US20060067817A1 - Damped assembly - Google Patents

Damped assembly Download PDF

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Publication number
US20060067817A1
US20060067817A1 US11/232,992 US23299205A US2006067817A1 US 20060067817 A1 US20060067817 A1 US 20060067817A1 US 23299205 A US23299205 A US 23299205A US 2006067817 A1 US2006067817 A1 US 2006067817A1
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US
United States
Prior art keywords
collar
assembly
rubber
resilient material
plate
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.)
Abandoned
Application number
US11/232,992
Inventor
Andrew Motherwell
Mark Thomas
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Assigned to ROLLS-ROYCE PLC reassignment ROLLS-ROYCE PLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: THOMAS, MARK, MOTHERWELL, ANDREW
Publication of US20060067817A1 publication Critical patent/US20060067817A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • B64C11/08—Blade mountings for non-adjustable blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • B64C11/08—Blade mountings for non-adjustable blades
    • B64C11/12—Blade mountings for non-adjustable blades flexible
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/431—Rubber
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments

Definitions

  • the invention relates to a damped assembly.
  • nozzle guide vane assembly for a compressor or fan stage of a gas turbine engine in which the guide vanes are held in position in an annular ring by means of an intermediate damping medium.
  • a damped assembly comprising at least one member carried in a supporting structure by at least one end of the member located in a socket formed in the supporting structure with an intermediate collar of resilient material interposed therebetween.
  • FIG. 1 shows a nozzle guide vane assembly for a gas turbine engine in which the vanes are located using a resilient collar;
  • FIG. 2 shows a detailed view of the resilient collar of FIG. 1 ;
  • FIG. 3 shows a section through the collar seated in position over a vane in the assembly of FIG. 1 .
  • FIG. 1 of the drawings there is shown a segment 2 of an annular nozzle guide vane assembly for a gas turbine engine including at 4 two nozzle guide vanes.
  • the vanes 4 have a hollow interior cavity 6 and are mounted in a supporting structure comprising an annular, radially outer casing, a portion of which is shown at 8 , and a concentric inner ring, a portion of which is shown at 10 .
  • the overall assembly includes a multiplicity of the vanes 4 spaced apart equidistantly around the rings 8 and 10 .
  • an aperture 12 is formed in the outer ring 8 opposite a corresponding aperture 14 in the inner ring 10 , both apertures conforming to the cross section of the vanes 4 plus a small gap to receive a collar 16 .
  • a collar or boot 16 made of resilient material to the shape of the vane cross-section to form a socket into which one end of the vane 4 is received.
  • a collar or boot 16 of resilient material interposed between adjoining metal parts 8 and 4 , or 10 and 4 .
  • the rubber collars 16 act to damp relative movement of the metal parts.
  • Each of the collars 16 is formed in an aerofoil shape so that there is an aperture 17 through its middle through which access to the interior 6 of the aerofoil 4 is provided, for example for the passage of cooling air.
  • this drawback is solved by the arrangement illustrated in FIG. 2 in which the collar or boot 16 is modified by the addition of stiffening means.
  • this stiffening means is in the form of a thin metal plate 18 attached to an end face of the collar.
  • the collar 16 was stiffened by the addition of a metal plate 18 formed of 0.5 mm thick stainless steel bonded to an end surface 20 of the collar 16 .
  • the inner and outer peripheries of the plate 18 were formed in the outline shape of an aerofoil cross-section.
  • the dimensions of the aperture 22 , defined by the inner periphery of the plate 18 were slightly larger than the corresponding external dimensions of the aerofoil vane 4 and of the end face 20 of the collar 16 .
  • the external dimensions of the plate 18 were slightly smaller than the corresponding dimensions of the collar face 20 .
  • the plate 18 was then bonded to the end surface 20 of the collar 16 in a position to leave a small clearance gap all round the aerofoil 4 after assembly.
  • the plate 18 was bonded to the collar 16 during a vulcanisation process to cure the silicone rubber material from which it was moulded.
  • the plate 18 was coated with a suitable primer and placed in the mould (not shown) on the uncured silicone rubber.
  • the stiffening plate 18 and the collar 16 were bonded together well enough to survive intact the mechanical stresses of assembly and use in which the assembly is subject to thermal cycles and simultaneous mechanical stresses.
  • the stiffness of this collar assembly 16 , 18 is influenced by several factors, including thickness of the plate 18 , the plate material and the width of overlap with the end face 20 of the rubber collar. These variables may be selected to produce a desired stiffness in the final assembly.
  • the in-plane and bending stiffness of the assembly will be increased by the high in-plane stiffness of the plate 18 . Therefore the stiffness of the assembly can be determined by selection of the plate material ie its modulus, thickness and width.
  • the transverse stiffness of the collar assembly is also influenced by all the above factors but is primarily determined by the width of plate overlap, or rather by the clearance between the plate 18 and the vane 4 . Lack of clearance acts to constrain local shear deformation of the rubber collar material adjacent to the vane surface ie reducing the width of overlap reduces the transverse stiffness of the collar 16 .
  • the plate 18 was bonded to one end surface 20 of the collar 16 .
  • the stiffening means ie the plate 18 and the collar 16 were formed as a unitary member.
  • the plate 18 was primed on both sides, and was placed in the mould when only partially filled with uncured silicone rubber, so that when filling was complete the plate 18 was fully embedded in the collar 16 with rubber on both sides. The vulcanisation procedure was then carried out as normal.
  • the inherent properties of the rubber material from which the collar was moulded were modified by inclusions within the body of the silicone rubber.
  • stiffening materials used are chopped fibres of carbon, glass, and Kevlar (p-phenylene terphthalamide) (Kevlar is a registered trade mark) or glass micro-spheres, ie minute (sub-millimetre) spheres of glass.
  • Kevlar p-phenylene terphthalamide
  • glass micro-spheres, ie minute (sub-millimetre) spheres of glass Such inclusions modify the way and degree to which the rubber deforms when subject to external mechanical stress.
  • Such modified material may be used in addition to a stiffening plate as described above or as an alternative thereto.
  • the thickness and length of the fibres used is dependent upon the design of the rubber boot, the inherent properties of the basic rubber material and the degree of modification of the resilient properties desired.

