EP2914818A1 - Moyeu de carter d'échappement pour une turbomachine - Google Patents
Moyeu de carter d'échappement pour une turbomachineInfo
- Publication number
- EP2914818A1 EP2914818A1 EP13795819.5A EP13795819A EP2914818A1 EP 2914818 A1 EP2914818 A1 EP 2914818A1 EP 13795819 A EP13795819 A EP 13795819A EP 2914818 A1 EP2914818 A1 EP 2914818A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- hub
- wall
- internal
- connecting wall
- vein wall
- 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
- 210000003462 vein Anatomy 0.000 claims description 60
- 238000011144 upstream manufacturing Methods 0.000 claims description 14
- 230000000295 complement effect Effects 0.000 claims description 2
- 230000035882 stress Effects 0.000 description 10
- 238000005266 casting Methods 0.000 description 3
- 239000003351 stiffener Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910000623 nickel–chromium alloy Inorganic materials 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- 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
-
- 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
Definitions
- the invention generally relates to the field of turbomachines, and more particularly the exhaust casings of turbomachines.
- a turbomachine has a main direction extending along a longitudinal axis, and typically comprises, upstream to downstream in the direction of the gas flow, a blower, a low pressure compressor, a high pressure compressor, a combustion chamber , a high pressure turbine, and a low pressure turbine comprising in particular an exhaust casing.
- the exhaust casing contributes to delimiting the primary stream of the fluid (or flow of gas) passing through the turbomachine, and ensures, via the bearing support, the concentricity between the rotor and the stator of the turbomachine, as well as the attachment of the engine downstream to the nacelle.
- the exhaust casing is therefore one of the main structural parts of the engine subject to very high thermal levels, and in which transit loads of extreme unbalance.
- This exhaust casing conventionally comprises:
- the hub generally comprises a flange (of very diverse shapes), connected at an inner portion, to one or more bearing supports adapted to center the rotor on the axis of the turbomachine, and at an outer portion, the exit cone (or exhaust cone, or "Plug" in English) via an external mounting flange.
- This flange is also surmounted by a sheet defining the vein, in the lower part, and having openings adapted to receive the arms.
- These hubs are traditionally of very little shape deformable (say Y or H among others), and this type of architecture induces high stresses in the entire housing, for example, at the intersection between the edge of the housing. attack of the arms and the flask (s).
- the turbomachine when the turbomachine is in operation, the exhaust casing undergoes very high temperatures and very large transient thermal gradients. This is particularly the case of the hub, between its lower part, or at the mounting flanges of the bearing support, and its upper part, or at the level of the vein sheet. Finally, the hub must be able to withstand breaking forces and moments resulting from a dawn loss.
- the hub is sufficiently rigid. However, it must also be able to mechanically admit a sufficient internal deformation (or, if it is associated with tangential arms, a free rotation around the crankcase axis) to be able to ensure the overall service life of the crankcase. 'exhaust.
- vein plate and the flange in two separate parts, in order to allow their relative movement during the thermal expansion of the parts in operation and thus to reduce the stresses applied to them and to their level. intersection with the arms.
- additional fastening means such as flanges and nuts, which increases the size of the hub and therefore increases the overall weight and cost of the casing.
- Significant flow leakage in the interstices may further result from this embodiment. It therefore remains necessary for some exhaust casings to form the flange and the vein plate integrally, that is to say in one piece.
- a hub of a casing of a turbomachine comprising an internal vein wall, from which vanes extend and a curved shaped connecting wall adapted to connect the inner vein wall to an internal fixing flange.
- the curved shape proposed by this document forms an obstacle to the flow likely to cause local aerodynamic disturbances.
- the concavity in the central portion of the connecting wall forms a cavity capable of generating parasitic thermal gradients very harmful to these temperature levels.
