EP2901021B1 - Turbomaschinengehäuse und laufrad - Google Patents
Turbomaschinengehäuse und laufrad Download PDFInfo
- Publication number
- EP2901021B1 EP2901021B1 EP13779269.3A EP13779269A EP2901021B1 EP 2901021 B1 EP2901021 B1 EP 2901021B1 EP 13779269 A EP13779269 A EP 13779269A EP 2901021 B1 EP2901021 B1 EP 2901021B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- groove
- strip
- casing
- downstream
- blades
- 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
- 239000000463 material Substances 0.000 claims description 35
- 238000011144 upstream manufacturing Methods 0.000 claims description 33
- 239000007789 gas Substances 0.000 description 5
- 239000012530 fluid Substances 0.000 description 4
- 229920000297 Rayon Polymers 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000002964 rayon Substances 0.000 description 2
- 229910018125 Al-Si Inorganic materials 0.000 description 1
- 229910018520 Al—Si Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 241000897276 Termes Species 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 240000008042 Zea mays Species 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000010959 steel Substances 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- 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
-
- 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
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
-
- 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
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F04D29/526—Details of the casing section radially opposing blade tips
Definitions
- the invention relates to an assembly comprising a turbomachine casing and a paddle wheel disposed therein.
- the casing can house one or more impellers, mounted for relative rotation inside the casing.
- the blades are generally arranged in such a way that their ends pass as close as possible to the internal wall of the casing.
- the internal surface of casings of turbomachines is in certain cases equipped with a strip of abradable material (that is to say, provided to undergo a abrasion), arranged inside the casing to the right of the tip of the blades.
- the length of the blades is then determined so that the blades, at full speed of the turbomachine, come into contact with the strip of abradable material.
- the strip of abradable material wears out until it reaches a shape which prevents it from coming into contact with the blades.
- the shape thus obtained is that which allows minimum clearance between the end of the blades and the casing.
- the objective of the invention is therefore to propose an arrangement of housing and / or blades which makes it possible to minimize the clearance between the blades and the housing, which limits as much as possible the contacts and friction between the blades and the housing, and keeps the blades at maximum efficiency.
- an assembly comprising a turbomachine casing and a paddle wheel disposed in said casing, the casing having an internal wall comprising a circumferential strip of abradable material; and in which, facing the ends of the blades, the casing has upstream, the strip of abradable material, and downstream, a circumferential groove; the strip of abradable material being delimited downstream by the circumferential groove, and a downstream limit of the circumferential groove being disposed axially to the right or downstream of the trailing edge of the blades.
- the housing / impeller assembly defined above which comprises, in line with the ends of the blades, a strip of abradable material on the upstream side, and a circumferential groove on the downstream side, has the following advantages.
- the strip of abradable material is placed in line with the tips of the blades, on an upstream portion thereof. However, it is at the upstream part of the end of the blades that the reduction in clearance between the end of the blades and the casing is most useful.
- the existence of a clearance between the tip of the blades and the casing is less important.
- the search for an absence of collisions between the end of the blades and the casing is preferred.
- the housing comprises a groove arranged immediately downstream of the strip of abradable material.
- the bottom of the groove is therefore hollow relative to the strip of abradable material.
- the groove has a larger radius than the strip of abradable material (more precisely, than the internal surface thereof).
- This radius difference results in blades having a substantially constant radius from the leading edge to the trailing edge, being able to have ends having an upstream part very close to the strip of abradable material, so as to wear this strip when putting implementation of the turbomachine, in a manner known per se, and a downstream part not or very unlikely to come into contact with the surfaces of the groove and therefore the casing.
- downstream limit of the circumferential groove can be located at the right, or substantially at the right, of the downstream limit of the blade ends.
- downstream limit of the circumferential groove is disposed axially downstream of the trailing edge of the blades.
- the downstream limit of the circumferential groove is then preferably arranged at an axial distance, relative to the trailing edge of the blades, between 5 and 20% of the axial chord of the blade taken at the blade tip. This distance allows the circumferential groove to have a sufficient range of travel from the top of the blade relative to its nominal position.
