EP1843008B1 - Stator vane with variable setting of a turbomachine - Google Patents
Stator vane with variable setting of a turbomachine Download PDFInfo
- Publication number
- EP1843008B1 EP1843008B1 EP07290419A EP07290419A EP1843008B1 EP 1843008 B1 EP1843008 B1 EP 1843008B1 EP 07290419 A EP07290419 A EP 07290419A EP 07290419 A EP07290419 A EP 07290419A EP 1843008 B1 EP1843008 B1 EP 1843008B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- zone
- plate
- pivot
- blade
- blade according
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000006837 decompression Effects 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 3
- 230000006835 compression Effects 0.000 abstract description 2
- 238000007906 compression Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 9
- 210000003462 vein Anatomy 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- 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
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- 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
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/304—Spool rotational speed
Definitions
- the present invention relates to the field of turbomachines such as an axial compressor of gas turbine engine, and aims in particular stator vanes with variable pitch of the machine.
- An articulated system such as the variable pitch stator vanes of a gas turbine engine compressor, includes moving parts relative to one another.
- a blade 1 of variable-pitch rectifier mounted in the housing 3 of the machine.
- the stator blade comprises a blade 12, a plate or platform 13 and a pivot rod 14 at one end.
- the pivot 14 is housed in a bore or radial orifice formed in the wall of the casing 3 by means of different bearings. Dawn is held only by this extremity.
- the other end retains a floating annular element 16 in which it is pivotally mounted by a second pivot 17.
- the ring is provided with sealing means for the portion of the rotor 18 which is adjacent thereto.
- the pivot 14 is journalled in the corresponding bore of the casing via bearings, for example a low bearing 4.
- the platform 13 is housed in a recess shaped machined in the wall of this housing.
- the housing wall is in radial contact with the platform 13 either directly or via a bushing or washer.
- the upper part of the pivot 14 is retained in a high bearing 5.
- the opposite face of the platform 13 with respect to the bearing 4 forms the base of the blade and is swept by the gases set in motion by the compressor. This face of the plate is shaped to ensure the continuity of the vein formed by the housing.
- a nut keeps the blade in its housing and a lever actuated by appropriate control members, controls the rotation of the blade around the axis XX of the rod to put it in the required position relative to the direction gas flow.
- the relative movements result from the sliding of the surfaces in contact with each other.
- the blade 12 In the case of an axial compressor of gas turbine engine or of a single axial compressor of air or other gas, such as blast furnace or natural gas, the blade 12 is subjected over its entire length to the aerodynamic forces and pressure generated by the gas flow.
- the component of these forces oriented perpendicular to the chord in the direction intrados towards extrados, passing generally by the axis of the pivot is the most important. Note, however, that in cases of major robberies the component may deviate from this axis.
- the blade is also subjected to axial forces of static pressure directed upstream due to the pressure difference between the downstream and the upstream. The resulting force is illustrated by the arrow F in the figures.
- the applicant also has a permanent goal to find solutions that can lighten the machine without affecting its performance and reliability. Any gain in mass improves the efficiency of the machine and reduces operating costs.
- the turbomachine stator vane, variable pitch comprising a blade, extended on one side by a pivot by which it is rotatably mounted in a bore of the casing of the turbomachine, and a plate, between the blade and the pivot, perpendicular to the direction formed by the blade and the pivot, is characterized in that the face of the plate opposite the blade comprises a first zone and a second zone, the first zone being subjected to friction with the wall of the casing due to the transverse forces applied to the blade and the second zone being subjected in normal operation to a lower friction than the first zone, the thickness of the plate on the second zone is reduced compared to the thickness of the plate on the first zone.
- the blades with variable pitch, in particular axial compressor, of the prior art have a plate of uniform thickness if one does not take into account the curvature and / or nonlinearity of the gas stream. So thanks to the invention we can reduce the mass of this part of the blade without impairing its functionality, namely ensure continuity of the vein and reduce leakage along the pivot.
