherein 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.
- A further embodiment of any of the foregoing fixtures, wherein the outer locator pin on the outer locating ring of the fixture, the inner locator pin on the inner locating ring and the clamp pin define the first plane.
- A further embodiment of any of the foregoing fixtures, wherein the 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.
- A further embodiment of any of the foregoing fixtures, wherein the 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.
- A further embodiment of any of the foregoing fixtures, wherein the radial locating pins include a locating surface transverse to the first plane.
- Although the different examples have the specific components shown in the illustrations, embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples.
- These and other features disclosed herein can be best understood from the following specification and drawings, the following of which is a brief description.
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Figure 1 is a schematic view of an example gas turbine engine. -
Figure 2 is a perspective view of an example stator vane assembly. -
Figure 3 is a partial schematic view of vanes for the example stator vane assembly. -
Figure 4 is a perspective view of a top portion of the example stator vane assembly. -
Figure 5 is a bottom view of the example stator vane assembly. -
Figure 6 is a top view of a fixture for assembling a stator vane assembly. -
Figure 7 is a perspective view of an outer portion of the example stator fixture for assembling a stator vane assembly. -
Figure 8a is a schematic view of the datum planes established by the example fixture assembly. -
Figure 8b is a schematic representation of a datum plane established by the example fixture assembly. -
Figure 9 is an enlarged view of datum planes defined by an outer locating ring. -
Figure 10 is an enlarged view of data points defined by an example outer locating ring. -
Figure 11 is an enlarged view of a datum point established by an example clamping section. -
Figure 12 is a perspective view showing the establishment of another datum point defining a desired datum plane. -
Figure 1 schematically illustrates an examplegas turbine engine 20 that includes afan section 22, acompressor section 24, acombustor section 26 and aturbine section 28. Alternative engines might include an augmenter section (not shown) among other systems or features. Thefan section 22 drives air along a bypass flow path B while thecompressor section 24 draws air in along a core flow path C where air is compressed and communicated to acombustor section 26. In thecombustor section 26, air is mixed with fuel and ignited to generate a high pressure exhaust gas stream that expands through theturbine section 28 where energy is extracted and utilized to drive thefan section 22 and thecompressor section 24. - Although the disclosed non-limiting embodiment depicts a turbofan gas turbine engine, it should be understood that 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 alow speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an enginestatic structure 36 viaseveral bearing systems 38. It should be understood thatvarious bearing systems 38 at various locations may alternatively or additionally be provided. - The
low speed spool 30 generally includes aninner shaft 40 that connects afan 42 and a low pressure (or first)compressor section 44 to a low pressure (or first)turbine section 46. Theinner shaft 40 drives thefan 42 through a speed change device, such as a gearedarchitecture 48, to drive thefan 42 at a lower speed than thelow speed spool 30. The high-speed spool 32 includes anouter shaft 50 that interconnects a high pressure (or second)compressor section 52 and a high pressure (or second)turbine section 54. Theinner shaft 40 and theouter shaft 50 are concentric and rotate via thebearing systems 38 about the engine central longitudinal axis A. - The example
gas turbine engine 20 includes afront architecture 62 that includes a plurality ofstator vanes 64. The plurality ofstator vanes 64 are disposed aft of thefan section 22 andfan blades 42 at the inlet for core air flow C. The plurality ofstator vanes 64 are disposed forward of a plurality ofinlet guide vanes 66 that are disposed prior to alow pressure compressor 44. The plurality ofstator vanes 64 are arranged circumferentially about the engine axis A within the inlet for core engine flow C. - Referring to the
Figure 2 , thestator vanes 64 are part of astator vane assembly 68 that includes anouter fairing 70 and aninner fairing 72. The plurality of stator vanes 64 extend between theinner fairing 72 and theouter fairing 70. - Referring to
Figures 3, 4, and 5 with continued reference toFigure 2 , thestator vanes 64 are supported within openings orslots 74 defined within each of the inner andouter fairings stator vanes 64 includes aninner end 80, anouter end 82, a leadingedge 84 and atrailing edge 86. Each of thestator vanes 64 are supported within theopenings 74 by asealant 76. Theexample sealant 76 is a curable material that remains flexible once cured. The stator vanes 64 are mounted within theopenings 74 by way of thecurable sealant material 76. - The