- the casing has an optimized contact surface, and advantageously comprises a strip of abradable material of minimum axial extent, which makes it possible to minimize the contacts and friction between the blades and the casing.
- the invention further relates to a turbomachine axial flow compressor, comprising a casing or the assembly (casing and impeller) defined above.
- the invention finally relates to a turbomachine comprising at least one casing as defined above.
- the figure 1 represents a turbomachine axial flow compressor 10.
- This comprises a casing 12, inside which is a paddle wheel 14.
- the paddle wheel 14 itself comprises a rotor disc 16, on which are fixed manner known per se of the radial vanes 18, in an axisymmetric manner.
- the impeller is arranged so that it can rotate along an axis of rotation A inside the casing 12.
- the casing 12 has an internal wall 20 delimiting a gas passage stream.
- This internal wall forms a surface of revolution, which has a generally substantially conical shape, and in this case cylindrical, at the level (axially) of the impeller 14.
- the upstream side of the casing 12 (relative to the direction of flow of gases in the casing) is arranged on the left side of the figure.
- Each of the blades 18 has a leading edge 18A, a trailing edge 18B, and an end 19.
- the radially internal part of the casing 12 mainly consists of two parts: a substantially cylindrical sleeve 22 made of metal or metal alloy (titanium alloy, aluminum, steel, etc.) , and a strip 24 of abradable material, different from the material of the part 22, for example an Al-Si based alloy.
- the sleeve 22 Upstream and downstream of the vanes 18, the sleeve 22 has a radially inner surface 23 which is substantially cylindrical.
- the radius R of the latter is slightly greater than the maximum radius of the impeller 14, measured at the end of the blades 18.
- the sleeve 22 has no channel or internal passage serving to ensure a circulation of gas in line with the paddle wheel 14.
- the sleeve 22 has a housing 26.
- the latter has the shape of a circular circumferential groove, having a shape of revolution around the axis A, and formed in the hollow in the sleeve 22.
- This housing 26 has a bottom surface 27 which is generally substantially cylindrical in shape.
- the casing has upstream the strip 24 of abradable material, and downstream a circumferential groove 30, which is simply the downstream part of the housing 26.
- the strip 24 has a radially inner surface 25.
- the thickness (in the radial direction) of the sleeve 24 is determined so that when the sleeve 24 is disposed in the housing 26, the inner surfaces 23 of the sleeve 22 and 25 of the strip 24 are in continuity with one another, and have the same radius R ( figure 2 ).
- the difference in radius between the surface 23 (inside of the sleeve 22) and the bottom surface 27 of the housing 26, at the level of the strip 24, is thus equal to the thickness of the strip 24.
- the upstream limit of the surface 25 of the strip 24 is disposed axially substantially in line with the leading edge 18A of the blades 18, or even slightly upstream of the latter.
- the surface 25 of the strip 24 may have a discontinuity (of position and / or tangency) relative to the surface 23.
- the strip 24 could have a slightly smaller internal radius , or slightly greater, than the radius R of the surface 23 of the sleeve 22.
- the downstream limit of the strip 24 is located approximately halfway (along the axis A) between the leading edge 18A and the trailing edge 18B of the blade 18.
- the strip 24 made of abradable material covers at least 30% of the axial extent of the blades.
- the groove 30 Immediately downstream of the strip 24 is the groove 30. This is delimited upstream by the strip 24, and at the bottom and on the downstream side by the sleeve 22.
- the groove 30 generally comprises, from upstream to downstream, three successive parts: an upstream part 32 delimited by the strip 24, a bottom 34, and a downstream part 36.
- the upstream part is formed by the downstream surface of the strip 24. Conversely, the bottom 34 and the downstream part 36 are not formed from abradable material.
- this surface is arranged in a plane transverse to the axis A of the casing 12. Consequently, the upstream surface 32 forms at the upstream end of the groove 30 an 'outgoing' stair step, at which the diameter fluid passage increases suddenly.
- the bottom surface 34 is a part of the bottom surface of the housing 26.
- the housing 26 has a cylindrical bottom surface and therefore in these embodiments, the bottom surfaces 27 are cylindrical.
- downstream surface 36 of the groove 30 can be, like the surface 32, arranged in a plane transverse to the axis A of the casing 12 (embodiment of the figure 2 ).