- the second zone of lower thickness extends practically over an arc of 60 to 120 degrees around the axis of the pivot.
- the first zone is located on the extrados side and the second zone extends on the intrados side.
- the second zone of reduced thickness is delimited by a thicker edge - in particular the upper face of this edge is in the extension of the upper plane surface of the plate - than the first zone so as to form a decompression chamber between the periphery of the plate and the pivot which improves the seal.
- this edge makes it possible to form a contact in the event that the forces become reversed, in particular when compressor pumping phenomena occur.
- this arrangement is appreciable when mounting the machine by preventing the parts from tilting too much.
- a simple and economical way to make blades with a second zone thus fitted is to machine the plate.
- the cavity is flat-bottomed, curved or any other shape.
- the plate 13 is viewed from above in perspective.
- a cavity 22A has been machined in the face of the plate facing towards the casing 3 in the second zone 22, which is not subjected to compression forces resulting from the application of the force F on the blade 12.
- This cavity 22A has been machined here by means known per se.
- the bottom of the cavity is flat, it could be curved if the machining head was ball-shaped. Shapes other than the one shown are possible.
- the cavity can come from foundry, forging or metallurgy powders.
- the cavity preferably extends over an arc, of a circle for example, of 60 to 120 degrees, advantageously corresponding to the arc underlying the zone of intense friction.
- This cavity has the function of reducing the mass of the blade but not reducing its mechanical characteristics.
- the resulting thickness of the plate is therefore sufficient to ensure the mechanical strength of the plate. It is observed that a border 23 has been preserved on the periphery of the plate. This border has a dual function. The first is to form a decompression chamber reducing air leakage between the vein of the turbomachine and the pivot 14 through the bore of the housing in which is housed the pivot 14.
- the second function is to form a surface of support in the event of inversion of the forces resulting from a malfunction of the turbomachine, such as the pumping of the compressor or to simplify assembly operations.
- the width of this border may not be constant. For example, it could be wider in an area to be strengthened.
- its upper plane is in the plane of the plate facing the housing.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
Description
La présente invention se rapporte au domaine des turbomachines tel qu'un compresseur axial de moteur à turbine à gaz, et vise en particulier les aubes de stator à calage variable de la machine.The present invention relates to the field of turbomachines such as an axial compressor of gas turbine engine, and aims in particular stator vanes with variable pitch of the machine.
Un système articulé, comme les aubes de redresseur à calage variable d'un compresseur de moteur à turbine à gaz, comprend des pièces en mouvement relatif les unes par rapport aux autres. Sur les
Dans le cas d'un compresseur axial de moteur à turbine à gaz ou bien d'un compresseur axial seul d'air ou autre gaz, tel que de haut fourneau ou gaz naturel, la pale 12 est soumise sur toute sa longueur aux efforts aérodynamiques et de pression engendrés par le flux gazeux. La composante de ces efforts orientée perpendiculairement à la corde dans le sens intrados vers extrados, en passant généralement par l'axe du pivot est la plus importante. On note cependant que dans les cas de braquages importants la composante peut s'écarter de cet axe. La pale est soumise aussi à des efforts axiaux de pression statique dirigés vers l'amont en raison de la différence de pression entre l'aval et l'amont. La force résultante est illustrée par la flèche F sur les figures. Il s'ensuit l'application d'un moment qui associé à la rotation de calage autour de l'axe XX sur une amplitude qui peut atteindre et dépasser 40 degrés, crée une zone de frottement intense. Ce frottement conduit accessoirement à une usure de la platine et/ou des douilles. Cette première zone 20 de frottement intense est localisée sur une partie de la surface de la platine. Elle est signalée par des croix sur la
Une aube de stator de l'art antérieur est décrite dans le document
Dans le domaine aéronautique toute surcharge pondérale est à éviter, et indépendamment de la suppression de toute surcharge, on cherche aussi à éliminer toute masse qui ne remplit aucune fonction qu'elle soit mécanique ou aérodynamique.In the aeronautical field any excess weight is to be avoided, and independently of the suppression of any overload, one also seeks to eliminate any mass which does not fulfill any function that it is mechanical or aerodynamic.