- An object of the invention is therefore to provide a hub and a housing, in particular an exhaust casing, which can be adapted to a larger number of turbomachines, which makes it possible to improve the life of the casing, while being able to withstand the extreme vibratory loads (for example the loads induced by the loss of a blade), that is to say, the loads coming from the housing interfaces (such as the bearings, the exit cone, as well as all the parts adjacent to the exhaust casing) and the very large thermal gradients that can be achieved in use in this type of casing, and to meet the objectives of space, mass and flexibility, while being simple to perform and for a moderate cost.
- extreme vibratory loads for example the loads induced by the loss of a blade
- the housing interfaces such as the bearings, the exit cone, as well as all the parts adjacent to the exhaust casing
- the very large thermal gradients that can be achieved in use in this type of casing, and to meet the objectives of space, mass and flexibility, while being simple to perform and for a moderate cost.
- the invention provides an exhaust casing hub of a turbomachine, comprising internal fixing flanges adapted to be fixed to a bearing support, a wall an annular connecting wall and an annular internal vein wall, the connecting wall connecting the internal vein wall to the internal fixing flanges, wherein a radial section of the connecting wall is curved, the hub further comprising a series of ribs extending radially between the connecting wall and the wall; internal vein.
- the hub then has sufficient flexibility to enable it to withstand the very large thermal gradients in the exhaust casing and to let the exhaust casing "breathe” globally so as not to force the expansion of the casing too much. outer ferrule.
- the ribs which form locally optimized reinforcements, can withstand the stresses in the case of forces and extreme moments generated at the borders of the means by the possible loss of a fan blade.
- the hub thus produced is dimensionally adapted to the dynamic stresses experienced by the exhaust casing, in compliance with the mass specifications, and can be obtained by a single casting step, without other mechanically welded operations.
- crankcase hub Some preferred but not limiting features of the crankcase hub are the following:
- the connecting wall, the internal vein wall and the internal fixing flanges are integrally formed
- the connecting wall has a concavity oriented upstream of the casing
- the radial section of the connecting wall comprises, from the internal fixing flanges towards the inner-vein wall, a first substantially straight portion extending radially towards the downstream end of the hub and a second portion of curved shape, whose concavity is oriented upstream of the hub,
- an upstream end (with respect to the direction of the gas flow in the exhaust casing) of the connecting wall located at the junction between the connecting wall and the internal vein wall, has a substantially parallel tangent at the internal vein wall
- the hub furthermore comprises an extra thickness at the intersection between the internal vein wall and the connecting wall,
- the hub further comprises first arm portions, extending from the inner vein wall and formed integrally therewith, and adapted to be fixed to second portions of complementary arms of the housing, the excess thickness extends to the right of a leading edge of the first arm portions, and
- the hub further comprises an annular ridge extending radially from the inner vein wall downstream of the series of ribs.
- the invention also proposes an exhaust casing for a turbomachine, having a main direction extending along a longitudinal axis and comprising
- the invention proposes a turbomachine comprising such a housing.
- FIG. 1 is a partial sectional view of an exemplary exhaust casing of a turbomachine according to the invention
- FIG. 2 is a perspective view of an exemplary embodiment of a hub 2 according to the invention.
- FIG. 3 is a partial perspective view of the example of the exhaust casing of FIG. 1, and
- Figure 4 is a detail view of Figure 1.
- An exhaust casing 1 of a turbomachine according to the invention has a main direction extending along a longitudinal axis X and comprises:
- the hub 2 is generally annular in shape and is adapted to be connected internally to bearing supports 5 via internal fastening flanges 24, and downstream, at an outer portion, to an exit cone of FIG. exhaust via external clamps 26.
- the hub 2 comprises an annular internal stream wall 20 disposed opposite the outer shell 3, adapted to delimit the internal vein of the gas flow, from which extends radially inwardly an annular connecting wall 22 .
- the intersection between the connecting wall 22 and the internal vein wall 20 may lie at the right of the leading edge BA of the arms 4 of the exhaust casing 1, and includes an extra thickness arranged so as to to standardize in this zone 360 ° radial displacements and to limit the creation of over-constraints.
- the internal fastening flanges 24 are integrally formed with the connecting wall 22, and extend from its free end 23, while the external fastening flanges 26 are integrally formed with the inner vein wall 20 and extend from its free end 21.