- the downstream surface 36 of the groove 30 forms at the downstream end of the groove 30 a 're-entering' staircase step, at which the diameter of passage of the fluid decreases suddenly to become equal to that of the inner surface of the room 22.
- the downstream limit of the surface 36 of the groove 30 is disposed axially substantially in line with the trailing edge 18B of the vanes 18, or even slightly downstream thereof.
- the groove 30 therefore has a concave axial section.
- the figures 3 to 7 have different embodiments of the groove 30.
- the axial extent of the bottom surface 34 is smaller than in the first embodiment, and conversely the axial extent of the downstream surface 36 is increased.
- the surface 34 ends upstream of the trailing edge of the blades 18, and not in line with it.
- the downstream surface 36 of the groove 30 therefore extends from the downstream limit of the bottom surface 34 upstream of the trailing edge of the vanes 18, to the level (axially) of this trailing edge or downstream thereof. this.
- downstream limit of the circumferential groove is disposed not in line with the trailing edge 18B of the blades, but downstream of the latter.
- the downstream limit of the circumferential groove is thus disposed at an axial distance along the axis A, counted from the trailing edge 18B of the blades, between 5 and 20% of the axial chord of the blades taken at the top of dawn.
- the value of the 'axial chord of the blades' corresponds to the distance along the axis A, such that shown in the figures, between the leading edge 18A and the trailing edge 18B of the blades.
- the embodiment of the figure 5 is close to that of the figure 4 .
- the only difference is the shape of the bottom of the housing 26.
- the bottom of the housing 26 is divided into two parts: an upstream part which receives the strip 24, and a downstream part which forms the groove 30.
- These two parts are both of cylindrical shape; the upstream part has a larger internal diameter than the downstream part, and consequently, these two parts are separated by a shoulder 38.
- This shoulder 38 serves to maintain the position of the strip 34, in particular in the axial direction.
- the figure 6 presents an embodiment in which the bottom surfaces 34 and downstream 36 are continuous; no limit between them is noticeable.
- This surface 40 has a strictly concave (locally) axial section at any point from upstream to downstream and consequently, this surface section does not have a straight line segment.
- Its shape is any shape, which ideally is determined by use or by calculation so as to ensure that in all operating modes of the turbomachine, the surfaces 34 and 36 (and therefore the surface 40) remain in contact with the vanes 18.
- figure 7 presents an embodiment which differs from that presented by the figure 3 by the shape of the upstream surface 32 of the groove 30.
- the upstream surface 32 is frustoconical, of axis A. It forms with the latter an angle at the apex ⁇ of 45 °.
- the angle ⁇ is preferably at least equal to 45 °.
- the end 19 of the blades 18 is located radially strictly inside the wall 20.
- the length of the blades (measured in the radial direction) is constant.
- the blades can have a length (measured in the radial direction) which varies according to the position considered on the axis of the impeller.
- the blades can thus have an axially variable total radius (overall radius of the blades mounted on the impeller).
- the blades can moreover have a total radius which may be greater or at least locally greater (that is to say only over a certain axial interval along the axis of the impeller) than the radius from the inner surface of the housing immediately upstream or downstream of the impeller.
- the end of the blades then penetrates at least locally inside the wall of the casing.
- the blades can also have a non-uniform radial clearance with the casing, as shown in the embodiments presented above.
- the total radius of the blades may be less than or greater than the interior radius (R) of the casing surface immediately upstream or downstream of the blades.
- the total radius of the blades can also vary between one and the other of these configurations depending on the position on the axis of the impeller.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Polishing Bodies And Polishing Tools (AREA)
Claims (11)
- Einheit, umfassend ein Turbomaschinengehäuse (12) und ein Laufrad (14), das in dem genannten Gehäuse angeordnet ist, wobei das Gehäuse (12) eine Innenwand (20) aufweist, umfassend ein Umfangsband (24) aus abreibbarem Material, wobei gegenüber den Enden der Schaufeln das Gehäuse stromaufwärts das Band aus abreibbarem Material und stromabwärts eine Umfangsrille (30) aufweist, wobei das Band aus abreibbarem Material stromabwärts von der Umfangsrille (30) begrenzt wird,
wobei die Einheit dadurch gekennzeichnet ist, dass eine stromabwärtige Begrenzung der Umfangsrille (30) axial rechts oder stromabwärts von der Hinterkante (18B) der Schaufeln (18) angeordnet ist. - Einheit nach Anspruch 1, wobei die Rille, mit Ausnahme einer Fläche (32) der Rille, die aus dem Band aus abreibbarem Material gebildet ist, einen konkaven axialen Querschnitt aufweist.