sealant 76 provides a bonded joint between the inner andouter fairings vanes 64 and thecorresponding slot 74 to vibrationally isolate the outer andinner fairings - Each of the
stator vanes 64 includetabs 78 that secured thevane 64 within theouter fairing 70 and prevents it from sliding through theopening 74. However, it is thesealant 76 that provides the joint that maintains each of thevanes 64 in a desired position relative to theother vanes 64 and each of the outer andinner fairings stator vane assembly 68 requires specific positioning of each of thevanes 64 within correspondingopenings 74. Positioning within theopenings 74 is provided such that thevanes 64 themselves do not engage the outer andinner fairings stator vanes 64 and the outer andinner fairings sealant 76 is applied and cured to form the completedstator vane assembly 68. - Referring to
Figures 6 and7 , an example disclosedassembly fixture 88 includes a base 90 that supports theouter fairing 70 and theinner fairing 72 along with the plurality ofstator vanes 64 in a desired position for assembly including the application and curing of the sealant 76 (Figures 4 and 5 ). Theexample assembly fixture 88 defines the specific datum planes and points required to properly align each of the plurality ofvanes 64 relative to adjacent vanes and the outer and inner andfairings - The
example fixture assembly 88 includes the base 90 that holdsclamps 114 that are provided to hold theouter fairing 70 in place. The base 90 also includespins 124 that align with openings within the fairing 70 to align theouter fairing 70. - An
outer locating ring 92 includes a plurality of locatingpins 94 disposed radially inward of the mountedouter fairing 70. Aninner locating ring 96 is disposed radially inward of theouter locating ring 92 and includesinner locating pin 98. Aclamp section 104 is disposed between the inner and outer locating rings 96, 92 and includes aclamp portion 106 supported on aclamp pin 108. - The
inner fairing 72 is supported on an inner portion of thebase 90 and held in place byinner clamps 116. Similarly, theouter fairing 70 is held in place byouter clamps 114. Theinner locating ring 96 and theouter locating ring 92 includessurfaces vane 64 within theopenings 74. - Referring to
Figures 8a and 8b , with continued reference toFigures 6 and7 , the inner and outer locating rings 96, 92 along within theclamp section 104 define three datum planes for eachvane 64 relative to the outer andinner fairings Figures 8a and 8b are schematic representations illustrating the planes utilized to align thevanes 64 relative to thefairings - In this example, a
first plane 118 is defined along a surface of thevane 64 that is transverse to a surface of thebase 90. A second plane 120 (Figure 8B ) is defined along thebase 90 and along thesurfaces third datum plane 122 is defined at the radially inner most position and sets a radial position of thevane 64. - The
first plane 118 is defined by theinner locating pin 98, theouter locating pin 94 and aclamp post 108. Each of theinner pin 98, theouter pin 94, and theclamp post 108 defines a point along thefirst plane 118. In this example, theinner locating pin 98 defines apoint 128. Theouter locating pin 94 defines anotherpoint 130 between thepin 94 and thevane 64. Theclamp post 108 defines athird locating point 132 between thepost 108 and thevane 64. - The second plane 120 (
Figure 8b ) is defined by thesurface 100 of theouter locating ring 92 and thesurface 102 of theinner locating ring 92. Thesurfaces pin plane 122 is defined by theradial pin 140 that abuts theinner end 80 of thevane 64. - Referring to
Figure 9 , with continued reference toFigures 8a and 8b , theexample fixture 88 includes theinner locating ring 96 that includes thesurface 102 and the locatingpin 98. Thesurface 102 defines the locating point 134 for thesecond plane 120. The locatingpin 98 defines thefirst point 128 along theplane 118. Thevane 64 is abutted against thepin 98 and thebottom surface 102 to set one point along thefirst plane 118 and thesecond plane 120. - Referring to
Figure 10 with continued reference toFigures 8a and 8b , theouter locating ring 92 includes thesurface 100 and the locatingpin 94. Thevane 64 is abutted against thesurface 100 and thepin 94. Thepin 94 defines thelocating point 130 that is a second point along theplane 118. Theouter ring surface 100 defines anotherpoint 136 that defines a second point along theplane 120. - Referring to
Figure 11 , with continued reference toFigures 8a and 8b , a third point along theplane 118 is defined by theclamp post 108. Theexample clamp section 104 includes theclamp post 108 that extends upwardly from thebase 90. Theexample clamp post 108 includes apoint 132 onto which thevane 64 comes into contact. Theexample point 132 defines a third point along theplane 118. Accordingly, theexample vane 64 abuts theouter locating pin 94, theinner locating pin 98, and theclamp pin 108 to define thefirst plane 118. As appreciated, thefirst plane 118 includes a specific orientation of thevane 64 that corresponds with the aerodynamic shape of thevane 64. Theclamp section 104 holds and defines an angular orientation of each of the plurality ofvanes 64 relative to each of the outer and inner fairings70, 72. - The