Abstract

In a nozzle guide vane assembly for a compressor or fan stage of a gas turbine engine each of the guide vanes is held in position between an outer casing and an annular inner ring by means of a rubber boot or collar at each end of the vane. Operational experience has shown potential for these assemblies to resonate within the engine, the cause of which is traced to the stiffness of the rubber collar. The present invention proposes as a solution a modified form of collar in which a stiffening plate is either bonded to the surface of the rubber or is incorporated into the construction during the rubber vulcanisation process. Alternatively or in addition the properties of the material from which the boots are moulded may be modified by the inclusion of chopped fibres of a range of materials.

Description

  • The invention relates to a damped assembly.
  • In particular it concerns a nozzle guide vane assembly for a compressor or fan stage of a gas turbine engine in which the guide vanes are held in position in an annular ring by means of an intermediate damping medium.
  • In known nozzle guide vane assemblies individual vanes are held in place between concentric rings by means of inserts of a resilient material such as silicone rubber material. The inserts of resilient material contribute some damping to the assembly as a result of its inherent energy absorbing properties. However, such an arrangement suffers the drawback that the due to the nature of the resilient material the overall assembly can have poor stiffness. This can lead to movement of the vanes relative to their supporting structure allowing vibration and resonant frequencies within the engine running range. This is generally undesirable and in the extreme can lead to structural failure. The invention is intended to overcome this drawback.
  • According to the broadest aspect of the invention there is provided a damped assembly comprising at least one member carried in a supporting structure by at least one end of the member located in a socket formed in the supporting structure with an intermediate collar of resilient material interposed therebetween.
  • The invention and how it may be carried into practice will now described by way of example with reference to the accompanying drawing in which:
  • FIG. 1 shows a nozzle guide vane assembly for a gas turbine engine in which the vanes are located using a resilient collar;
  • FIG. 2 shows a detailed view of the resilient collar of FIG. 1; and
  • FIG. 3 shows a section through the collar seated in position over a vane in the assembly of FIG. 1.
  • Referring firstly to FIG. 1 of the drawings there is shown a segment 2 of an annular nozzle guide vane assembly for a gas turbine engine including at 4 two nozzle guide vanes. The vanes 4 have a hollow interior cavity 6 and are mounted in a supporting structure comprising an annular, radially outer casing, a portion of which is shown at 8, and a concentric inner ring, a portion of which is shown at 10. The overall assembly includes a multiplicity of the vanes 4 spaced apart equidistantly around the rings 8 and 10.
  • At each of the vane locations an aperture 12 is formed in the outer ring 8 opposite a corresponding aperture 14 in the inner ring 10, both apertures conforming to the cross section of the vanes 4 plus a small gap to receive a collar 16. Into each said aperture there is fitted a collar or boot 16 made of resilient material to the shape of the vane cross-section to form a socket into which one end of the vane 4 is received. Thus, there is a collar or boot 16 of resilient material interposed between adjoining metal parts 8 and 4, or 10 and 4. In engine operation, the rubber collars 16 act to damp relative movement of the metal parts. Each of the collars 16 is formed in an aerofoil shape so that there is an aperture 17 through its middle through which access to the interior 6 of the aerofoil 4 is provided, for example for the passage of cooling air.
