GB2418709A - Damped assembly - Google Patents
Damped assembly Download PDFInfo
- Publication number
- GB2418709A GB2418709A GB0421588A GB0421588A GB2418709A GB 2418709 A GB2418709 A GB 2418709A GB 0421588 A GB0421588 A GB 0421588A GB 0421588 A GB0421588 A GB 0421588A GB 2418709 A GB2418709 A GB 2418709A
- Authority
- GB
- United Kingdom
- Prior art keywords
- collar
- assembly
- damped
- damped assembly
- resilient material
- 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.)
- Granted
Links
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A member 4 (which may be a compressor or fan stage nozzle guide vane of a gas turbine engine) has an end located in a socket of a support member 8 (which may be a casing) with a collar 16 or resilient material (such as silicone rubber) interposed between the support member 8 and member 4. The collar may be stiffened by providing a metal plate 18, which may be bonded to the collar or embedded therein, and/or by incorporating fibres or microspheres within the resilient material. The member 4 may comprise a nozzle guide vane having ends supported respectively by inner and outer casings.
Description
241 8709
DAMPED ASSEMBI Y
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: Figure 1 shows a nozzle guide vane assembly for a gas turbine engine in which the vanes are located using a resilient collar, Figure 2 shows a detailed view of the resilient collar of Fig 1, and Figure 3 shows a section through the collar seated in position over a vane in the assembly of Fig 1.
Vlb/lVO4 1 46spec#2 - 2 Referring firstly to Figure 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 fonm a socket into which one end of the vane 4 is rece ved. 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 Figure 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 0,5mm thick Vb/lV04 1 46spec#2 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- sectlon. 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 vulcanization 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 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 i.e. 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 i.e. 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, i.e. the plate 18 and !;I'/04146spec#2 - 4 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 vulcanization 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, i.e. 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.
Vb/lV,4 1 46spec#2 - 5
Claims (9)
- CLAiMS 1 A damped assembly comprising at least one member carried in asupporting 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.
- 2 A damped assembly as claimed in claim 1 wherein the collar of resilient material includes stiffening means.
- 3 A damped assembly as claimed in claim 2 wherein the stiffening means includes a metal plate.
- 4 A damped assembly as claimed in claim 2 or claim 3 wherein the metal plate is bonded to a surface of the collar.
- A damped assembly as claimed in claim 2 or claim 3 wherein the stiffening means and the collar are formed as a unitary member.
- 6 A damped assembly as claimed in any preceding claim wherein the properties of the resilient material of which the intermediate collar is comprised are modified by the inclusion of a further material.
- 7 A damped assembly as claimed in claim 6 wherein the further material is selected from the group of materials including carbon fibre, glass fibre Kevlar fibre and glass micro-spheres.
- 8 A damped assembly as claimed in any preceding claim comprising a nozzle guide vane assembly for a gas turbine engine.
- 9 A damped assembly substantially as hereinbefore described with reference to and as illustrated in the accompanying drawings.yb/lV04146spec#2
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0421588A GB2418709B (en) | 2004-09-29 | 2004-09-29 | Damped assembly |
US11/232,992 US20060067817A1 (en) | 2004-09-29 | 2005-09-23 | Damped assembly |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0421588A GB2418709B (en) | 2004-09-29 | 2004-09-29 | Damped assembly |
Publications (3)
Publication Number | Publication Date |
---|---|
GB0421588D0 GB0421588D0 (en) | 2004-10-27 |
GB2418709A true GB2418709A (en) | 2006-04-05 |
GB2418709B GB2418709B (en) | 2007-10-10 |
Family
ID=33397419
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB0421588A Expired - Fee Related GB2418709B (en) | 2004-09-29 | 2004-09-29 | Damped assembly |
Country Status (2)
Country | Link |
---|---|
US (1) | US20060067817A1 (en) |
GB (1) | GB2418709B (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2075415A1 (en) * | 2007-12-27 | 2009-07-01 | 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 |
EP2434101A2 (en) | 2010-09-22 | 2012-03-28 | Rolls-Royce plc | A damped assembly |
GB2490858A (en) * | 2011-03-22 | 2012-11-21 | Rolls Royce Plc | Bladed rotor seal |
US8672623B2 (en) | 2009-04-03 | 2014-03-18 | Rolls-Royce Plc | Stator vane assembly |