Le déposant a par ailleurs comme objectif permanent de trouver des solutions qui permettent d'alléger la machine sans nuire pour autant à ses performances et à sa fiabilité. Tout gain en masse améliore le rendement de la machine et permet de réduire les coûts d'exploitation.The applicant also has a permanent goal to find solutions that can lighten the machine without affecting its performance and reliability. Any gain in mass improves the efficiency of the machine and reduces operating costs.
Le déposant en poursuivant cet objectif est ainsi parvenu à la présente invention se rapportant à une aube de stator à calage variable.The applicant in pursuit of this object has thus come to the present invention relating to a variable-pitch stator blade.
Conformément à l'invention, l'aube de stator de turbomachine, à calage variable, comportant une pale, prolongée d'un côté par un pivot par lequel elle est montée rotative dans un alésage du carter de la turbomachine, et une platine, entre la pale et le pivot, perpendiculaire à la direction formée par la pale et le pivot , est caractérisée par le fait que la face de la platine opposée à la pale comprenant une première zone et une seconde zone, la première zone étant soumise à un frottement intense avec la paroi du carter en raison des effort transversaux appliqués sur la pale et la seconde zone étant soumise en fonctionnement normal à un frottement plus faible que la première zone, l'épaisseur de la platine sur la seconde zone est réduite par rapport à l'épaisseur de la platine sur la première zone.According to the invention, the turbomachine stator vane, variable pitch, comprising a blade, extended on one side by a pivot by which it is rotatably mounted in a bore of the casing of the turbomachine, and a plate, between the blade and the pivot, perpendicular to the direction formed by the blade and the pivot, is characterized in that the face of the plate opposite the blade comprises a first zone and a second zone, the first zone being subjected to friction with the wall of the casing due to the transverse forces applied to the blade and the second zone being subjected in normal operation to a lower friction than the first zone, the thickness of the plate on the second zone is reduced compared to the thickness of the plate on the first zone.
Les aubes à calage variable, notamment de compresseur axial, de l'art antérieur ont une platine d'épaisseur uniforme si on ne tient pas compte de la courbure et/ou non linéarité de la veine de gaz. Ainsi grâce à l'invention on permet de réduire la masse de cette partie de l'aube sans nuire à sa fonctionnalité, à savoir assurer la continuité de la veine et réduire les fuites le long du pivot.The blades with variable pitch, in particular axial compressor, of the prior art have a plate of uniform thickness if one does not take into account the curvature and / or nonlinearity of the gas stream. So thanks to the invention we can reduce the mass of this part of the blade without impairing its functionality, namely ensure continuity of the vein and reduce leakage along the pivot.
La seconde zone d'épaisseur plus faible s'étend pratiquement sur un arc de 60 à 120 degrés autour de l'axe du pivot.The second zone of lower thickness extends practically over an arc of 60 to 120 degrees around the axis of the pivot.
Pour un compresseur axial, la première zone est située côté extrados et la seconde zone s'étend du côté de l'intrados.For an axial compressor, the first zone is located on the extrados side and the second zone extends on the intrados side.
De préférence la seconde zone d'épaisseur réduite est délimitée par une bordure plus épaisse - notamment la face supérieure de cette bordure est dans le prolongement de la surface plane supérieure de la platine - que la première zone de façon à former une chambre de décompression entre la périphérie de la platine et le pivot ce qui permet d'améliorer l'étanchéité. En outre cette bordure permet de former un contact dans le cas où les efforts viendraient à s'inverser, notamment lorsqu'il se produit des phénomènes de pompage du compresseur. En outre cette disposition est appréciable au montage de la machine en empêchant les pièces de basculer exagérément.Preferably the second zone of reduced thickness is delimited by a thicker edge - in particular the upper face of this edge is in the extension of the upper plane surface of the plate - than the first zone so as to form a decompression chamber between the periphery of the plate and the pivot which improves the seal. In addition, this edge makes it possible to form a contact in the event that the forces become reversed, in particular when compressor pumping phenomena occur. In addition, this arrangement is appreciable when mounting the machine by preventing the parts from tilting too much.