- a radial section (that is to say in a plane normal to the longitudinal axis X) of the connecting wall 22 is curved and has a shape of lyre or comma, which makes the hub 2 sufficiently flexible to accompany the expansion of the arms 4 and the outer shell 3, but sufficiently rigid from a thermal and mechanical point of view at the intersection between the internal vein wall 20 and the leading edge of the arms 4 to standardize radial deformations on 360 ° in the inner vein wall 20.
- the concavity of the radial section of the connecting wall 22 is oriented upstream, without point of inflection, in order to be deformable (opening or closing) and compensating for the relative expansions caused by the thermal gradients of the hub 2 relative to the outer shell 3 in the exhaust casing 1.
- the connecting wall 22 can indeed deform in bending under the effect of different deformations, thanks to its shape that makes it more flexible.
- the radial section of the connecting wall 22 may comprise, internal fixing flanges 24 towards the internal vein wall 20:
- first portion 22a substantially straight, extending radially in the direction of the external fixing flange 26.
- This first portion therefore has a radial section generally inclined towards the downstream direction (in the direction of the gas flow in the exhaust casing) at an angle of between 20 ° and 60 °, preferably of the order of 40 °.
- the angle ⁇ is measured between the axis Xa along which extends the first portion 22a of the connecting wall, and the axis substantially Y perpendicular to the axis of the exhaust casing passing through the edge of BA attack of arm 4;
- the radial section of the second portion 2b may have a radius R2 of between 15 mm and 30 mm, preferably between 15 mm and 30 mm. mm and 20 mm, for example of the order of 18.5 mm, and
- a third portion 22c curved in shape, whose concavity is oriented upstream of the hub and whose upstream end is located at the junction between the connecting wall 22 and the inner vein wall 20.
- the third portion 22c has a tangent substantially parallel to the internal vein wall 20, so as to form a softened junction not disturbing the flow in the exhaust casing.
- the third portion 22c and the inner vein wall 20 thus have a point of tangency.
- the section radial of the third portion has a radius R1 between 5 mm and 20 mm, preferably between 10 mm and 15 mm, for example of the order of 12 mm.
- the second portion 22c and the third portion 22c together form the concave portion of the connecting wall 22.
- the first portion 22a on the one hand, and the second portion 22b and the third portion 22c on the other hand, have a substantially equal curvilinear length. Furthermore, the intersection between the connecting wall 22 and the internal vein wall 20 is generally in line with the free end 23 of the connecting wall 22, that is to say in the same plane radial passing through the axis X of the casing 1.
- the connecting wall 22 may be relatively thin.
- the thickness of the connecting wall may be of the order of the thickness of the internal vein wall, or between 1 mm and 3 mm.
- the hub 2 can therefore deform at the connecting wall 22 which opens and flexes (its curvature then being greater than at rest) or lengthens and tends to separate the inner vein wall 20 from the internal fastening flange 24, thus avoiding damaging the rest of the hub 2 or the exhaust casing 1
- the internal vein wall 20 may be integrally formed with the connecting wall 22, that is to say in one piece, so as to eliminate the risk of leakage and reduce the overall size and mass of the hub 2 It is also relatively thin in order to optimize the overall mass of the hub 2, except at the leading edge BA, where as will be seen later, the internal vein wall 20 may have an annular extra thickness 29 so to standardize 360 ° radial deformations.
- the internal vein wall 20 and the connecting wall 22 are preferably obtained by casting in a conventional material for the hub 2, that is to say a material capable of resisting, in long use, the very high temperatures experienced by the hub 2 (of the order of 650 ° C to 700 ° C) while supporting the oligo-cyclic and vibratory fatigue and having a good resistance under load.
- the walls 20 and 22 may be made of a nickel-chromium alloy.
- the arms 4 of the exhaust casing 1 extend between the internal vein wall 20 of the hub 2 and the outer shell 3.