clamp post 108 that supports a surface of thevane 64 and also aclamp portion 106 including aclamp surface 112 that engages an opposite end of thevane 64 and is utilized to hold thevane 64 in contact with theclamp post 108 and the locating pins 94 and 98. - Referring to
Figure 12 , with continued reference toFigures 8a and 8b , the radial location of each of thevanes 64 is defined by radial locating pins 140 within theradial positioning section 142. Aninner end 80 of each of thevanes 64 engages the surface of each of the corresponding radial locator pins 140 to define and set a desired radial position of each of thevanes 64 in relation to the corresponding outer andinner fairings -
Figure 12 further shows a top view of theclamp section 104 where theclamp portions 106 are held to acorresponding clamp post 108 by aclamp fastener 110. Each of theclamp fasteners 110 provides for securement of the correspondingvane 64 independent of theother vanes 64. - In operation, the
example fixture 88 is utilized to define the relative position between the outer andinner fairings sealant 76. Theindividual vanes 64 are inserted into thefixture 88 after the corresponding outer andinner fairings base plate 90. The outer and inner andouter fairings base plate 90 utilizing the locating pins 124 and 126. - The
outer fairing 70 is then secured utilizing theouter clamp 114 and theinner fairing 72 is secured theinner clamp 116. With the inner andouter fairings vanes 64 is inserted into thefixture 88. Thevanes 64 are inserted through theopening 74 within theouter fairing 70 radially inward until abutting theradial locating pin 40. Once thevanes 64 are inserted and abutted against theradial locating pin 140, theclamp portion 106 of theclamp section 104 is secured to bias and hold thevane 64 against the locating pins 98 and 94 on corresponding inner and outer locating rings 92, 96. Theclamp portion 106 also secures and holds thevane assembly 64 against the corresponding inner locatingring surface 100 and outer locatingsurface 102. - With each of the
vanes 64 held in a desired position relative to the corresponding outer andinner fairings sealant 76 can be applied to the gaps between each of thevanes 64 and the correspondingfairings 70. 72. Thesealant 76 is applied within the gap to secure thevane 64 within the outer andinner fairings - The
example fixture 88 is comprised of a material compatible with the conditions utilized for curing thesealant 76 within theopenings 74. Once thesealant 76 has properly cured thestator vane assembly 68 can be removed from thefixture 88. Removal of the vane assembly from the fixture includes removal of theclamp portions 106 from theclamp section 104. Once theclamp portions 106 are removed, theouter clamps 114 and theinner clamps 116 can be removed to allow the completedstator vane assembly 68 to be lifted upwardly off of thebase plate 90. - Accordingly, the
example fixture 88 provides for the specific positioning of each of a plurality ofvanes 64 relative to the outer andinner fairings sealant 76 can be applied to hold each of thevanes 64 within the assembly. Further, theexample fixture 88 defines the specific datum points and planes that are utilized to align each of thevanes 64 relative toadjacent vanes 64 and the outer andinner fairings - Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. For that reason, the following claims should be studied to determine the scope and content of this disclosure.
Claims (14)
- A method of assembling a gas turbine engine (20) front architecture comprising the steps of:securing inner and outer fairings (72, 70) within a fixture (88) relative to one another;positioning each of the multiple vanes (64) within an opening (74) of each of the inner and outer fairings (72, 70), such that the multiple vanes (64) do not engage the outer or inner fairings (72, 70);securing multiple vanes (64) between the inner and outer fairing (72, 70) within the fixture;applying a curable material at an interface between each of the multiple vanes (64) and the inner and outer fairings (72, 70);curing the curable material while maintaining a relative position between the multiple vanes (64) and the inner and outer fairings (72; 70); wherein the curable material remains flexible once cured;and releasing the multiple vanes (64) and the inner and outer fairings (72; 70) from the fixture (88).
- The method as recited in claim 1, including positioning each of the multiple vanes (64) by defining a first plane (118) with at least three contact points (128, 130, 132) on the fixture (88), a second plane (120) with at least two contact points (134, 136) on the fixture and a third plane (122) with at least one contact point defined on the fixture (88).
- The method as recited in claim 2, including defining the first plane (118) with an outer locator pin (94) on an outer locating ring (92) of the fixture, an inner locator pin (98) on an inner locating ring (96) and a clamp (104) disposed between the inner and outer locating rings (96, 92).
- The method as recited in claim 3, including a single clamp (104) for holding each of the vanes (64) in position.
- The method as recited in claim 4, wherein the single clamp (104) is disposed between the inner locating pin (98) and the outer locating pin (94) and includes a clamp portion (106) supported on a clamp pin (108) with the vane (64) being clamped between the clamp portion (106) and the clamp pin (108).