Un moyen simple et économique de réaliser des aubes avec une seconde zone ainsi aménagée est d'usiner la platine. Selon l'outil choisi la cavité est à fond plat, incurvé ou encore de toute autre forme.A simple and economical way to make blades with a second zone thus fitted is to machine the plate. Depending on the chosen tool, the cavity is flat-bottomed, curved or any other shape.
D'autres caractéristiques et avantages ressortiront de la description qui suit d'un mode de réalisation non limitatif de l'invention en regard des dessins sur lesquels
- La
figure 1 montre en coupe selon l'axe de la machine un exemple d'aube de stator à calage variable conventionnelle montée dans un carter de compresseur, - La
figure 2 montre la même aube vue de dessus, - La
figure 3 est une vue en perspective d'une partie d'aube présentant les caractéristiques de l'invention.
- The
figure 1 shows in section along the axis of the machine an example of conventional variable-pitch stator vane mounted in a compressor housing, - The
figure 2 shows the same dawn seen from above, - The
figure 3 is a perspective view of a blade portion having the features of the invention.
En se reportant à la
On a décrit une solution où la réduction d'épaisseur était réalisée sur la face supérieure de la platine. Cependant il entre également dans le cadre de l'invention de réaliser cette réduction d'épaisseur en formant une cavité dans la face de la platine située du côté de la veine de gaz ou en amincissant la platine par cette face.A solution has been described in which the thickness reduction is performed on the upper face of the plate. However, it is also within the scope of the invention to achieve this reduction in thickness by forming a cavity in the face of the plate located on the side of the gas stream or by slimming the plate by this face.
Claims (8)
- Turbomachine variable-pitch stator blade comprising an aerofoil (12), extended on one side by a pivot (14) by which it is mounted so as to rotate in a bore of the casing (3) of the turbomachine, and a plate (13), between the aerofoil and the pivot, perpendicular to the line formed by the aerofoil and the pivot, characterized in that, since the face of the plate opposite to the aerofoil comprises a first zone (20) and a second zone (22), the first zone (20) being subjected to an intense friction with the wall of the casing (3) because of the transverse forces applied to the aerofoil (12), the thickness of the plate on the second zone (22) is reduced relative to the thickness of the plate of the first zone (20).
- Blade according to Claim 1, whereof the thinner portion of the second zone (22) extends over an arc of 60 to 120 degrees about the pivot (14).
- Blade according to Claim 1, whereof the first zone is situated on the suction side and the second zone extends from the pressure side of the aerofoil.
- Blade according to Claim 1, 2 or 3, whereof the second thinner zone is delimited by a border (23) so as to form a decompression chamber between the periphery of the plate (13) and the pivot (14).
- Blade according to one of the preceding claims, whereof the second thinner zone (22) forms a cavity obtained by machining the plate (13).
- Blade according to the preceding claim, whereof the cavity has a flat or curved bottom.
- Blade according to one of Claims 5 or 6, whereof the cavity is elongate in an arc of a circle.