  • Experience in the gas turbine environment has shown that due to the nature of the resilient material the overall system has relatively poor stiffness. This can result in increased axial deflection of the inner ring 10 if the whole assembly is supported by means of cantilevered mounting of the outer casing annulus 8. The extent to which the modal vibration frequencies of the aerofoils can be tuned, to avoid resonances in the engine running range, is limited by the resilient material of which the collars or boots 16 are made.
  • According to the present invention this drawback is solved by the arrangement illustrated in FIG. 2 in which the collar or boot 16 is modified by the addition of stiffening means. In one embodiment of the invention this stiffening means is in the form of a thin metal plate 18 attached to an end face of the collar. In this example the collar 16 was stiffened by the addition of a metal plate 18 formed of 0.5 mm thick stainless steel bonded to an end surface 20 of the collar 16. The inner and outer peripheries of the plate 18 were formed in the outline shape of an aerofoil cross-section. The dimensions of the aperture 22, defined by the inner periphery of the plate 18 were slightly larger than the corresponding external dimensions of the aerofoil vane 4 and of the end face 20 of the collar 16. Also the external dimensions of the plate 18 were slightly smaller than the corresponding dimensions of the collar face 20. The plate 18 was then bonded to the end surface 20 of the collar 16 in a position to leave a small clearance gap all round the aerofoil 4 after assembly.
  • The plate 18 was bonded to the collar 16 during a vulcanisation process to cure the silicone rubber material from which it was moulded. The plate 18 was coated with a suitable primer and placed in the mould (not shown) on the uncured silicone rubber. Upon completion of the curing process the stiffening plate 18 and the collar 16 were bonded together well enough to survive intact the mechanical stresses of assembly and use in which the assembly is subject to thermal cycles and simultaneous mechanical stresses.
  • The stiffness of this collar assembly 16, 18 is influenced by several factors, including thickness of the plate 18, the plate material and the width of overlap with the end face 20 of the rubber collar. These variables may be selected to produce a desired stiffness in the final assembly. The in-plane and bending stiffness of the assembly will be increased by the high in-plane stiffness of the plate 18. Therefore the stiffness of the assembly can be determined by selection of the plate material ie its modulus, thickness and width. The transverse stiffness of the collar assembly is also influenced by all the above factors but is primarily determined by the width of plate overlap, or rather by the clearance between the plate 18 and the vane 4. Lack of clearance acts to constrain local shear deformation of the rubber collar material adjacent to the vane surface ie reducing the width of overlap reduces the transverse stiffness of the collar 16.
  • In the case of the illustrated example the plate 18 was bonded to one end surface 20 of the collar 16. In another example (not shown) the stiffening means, ie the plate 18 and the collar 16 were formed as a unitary member. The plate 18, was primed on both sides, and was placed in the mould when only partially filled with uncured silicone rubber, so that when filling was complete the plate 18 was fully embedded in the collar 16 with rubber on both sides. The vulcanisation procedure was then carried out as normal.
  • In further embodiments the inherent properties of the rubber material from which the collar was moulded were modified by inclusions within the body of the silicone rubber. Examples of stiffening materials used are chopped fibres of carbon, glass, and Kevlar (p-phenylene terphthalamide) (Kevlar is a registered trade mark) or glass micro-spheres, ie minute (sub-millimetre) spheres of glass. Such inclusions modify the way and degree to which the rubber deforms when subject to external mechanical stress. Such modified material may be used in addition to a stiffening plate as described above or as an alternative thereto. The thickness and length of the fibres used is dependent upon the design of the rubber boot, the inherent properties of the basic rubber material and the degree of modification of the resilient properties desired.