- The method as recited in any of claims 2 to 5, including defining the second plane (120) with a surface (102, 100) of an outer locating ring (92) and an inner locating ring (96).
- The method as recited in any of claims 2 to 6, including defining the third plane (122) with a radial locating pin (140) supported radially inward of the inner fairing (72).
- The method as recited in any preceding claim, wherein the plurality of vanes (64) are held within the fixture (88) during curing of the curable material.
- A fixture (88) for assembling a stator vane assembly (68) for a gas turbine engine (20) comprising:an outer fairing (70); andan inner fairing (72); characterised byan outer locating ring (92) including a plurality of outer locating pins (94) defining a position for each of a plurality of vanes (64) relative to the outer fairing (70);an inner locating ring (96) including a plurality of inner locating pins (98) defining a position of each of the plurality of vanes (64) relative to the inner fairing (72);a clamp section (104) including a clamp portion (106) and a clamp pin (108) defining an angular orientation of each of the plurality of vanes (64) relative to each of the inner and outer fairings (72, 70); andan inner locating section (142) supporting a plurality of radial locating pins (140) defining a radial position of each of the plurality of vanes (64) relative to the inner and outer fairings (72, 70).
- The fixture as recited in claim 9, wherein the fixture defines a first plane (118) with at least three contact points (128, 130, 132), a second plane (120) with at least two contact points (134, 136) and a third plane (122) with at least one contact point.
- The fixture as recited in claim 10, wherein the outer locator pin (94) on the outer locating ring (92) of the fixture, the inner locator pin (98) on the inner locating ring (96) and the clamp pin (108) define the first plane (118).
- The fixture as recited in claim 10 or 11, wherein the clamp portion (104) is supported on the clamp pin (108) and is configured to hold the vane (64) against the clamp pin (108), the inner locating pin (98) and the outer locating pin (94), and optionally wherein the fixture includes a fastener (110) for applying a desired pressure to a corresponding one of the plurality of vanes (64) for holding the vane (64) within the defined first, second and third planes (118, 120, 122).
- The fixture as recited in claim 11 or 12, wherein the outer locating pin (94) extends transversely from an outer locating surface (102) and the inner locating pin (98) extends transversely from an inner locating surface (100) and the second plane (120) is defined by the outer and inner locating surfaces (102, 100) adjacent the corresponding inner and outer locating pins (98, 94).
- The fixture as recited in any of claims 10 to 13, wherein the radial locating pins (140) include a locating surface transverse to the first plane (118).
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 (en) | 2012-05-30 | 2013-05-08 | Assembly fixture for a stator vane assembly |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2859189A1 EP2859189A1 (en) | 2015-04-15 |
EP2859189A4 EP2859189A4 (en) | 2016-08-24 |
EP2859189B1 true EP2859189B1 (en) | 2017-12-27 |
Family
ID=49673815
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13796412.8A Active EP2859189B1 (en) | 2012-05-30 | 2013-05-08 | Assembly fixture for a stator vane assembly |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP2859189B1 (en) |
WO (1) | WO2013180916A1 (en) |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2728016B1 (en) * | 1994-12-07 | 1997-01-17 | Snecma | NON-SECTORIZED MONOBLOCK DISTRIBUTOR OF A TURBOMACHINE TURBINE STATOR |
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 |
US8092157B2 (en) * | 2007-12-19 | 2012-01-10 | United Technologies Corporation | Variable turbine vane actuation mechanism having a bumper ring |
US8511983B2 (en) * | 2008-02-19 | 2013-08-20 | United Technologies Corporation | LPC exit guide vane and assembly |
CA2682818A1 (en) * | 2009-10-15 | 2011-04-15 | General Electric Company | Method of manufacturing a fairing with an integrated seal |
EP2312186A1 (en) * | 2009-10-16 | 2011-04-20 | General Electric Company | Method of manufacturing a fairing with an integrated seal |
US8533947B2 (en) * | 2010-10-28 | 2013-09-17 | Pcc Airfoils, Inc. | Method of forming a turbine engine component |
US8668448B2 (en) * | 2010-10-29 | 2014-03-11 | United Technologies Corporation | Airfoil attachment arrangement |
-
2013
- 2013-05-08 EP EP13796412.8A patent/EP2859189B1/en active Active
- 2013-05-08 WO PCT/US2013/040042 patent/WO2013180916A1/en unknown
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
EP2859189A1 (en) | 2015-04-15 |
EP2859189A4 (en) | 2016-08-24 |
WO2013180916A1 (en) | 2013-12-05 |
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