- Einheit nach Anspruch 1 oder 2, wobei ein Boden (34) der Rille einen zylindrischen Abschnitt umfasst.
- Einheit nach Anspruch 2, wobei die Rille (30), mit Ausnahme einer Fläche der Rille, die aus dem Band aus abreibbarem Material gebildet ist, einen konkaven axialen Querschnitt an jedem Punkt von stromaufwärts bis nach stromabwärts aufweist.
- Einheit nach einem der Ansprüche 1 bis 4, wobei die Rille auf der stromabwärtigen Seite mit der Innenwand (30) des Gehäuses durch eine konkave Anschlussformung (36) verbunden ist, insbesondere mit einem Abschnitt eines Kreisbogens.
- Einheit nach einem der Ansprüche 1 bis 3, wobei die Rille auf der stromabwärtigen Seite mit der Innenwand des Gehäuses durch eine im Wesentlichen kegelstumpfförmige Fläche (36) verbunden ist.
- Einheit nach einem der Ansprüche 1 bis 6, wobei ein Boden (34) der Rille einen Radius aufweist, der kleiner ist als der maximale Radius des Bands aus abreibbarem Material.
- Einheit nach einem der Ansprüche 1 bis 7, wobei eine Fläche der Rille, die aus dem Band aus abreibbarem Material gebildet ist, kegelstumpfförmig ist, wobei der Winkel (α) des Kegelstumpfs mindestens 45° und vorzugsweise mindestens 60° beträgt.
- Einheit nach einem der Ansprüche 1 bis 8, wobei die Rille (30) einen dichten Boden aufweist.
- Einheit nach einem der Ansprüche 1 bis 9, wobei Band aus abreibbarem Material 30 % bis 70 % der axialen Ausdehnung der genannten Schaufeln bedeckt.
- Turbomaschine, umfassend mindestens eine Einheit nach einem der Ansprüche 1 bis 10.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1258959A FR2995949B1 (fr) | 2012-09-25 | 2012-09-25 | Carter de turbomachine |
PCT/FR2013/052172 WO2014049239A1 (fr) | 2012-09-25 | 2013-09-19 | Carter et roue a aubes de turbomachine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2901021A1 EP2901021A1 (de) | 2015-08-05 |
EP2901021B1 true EP2901021B1 (de) | 2020-05-20 |
EP2901021B2 EP2901021B2 (de) | 2023-07-19 |
Family
ID=47505053
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13779269.3A Active EP2901021B2 (de) | 2012-09-25 | 2013-09-19 | Turbomaschinengehäuse und laufrad |
Country Status (9)
Country | Link |
---|---|
US (1) | US9982554B2 (de) |
EP (1) | EP2901021B2 (de) |
JP (1) | JP6382821B2 (de) |
CN (1) | CN104704244B (de) |
BR (1) | BR112015006386B1 (de) |
CA (1) | CA2885650C (de) |
FR (1) | FR2995949B1 (de) |
RU (1) | RU2727943C2 (de) |
WO (1) | WO2014049239A1 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9598981B2 (en) * | 2013-11-22 | 2017-03-21 | Siemens Energy, Inc. | Industrial gas turbine exhaust system diffuser inlet lip |
US11092163B2 (en) | 2017-02-08 | 2021-08-17 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Compressor and turbocharger |
US10648484B2 (en) | 2017-02-14 | 2020-05-12 | Honeywell International Inc. | Grooved shroud casing treatment for high pressure compressor in a turbine engine |
US10876423B2 (en) | 2018-12-28 | 2020-12-29 | Honeywell International Inc. | Compressor section of gas turbine engine including hybrid shroud with casing treatment and abradable section |
FR3091548B1 (fr) * | 2019-01-09 | 2022-12-09 | Safran Aircraft Engines | Elément abradable de turbomachine pourvu de témoins d’usure visuels |