US9879562B2 (en) | 2012-04-05 | 2018-01-30 | Snecma | Compressor guide-vane stage for a turbine engine including a gasket between a vane and a shroud of the guide-vane stage |
FR3074219A1 (en) * | 2017-11-30 | 2019-05-31 | Safran Aircraft Engines | TURBOMACHINE ASSEMBLY WITH AN INTEGRATED PLATFORM STEERING VANE AND MEANS FOR MAINTAINING. |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2950116B1 (en) * | 2009-09-15 | 2011-12-09 | Snecma | COMPRESSOR RECTIFIER FOR TURBOMACHINE, COMPRISING AUB HEADS MOUNTED USING A VIBRATION SHOCK ABSORBER MATERIAL ON THE EXTERNAL VIROLE |
EP2436884A1 (en) * | 2010-09-29 | 2012-04-04 | Siemens Aktiengesellschaft | Turbine arrangement and gas turbine engine |
US9109448B2 (en) * | 2012-03-23 | 2015-08-18 | Pratt & Whitney Canada Corp. | Grommet for gas turbine vane |
US9840929B2 (en) * | 2013-05-28 | 2017-12-12 | Pratt & Whitney Canada Corp. | Gas turbine engine vane assembly and method of mounting same |
BE1023134B1 (en) * | 2015-05-27 | 2016-11-29 | Techspace Aero S.A. | DAWN AND VIROLE WITH COMPRESSOR OF AXIAL TURBOMACHINE COMPRESSOR |
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 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB903792A (en) * | 1959-01-20 | 1962-08-22 | Sulzer Ag | Blade and blade mounting assemblies for axial flow turbines, compressors or pumps |
GB2115883A (en) * | 1982-02-26 | 1983-09-14 | Gen Electric | Turbomachine airfoil mounting assembly |
US4734600A (en) * | 1985-12-10 | 1988-03-29 | Robert Bosch Gmbh | Noise damped dynamo electric machine, especially vehicular type alternator |
EP0491648A1 (en) * | 1990-12-17 | 1992-06-24 | United Technologies Corporation | Articulated helicopter rotor with an improved blade-to-hub connection |
US20020076320A1 (en) * | 2000-12-19 | 2002-06-20 | Glover Samuel L. | Machined fan exit guide vane attachment pockets for use in a gas turbine |
Family Cites Families (7)
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 |
US5226789A (en) * | 1991-05-13 | 1993-07-13 | General Electric Company | Composite fan stator assembly |
DE9412946U1 (en) * | 1994-08-11 | 1995-12-07 | Bosch Gmbh Robert | Anti-vibration bushing |
US6002588A (en) * | 1997-12-04 | 1999-12-14 | Lockheed Martin Corporation | Thermally conductive vibration isolators |
GB2427900B (en) * | 2005-07-02 | 2007-10-10 | Rolls Royce Plc | Vane support in a gas turbine engine |
-
2004
- 2004-09-29 GB GB0421588A patent/GB2418709B/en not_active Expired - Fee Related
-
2005
- 2005-09-23 US US11/232,992 patent/US20060067817A1/en not_active Abandoned
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB903792A (en) * | 1959-01-20 | 1962-08-22 | Sulzer Ag | Blade and blade mounting assemblies for axial flow turbines, compressors or pumps |
GB2115883A (en) * | 1982-02-26 | 1983-09-14 | Gen Electric | Turbomachine airfoil mounting assembly |
US4734600A (en) * | 1985-12-10 | 1988-03-29 | Robert Bosch Gmbh | Noise damped dynamo electric machine, especially vehicular type alternator |
EP0491648A1 (en) * | 1990-12-17 | 1992-06-24 | United Technologies Corporation | Articulated helicopter rotor with an improved blade-to-hub connection |
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 |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2075415A1 (en) * | 2007-12-27 | 2009-07-01 | 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 |
WO2009083568A1 (en) * | 2007-12-27 | 2009-07-09 | Techspace Aero | Lightweight annular stator structure for an aircraft turbine engine |
WO2009083567A1 (en) * | 2007-12-27 | 2009-07-09 | Techspace Aero | Stator inner shroud to delimit a primary flow through an aircraft turbine engine |
US8672623B2 (en) | 2009-04-03 | 2014-03-18 | Rolls-Royce Plc | Stator vane assembly |
EP2434101A3 (en) * | 2010-09-22 | 2014-01-01 | Rolls-Royce plc | A damped assembly |
EP2434101A2 (en) | 2010-09-22 | 2012-03-28 | Rolls-Royce plc | A damped assembly |
US9074478B2 (en) | 2010-09-22 | 2015-07-07 | Rolls-Royce Plc | Damped assembly |
GB2490858A (en) * | 2011-03-22 | 2012-11-21 | Rolls Royce Plc | Bladed rotor seal |
GB2490858B (en) * | 2011-03-22 | 2014-01-01 | Rolls Royce Plc | A bladed rotor |
US9017032B2 (en) | 2011-03-22 | 2015-04-28 | Rolls-Royce Plc | Bladed rotor |
US9879562B2 (en) | 2012-04-05 | 2018-01-30 | Snecma | Compressor guide-vane stage for a turbine engine including a gasket between a vane and a shroud of the guide-vane stage |
GB2502868B (en) * | 2012-04-05 | 2018-06-27 | Snecma | A compressor guide-vane stage for a turbine engine |
FR3074219A1 (en) * | 2017-11-30 | 2019-05-31 | Safran Aircraft Engines | TURBOMACHINE ASSEMBLY WITH AN INTEGRATED PLATFORM STEERING VANE AND MEANS FOR MAINTAINING. |
Also Published As
Publication number | Publication date |
---|---|
GB2418709B (en) | 2007-10-10 |
US20060067817A1 (en) | 2006-03-30 |
GB0421588D0 (en) | 2004-10-27 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20110929 |