- Turbomachine comprising at least one stator blade according to one of Claims 1 to 7.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0651243A FR2899637B1 (en) | 2006-04-06 | 2006-04-06 | STATOR VANE WITH VARIABLE SETTING OF TURBOMACHINE |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1843008A1 EP1843008A1 (en) | 2007-10-10 |
EP1843008B1 true EP1843008B1 (en) | 2009-06-17 |
Family
ID=37491722
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07290419A Active EP1843008B1 (en) | 2006-04-06 | 2007-04-05 | Stator vane with variable setting of a turbomachine |
Country Status (10)
Country | Link |
---|---|
US (1) | US7980815B2 (en) |
EP (1) | EP1843008B1 (en) |
JP (1) | JP5143465B2 (en) |
CN (1) | CN101054908B (en) |
AT (1) | ATE434116T1 (en) |
CA (1) | CA2583850C (en) |
DE (1) | DE602007001294D1 (en) |
ES (1) | ES2328530T3 (en) |
FR (1) | FR2899637B1 (en) |
RU (1) | RU2436967C2 (en) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009004933A1 (en) * | 2009-01-16 | 2010-07-29 | Mtu Aero Engines Gmbh | Guide vane for a stator of a turbocompressor |
US9309778B2 (en) | 2010-12-30 | 2016-04-12 | Rolls-Royce North American Technologies, Inc. | Variable vane for gas turbine engine |
US9062560B2 (en) * | 2012-03-13 | 2015-06-23 | United Technologies Corporation | Gas turbine engine variable stator vane assembly |
US9334751B2 (en) * | 2012-04-03 | 2016-05-10 | United Technologies Corporation | Variable vane inner platform damping |
CN103397912B (en) * | 2013-08-19 | 2015-07-15 | 中国航空动力机械研究所 | Turbine engine rotor blade, turbine and turbine engine |
CN104153822B (en) * | 2014-07-22 | 2015-09-30 | 哈尔滨工程大学 | A kind ofly comprise the variable geometry turbine of end of blade with the variable stator vane angle of the little wing structure of groove-like |
US9784285B2 (en) | 2014-09-12 | 2017-10-10 | Honeywell International Inc. | Variable stator vane assemblies and variable stator vanes thereof having a locally swept leading edge and methods for minimizing endwall leakage therewith |
US9995166B2 (en) * | 2014-11-21 | 2018-06-12 | General Electric Company | Turbomachine including a vane and method of assembling such turbomachine |
CN104533544B (en) * | 2015-01-26 | 2016-01-06 | 成都成发科能动力工程有限公司 | For the stator blade controlling device of TRT |
DE102015110250A1 (en) * | 2015-06-25 | 2016-12-29 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a turbomachine with a housing device and a plurality of guide vanes |
DE102015110249A1 (en) * | 2015-06-25 | 2017-01-12 | Rolls-Royce Deutschland Ltd & Co Kg | Stator device for a turbomachine with a housing device and a plurality of guide vanes |
CN109312658B (en) * | 2016-03-30 | 2022-02-22 | 三菱重工发动机和增压器株式会社 | Variable capacity turbocharger |
US10436050B2 (en) | 2017-04-11 | 2019-10-08 | United Technologies Corporation | Guide vane arrangement for gas turbine engine |
US11572798B2 (en) * | 2020-11-27 | 2023-02-07 | Pratt & Whitney Canada Corp. | Variable guide vane for gas turbine engine |
CN113623021B (en) * | 2021-07-30 | 2023-01-17 | 中国航发沈阳发动机研究所 | Variable-geometry low-pressure turbine guide vane |
CN114321019A (en) * | 2021-12-27 | 2022-04-12 | 中国航发沈阳发动机研究所 | Adjustable stator structure of gas compressor |
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BE496713A (en) * | 1949-07-01 | |||
US3542484A (en) * | 1968-08-19 | 1970-11-24 | Gen Motors Corp | Variable vanes |