Claims (6)

1. A damped assembly comprising at least one member carried in a supporting structure by at least one end of the member located in a socket formed in the supporting structure with an intermediate collar of resilient material interposed therebetween wherein the collar of resilient material includes stiffening means.
2. A damped assembly as claimed in claim 1 wherein the stiffening means includes a metal plate.
3. A damped assembly as claimed in claim 2 wherein the metal plate is bonded to a surface of the collar.
4. A damped assembly as claimed in claim 2 wherein the stiffening means and the collar are formed as a unitary member.
5. A damped assembly as claimed in claim 1 wherein the properties of the resilient material of which the intermediate collar is comprised are modified by the inclusion of a further material to increase the stiffness of the resilient material.
6. A damped assembly as claimed in claim 5 wherein the further material is selected from the group of materials including carbon fibre, glass fibre Kevlar fibre and glass micro-spheres.
US11/232,992 2004-09-29 2005-09-23 Damped assembly Abandoned US20060067817A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0421588A GB2418709B (en) 2004-09-29 2004-09-29 Damped assembly
GB0421588.5 2004-09-29

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2950116A1 (en) * 2009-09-15 2011-03-18 Snecma Rectifier stage for use in high pressure compressor of e.g. turbojet engine of aircraft, has fixation unit fixing blade tip in mortise of outer shell, where fixation unit is in form of seal made of vibration damping material
US20130189110A1 (en) * 2010-09-29 2013-07-25 Stephen Batt Turbine arrangement and gas turbine engine
US20130251517A1 (en) * 2012-03-23 2013-09-26 Richard Ivakitch Grommet for gas turbine vane
US20140356158A1 (en) * 2013-05-28 2014-12-04 Pratt & Whitney Canada Corp. Gas turbine engine vane assembly and method of mounting same
US20190257214A1 (en) * 2018-02-19 2019-08-22 Pratt & Whitney Canada Corp. Seal and bearing assembly with bearing outer portion defining seal static portion
US11326461B2 (en) * 2019-09-16 2022-05-10 Raytheon Technologies Corporation Hybrid rubber grommet for potted stator

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2075415B1 (en) * 2007-12-27 2016-10-19 Techspace Aero Lightened annular stator structure for aircraft turboshaft engine
EP2075414A1 (en) * 2007-12-27 2009-07-01 Techspace aero Internal collar of a stator for delimiting a primary flow of an aircraft turboshaft engine
GB0905729D0 (en) 2009-04-03 2009-05-20 Rolls Royce Plc Stator vane assembly
GB201015862D0 (en) 2010-09-22 2010-10-27 Rolls Royce Plc A damped assembly
GB2490858B (en) * 2011-03-22 2014-01-01 Rolls Royce Plc A bladed rotor
FR2989130B1 (en) * 2012-04-05 2014-03-28 Snecma COMPRESSOR RECTIFIER STAGE FOR A TURBOMACHINE
BE1023134B1 (en) * 2015-05-27 2016-11-29 Techspace Aero S.A. DAWN AND VIROLE WITH COMPRESSOR OF AXIAL TURBOMACHINE COMPRESSOR
FR3074219B1 (en) * 2017-11-30 2019-10-25 Safran Aircraft Engines TURBOMACHINE ASSEMBLY WITH AN INTEGRATED PLATFORM STEERING VANE AND MEANS FOR MAINTAINING.