- the arms 4 are preferably made in two parts, a first part 42, forming the foot of the arms 4, extending radially from the internal vein wall 20, and a second portion 44, forming the body of the arms 4, extending radially from the outer shell 3.
- the feet 42 are preferably made integrally with the inner vein wall 20 of the hub 2, while the bodies 44 may be formed integrally with the shell 3, for example by casting.
- the two arm portions 42, 44 are then positioned opposite to be fixed together, for example by welding along a weld plane 43, in order to connect the hub 2 and the outer shell 3.
- the feet 42 extend over a height less than or equal to one quarter of the total height of the arms 4.
- the release of the hub 2, formed of a portion of the internal fastening clamps 24 and external 26, connection walls 22, internal vein 20 and feet 42, can then be made more easily than if the weld plane 43 was further away from the inner wall of vein 20.
- Feet 42 have a non-zero height so not to interfere, given the weld plane 43, with the radius of connection of the arms 4 to the inner vein wall 20.
- the inner vein wall 20 of the hub 2 may further comprise ribs 28.
- the ribs 28 extend from preferably between the internal vein wall 20 and the connecting wall 22, facing the arms 4 of the exhaust casing 1. This improves the resistance to deformation of the hub 2 resulting from thermal stresses and loading in extreme loads.
- the hub 2 may comprise two ribs 28 opposite each arm 4 of the exhaust casing 1.
- the ribs 28 may be integrally formed with the internal vein wall 20 and the connecting wall 22. As illustrated in FIGS. 2 and 3, the ribs may each comprise two radial ridges 28a, 28b disposed in the extension of the wall of the wall. extrados and intrados wall respectively, and which extend parallel to the axis X of the connecting wall 20 to the downstream end 21 of the inner vein wall 20, right to the trailing edge BF of the arms 4.
- the radial ridges 28a, 28b of the ribs therefore first have a convergent shape from upstream to downstream in the direction of the gas flow, then meet, and are thus capable of better support the loading imposed by the arms 4 and the bearing support to the hub 2.
- the height of the ribs 28 may furthermore vary between their upstream end, at the level of the connecting wall 20, and their downstream end, at the right of the trailing edge BF of the arms. 4.
- the height of the ribs 28 is maximum at the connecting wall 22, then decreases downstream until the edges 28a and 28b meet, where it stabilizes to the downstream end of the ribs 28, as illustrated in FIGS. 2 and 3, in order to optimize the overall mass of the hub 2 while guaranteeing the load-bearing resistance of the ribs 28.
- the hub 2 may further comprise a stiffener 28c, for uniformly distributing 360 ° radial deformations downstream of the internal vein wall 20, in the vicinity of the trailing edges BF of the arms 4 and supporting the ribs under the charges that pass through these ribs.
- the stiffener 28c may in particular be an annular ridge coaxial with the hub 2, extending radially from the internal vein wall 20 at the downstream end of the ribs 28, or at the right of the trailing edge BF of the arms 4.
- the stiffener 28c extends over a height equal to the height of the downstream end of the ridges 28a, 28b of the rib 28.
- the hub 2 may further comprise an annular extra thickness 29 at the intersection between its connecting wall 22 and its internal vein wall 20, at the right of the leading edge BA of the arms 4.
- This extra thickness 29 which is visible in Figures 1 and 3, in fact makes it possible to standardize the 360 ° radial deformations of the inner vein wall 20 despite the thermal or load stresses experienced by the exhaust casing 1.
- This extra thickness 29 also makes it possible to locally reinforce the hub 2 and to improve its resistance to stresses in the case of forces and extreme moments generated at the borders of the hub 2 by the possible loss of a fan blade.
- the excess thickness 29 is preferably local and does not extend over the entire internal vein wall 20, and remains thin in order to reduce the overall mass of the hub 2.
- the extra thickness may have a radial cross-section. thickness between 4 mm and 8 mm, typically of the order of 5 mm.