US4498790A (en) * | 1983-11-21 | 1985-02-12 | United Technologies Corporation | Bushing securing apparatus |
US4889470A (en) * | 1988-08-01 | 1989-12-26 | Westinghouse Electric Corp. | Compressor diaphragm assembly |
CA2082709A1 (en) * | 1991-12-02 | 1993-06-03 | Srinivasan Venkatasubbu | Variable stator vane assembly for an axial flow compressor of a gas turbine engine |
FR2685033B1 (en) * | 1991-12-11 | 1994-02-11 | Snecma | STATOR DIRECTING THE AIR INLET INSIDE A TURBOMACHINE AND METHOD FOR MOUNTING A VANE OF THIS STATOR. |
FR2723614B1 (en) * | 1994-08-10 | 1996-09-13 | Snecma | DEVICE FOR ASSEMBLING A CIRCULAR STAGE OF PIVOTING VANES. |
US5593275A (en) * | 1995-08-01 | 1997-01-14 | General Electric Company | Variable stator vane mounting and vane actuation system for an axial flow compressor of a gas turbine engine |
US5622473A (en) * | 1995-11-17 | 1997-04-22 | General Electric Company | Variable stator vane assembly |
JPH1054206A (en) * | 1996-08-09 | 1998-02-24 | Mitsubishi Heavy Ind Ltd | Support bearing device of variable vane |
FR2775731B1 (en) * | 1998-03-05 | 2000-04-07 | Snecma | CIRCULAR STAGE OF BLADES AT INTERIOR ENDS JOINED BY A CONNECTING RING |
US6209198B1 (en) * | 1998-12-16 | 2001-04-03 | General Electric Company | Method of assembling a variable stator vane assembly |
US6283705B1 (en) * | 1999-02-26 | 2001-09-04 | Allison Advanced Development Company | Variable vane with winglet |
US6682299B2 (en) * | 2001-11-15 | 2004-01-27 | General Electric Company | Variable stator vane support arrangement |
US6843638B2 (en) * | 2002-12-10 | 2005-01-18 | Honeywell International Inc. | Vane radial mounting apparatus |
US6808364B2 (en) * | 2002-12-17 | 2004-10-26 | General Electric Company | Methods and apparatus for sealing gas turbine engine variable vane assemblies |
US7220098B2 (en) * | 2003-05-27 | 2007-05-22 | General Electric Company | Wear resistant variable stator vane assemblies |
US20050084190A1 (en) * | 2003-10-15 | 2005-04-21 | Brooks Robert T. | Variable vane electro-graphitic bushing |
US7112039B2 (en) * | 2003-10-29 | 2006-09-26 | United Technologies Corporation | Variable vane electro-graphic thrust washer |
-
2006
- 2006-04-06 FR FR0651243A patent/FR2899637B1/en not_active Expired - Fee Related
-
2007
- 2007-04-05 CA CA2583850A patent/CA2583850C/en active Active
- 2007-04-05 DE DE602007001294T patent/DE602007001294D1/en active Active
- 2007-04-05 AT AT07290419T patent/ATE434116T1/en not_active IP Right Cessation
- 2007-04-05 EP EP07290419A patent/EP1843008B1/en active Active
- 2007-04-05 ES ES07290419T patent/ES2328530T3/en active Active
- 2007-04-06 CN CN2007101016223A patent/CN101054908B/en active Active
- 2007-04-06 RU RU2007112880/06A patent/RU2436967C2/en active
- 2007-04-06 US US11/697,455 patent/US7980815B2/en active Active
- 2007-04-06 JP JP2007100147A patent/JP5143465B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
JP2007278291A (en) | 2007-10-25 |
CA2583850C (en) | 2014-02-18 |
FR2899637A1 (en) | 2007-10-12 |
RU2007112880A (en) | 2008-10-20 |
DE602007001294D1 (en) | 2009-07-30 |
ES2328530T3 (en) | 2009-11-13 |
CN101054908B (en) | 2010-09-08 |
US20100266389A1 (en) | 2010-10-21 |
US7980815B2 (en) | 2011-07-19 |
CN101054908A (en) | 2007-10-17 |
EP1843008A1 (en) | 2007-10-10 |
JP5143465B2 (en) | 2013-02-13 |
FR2899637B1 (en) | 2010-10-08 |
RU2436967C2 (en) | 2011-12-20 |
ATE434116T1 (en) | 2009-07-15 |
CA2583850A1 (en) | 2007-10-06 |
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