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US2430709A (en) * 1942-09-02 1947-11-11 Us Rubber Co Resilient mounting
US4486183A (en) * 1980-06-30 1984-12-04 The Gates Rubber Company Torsionally elastic power transmitting device and drive
US4734600A (en) * 1985-12-10 1988-03-29 Robert Bosch Gmbh Noise damped dynamo electric machine, especially vehicular type alternator
US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
US6151216A (en) * 1997-12-04 2000-11-21 Lockheed Martin Corporation Thermally conductive vibration isolators
US20020076320A1 (en) * 2000-12-19 2002-06-20 Glover Samuel L. Machined fan exit guide vane attachment pockets for use in a gas turbine
US7311495B2 (en) * 2005-07-02 2007-12-25 Rolls-Royce Plc Vane support in a gas turbine engine

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US5110260A (en) * 1990-12-17 1992-05-05 United Technologies Corporation Articulated helicopter rotor within an improved blade-to-hub connection
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Publication number Priority date Publication date Assignee Title
US2430709A (en) * 1942-09-02 1947-11-11 Us Rubber Co Resilient mounting
US2425566A (en) * 1945-12-15 1947-08-12 Cecil S Robinson Vibration absorption block
US4486183A (en) * 1980-06-30 1984-12-04 The Gates Rubber Company Torsionally elastic power transmitting device and drive
US4734600A (en) * 1985-12-10 1988-03-29 Robert Bosch Gmbh Noise damped dynamo electric machine, especially vehicular type alternator
US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
US6151216A (en) * 1997-12-04 2000-11-21 Lockheed Martin Corporation Thermally conductive vibration isolators
US20020076320A1 (en) * 2000-12-19 2002-06-20 Glover Samuel L. Machined fan exit guide vane attachment pockets for use in a gas turbine
US20040033137A1 (en) * 2000-12-19 2004-02-19 Glover Samuel L. Machined fan exit guide vane attachment pockets for use in a gas turbine
US7311495B2 (en) * 2005-07-02 2007-12-25 Rolls-Royce Plc Vane support in a gas turbine engine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2950116A1 (en) * 2009-09-15 2011-03-18 Snecma Rectifier stage for use in high pressure compressor of e.g. turbojet engine of aircraft, has fixation unit fixing blade tip in mortise of outer shell, where fixation unit is in form of seal made of vibration damping material
US20130189110A1 (en) * 2010-09-29 2013-07-25 Stephen Batt Turbine arrangement and gas turbine engine
US9238969B2 (en) * 2010-09-29 2016-01-19 Siemens Aktiengesellschaft Turbine assembly and gas turbine engine
US20130251517A1 (en) * 2012-03-23 2013-09-26 Richard Ivakitch Grommet for gas turbine vane
US9109448B2 (en) * 2012-03-23 2015-08-18 Pratt & Whitney Canada Corp. Grommet for gas turbine vane
US20140356158A1 (en) * 2013-05-28 2014-12-04 Pratt & Whitney Canada Corp. Gas turbine engine vane assembly and method of mounting same
US9840929B2 (en) * 2013-05-28 2017-12-12 Pratt & Whitney Canada Corp. Gas turbine engine vane assembly and method of mounting same
US20190257214A1 (en) * 2018-02-19 2019-08-22 Pratt & Whitney Canada Corp. Seal and bearing assembly with bearing outer portion defining seal static portion
US11085330B2 (en) * 2018-02-19 2021-08-10 Pratt & Whitney Canada Corp. Seal and bearing assembly with bearing outer portion defining seal static portion
US11326461B2 (en) * 2019-09-16 2022-05-10 Raytheon Technologies Corporation Hybrid rubber grommet for potted stator

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GB2418709A (en) 2006-04-05
GB0421588D0 (en) 2004-10-27
GB2418709B (en) 2007-10-10

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