- the excess thickness 29 can be arranged at the junction between the connecting wall 22 and the internal vein wall 20, and extends generally along the third portion 22c of the connecting wall 22.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1260439A FR2997444B1 (fr) | 2012-10-31 | 2012-10-31 | Moyeu de carter pour une turbomachine |
PCT/FR2013/052519 WO2014068220A1 (fr) | 2012-10-31 | 2013-10-22 | Moyeu de carter d'échappement pour une turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2914818A1 true EP2914818A1 (fr) | 2015-09-09 |
EP2914818B1 EP2914818B1 (fr) | 2017-06-21 |
Family
ID=47505137
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13795819.5A Active EP2914818B1 (fr) | 2012-10-31 | 2013-10-22 | Moyeu de carter d'échappement pour une turbomachine |
Country Status (9)
Country | Link |
---|---|
US (1) | US9970320B2 (fr) |
EP (1) | EP2914818B1 (fr) |
JP (1) | JP6209218B2 (fr) |
CN (1) | CN104903549B (fr) |
BR (1) | BR112015009659B1 (fr) |
CA (1) | CA2889751C (fr) |
FR (1) | FR2997444B1 (fr) |
RU (1) | RU2670645C9 (fr) |
WO (1) | WO2014068220A1 (fr) |
Families Citing this family (14)
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FR3013387B1 (fr) * | 2013-11-20 | 2015-11-20 | Snecma | Support de palier presentant une geometrie facilitant l'evacuation des noyaux de fonderie |
US11274563B2 (en) * | 2016-01-21 | 2022-03-15 | General Electric Company | Turbine rear frame for a turbine engine |
FR3048015B1 (fr) * | 2016-02-19 | 2020-03-06 | Safran Aircraft Engines | Aube de turbomachine, comprenant un pied aux concentrations de contrainte reduites |
US10343765B2 (en) * | 2016-06-02 | 2019-07-09 | United Technologies Corporation | Toroidal spinner aft flange |
FR3072712B1 (fr) * | 2017-10-20 | 2019-09-27 | Safran Aircraft Engines | Partie arriere de turbomachine presentant un chemin d'efforts allonge entre un cone d'ejection et une virole interne de carter d'echappement |
US10746049B2 (en) * | 2018-03-30 | 2020-08-18 | United Technologies Corporation | Gas turbine engine case including bearing compartment |
FR3091904A1 (fr) * | 2019-01-17 | 2020-07-24 | Airbus Operations | Structure interne d’un conduit d’ejection primaire |
FR3097259B1 (fr) * | 2019-06-12 | 2021-05-21 | Safran Helicopter Engines | Piece annulaire de support d’un palier pour une turbomachine |
FR3097900B1 (fr) * | 2019-06-26 | 2021-06-04 | Safran Aircraft Engines | Support de palier de sortie de turbomachine |
US11286814B1 (en) * | 2020-09-17 | 2022-03-29 | Pratt & Whitney Canada Corp. | Exhaust duct of gas turbine engine |
US11448097B1 (en) | 2021-05-27 | 2022-09-20 | Pratt & Whitney Canada Corp. | Turbine exhaust strut internal core structure |
US11629615B2 (en) * | 2021-05-27 | 2023-04-18 | Pratt & Withney Canada Corp. | Strut reinforcing structure for a turbine exhaust case |
US11725525B2 (en) * | 2022-01-19 | 2023-08-15 | Rolls-Royce North American Technologies Inc. | Engine section stator vane assembly with band stiffness features for turbine engines |
US11898467B2 (en) * | 2022-02-11 | 2024-02-13 | Pratt & Whitney Canada Corp. | Aircraft engine struts with stiffening protrusions |
Family Cites Families (17)
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US3117826A (en) * | 1962-08-31 | 1964-01-14 | Gen Electric | Intermediate rotor support structure |
US4989406A (en) * | 1988-12-29 | 1991-02-05 | General Electric Company | Turbine engine assembly with aft mounted outlet guide vanes |
JPH09324699A (ja) * | 1996-06-05 | 1997-12-16 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンのフレーム構造 |
US6511284B2 (en) * | 2001-06-01 | 2003-01-28 | General Electric Company | Methods and apparatus for minimizing gas turbine engine thermal stress |
US6672966B2 (en) * | 2001-07-13 | 2004-01-06 | Honeywell International Inc. | Curvic coupling fatigue life enhancement through unique compound root fillet design |
US7097412B2 (en) * | 2003-02-14 | 2006-08-29 | United Technologies Corporation | Turbine engine bearing support |
EP1777378A3 (fr) | 2003-07-29 | 2011-03-09 | Pratt & Whitney Canada Corp. | Enveloppe de réacteur à double flux et procédé de fabrication |
US7370467B2 (en) * | 2003-07-29 | 2008-05-13 | Pratt & Whitney Canada Corp. | Turbofan case and method of making |
FR2859002A1 (fr) * | 2003-08-18 | 2005-02-25 | Snecma Moteurs | Dispositif abradable sur carter de soufflante d'un moteur de turbine a gaz |
SE527711C2 (sv) * | 2004-10-06 | 2006-05-16 | Volvo Aero Corp | Lagerstativstruktur och gasturbinmotor som innefattar lagerstativstrukturen |
US7371046B2 (en) * | 2005-06-06 | 2008-05-13 | General Electric Company | Turbine airfoil with variable and compound fillet |
US7762509B2 (en) * | 2007-10-18 | 2010-07-27 | United Technologies Corp. | Gas turbine engine systems involving rotatable annular supports |
EP2379276A4 (fr) * | 2008-12-19 | 2012-06-27 | Volvo Aero Corp | Rayon pour un composant de stator, composant de stator et procédé de fabrication d'un composant de stator |
EP2216516A1 (fr) * | 2009-02-04 | 2010-08-11 | ABB Turbo Systems AG | Dispositif de protection contre l'éclatement d'un compresseur radial |
US8408011B2 (en) * | 2009-04-30 | 2013-04-02 | Pratt & Whitney Canada Corp. | Structural reinforcement strut for gas turbine case |
US9765648B2 (en) * | 2011-12-08 | 2017-09-19 | Gkn Aerospace Sweden Ab | Gas turbine engine component |
CA2872038C (fr) * | 2012-06-15 | 2018-10-16 | United Technologies Corporation | Carter de sortie de turbine a haute durabilite |
-
2012
- 2012-10-31 FR FR1260439A patent/FR2997444B1/fr active Active
-
2013
- 2013-10-22 RU RU2015120552A patent/RU2670645C9/ru active
- 2013-10-22 JP JP2015538532A patent/JP6209218B2/ja active Active
- 2013-10-22 BR BR112015009659-0A patent/BR112015009659B1/pt active IP Right Grant
- 2013-10-22 EP EP13795819.5A patent/EP2914818B1/fr active Active
- 2013-10-22 CA CA2889751A patent/CA2889751C/fr active Active
- 2013-10-22 WO PCT/FR2013/052519 patent/WO2014068220A1/fr active Application Filing
- 2013-10-22 CN CN201380069494.2A patent/CN104903549B/zh active Active
- 2013-10-22 US US14/439,998 patent/US9970320B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR2997444A1 (fr) | 2014-05-02 |
US20150285098A1 (en) | 2015-10-08 |
US9970320B2 (en) | 2018-05-15 |
JP6209218B2 (ja) | 2017-10-04 |
RU2670645C2 (ru) | 2018-10-24 |
CA2889751C (fr) | 2020-07-28 |
EP2914818B1 (fr) | 2017-06-21 |
CN104903549A (zh) | 2015-09-09 |
RU2015120552A (ru) | 2016-12-20 |
BR112015009659B1 (pt) | 2021-01-19 |
JP2015533399A (ja) | 2015-11-24 |
CN104903549B (zh) | 2017-07-07 |
CA2889751A1 (fr) | 2014-05-08 |
RU2670645C9 (ru) | 2018-12-11 |
WO2014068220A1 (fr) | 2014-05-08 |
FR2997444B1 (fr) | 2018-07-13 |
BR112015009659A2 (pt) | 2017-07-04 |
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