US10914318B2 (en) * | 2019-01-10 | 2021-02-09 | General Electric Company | Engine casing treatment for reducing circumferentially variable distortion |
US11015465B2 (en) | 2019-03-25 | 2021-05-25 | Honeywell International Inc. | Compressor section of gas turbine engine including shroud with serrated casing treatment |
US11078805B2 (en) * | 2019-04-15 | 2021-08-03 | Raytheon Technologies Corporation | Inclination of forward and aft groove walls of casing treatment for gas turbine engine |
JP7234178B2 (ja) * | 2020-03-19 | 2023-03-07 | 株式会社東芝 | 記憶装置 |
KR102519091B1 (ko) * | 2021-05-28 | 2023-04-05 | 두산에너빌리티 주식회사 | 가스터빈의 축류 압축기 유로형상 설계방법 |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
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JP2009174429A (ja) * | 2008-01-24 | 2009-08-06 | Hitachi Ltd | 回転機械 |
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US4534698A (en) * | 1983-04-25 | 1985-08-13 | General Electric Company | Blade containment structure |
GB2245312B (en) * | 1984-06-19 | 1992-03-25 | Rolls Royce Plc | Axial flow compressor surge margin improvement |
JPH0835402A (ja) * | 1994-07-26 | 1996-02-06 | Ishikawajima Harima Heavy Ind Co Ltd | タービンケーシング構造 |
US5607284A (en) * | 1994-12-29 | 1997-03-04 | United Technologies Corporation | Baffled passage casing treatment for compressor blades |
US5474417A (en) * | 1994-12-29 | 1995-12-12 | United Technologies Corporation | Cast casing treatment for compressor blades |
US6227794B1 (en) * | 1999-12-16 | 2001-05-08 | Pratt & Whitney Canada Corp. | Fan case with flexible conical ring |
US6382905B1 (en) * | 2000-04-28 | 2002-05-07 | General Electric Company | Fan casing liner support |
US6536773B2 (en) * | 2000-11-06 | 2003-03-25 | Advanced Components & Materials, Inc. | Compliant brush shroud assembly for gas turbine engine compressors |
US6585479B2 (en) * | 2001-08-14 | 2003-07-01 | United Technologies Corporation | Casing treatment for compressors |
FR2832180B1 (fr) * | 2001-11-14 | 2005-02-18 | Snecma Moteurs | Revetement abradable pour parois de turbines a gaz |
GB0206136D0 (en) * | 2002-03-15 | 2002-04-24 | Rolls Royce Plc | Improvements in or relating to cellular materials |
US20080041842A1 (en) * | 2005-09-07 | 2008-02-21 | United Technologies Corporation | Connector for heater |
GB0526011D0 (en) * | 2005-12-22 | 2006-02-01 | Rolls Royce Plc | Fan or compressor casing |
FR2899274B1 (fr) * | 2006-03-30 | 2012-08-17 | Snecma | Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine |
US8177494B2 (en) * | 2009-03-15 | 2012-05-15 | United Technologies Corporation | Buried casing treatment strip for a gas turbine engine |
FR2947016B1 (fr) * | 2009-06-17 | 2013-07-12 | Snecma | Compresseur centrifuge. |
GB2483059A (en) | 2010-08-23 | 2012-02-29 | Rolls Royce Plc | An aerofoil blade with a set-back portion |
US9115594B2 (en) * | 2010-12-28 | 2015-08-25 | Rolls-Royce Corporation | Compressor casing treatment for gas turbine engine |
GB201103682D0 (en) * | 2011-03-04 | 2011-04-20 | Rolls Royce Plc | A turbomachine casing assembly |
-
2012
- 2012-09-25 FR FR1258959A patent/FR2995949B1/fr active Active
-
2013
- 2013-09-19 US US14/430,864 patent/US9982554B2/en active Active
- 2013-09-19 JP JP2015533666A patent/JP6382821B2/ja active Active
- 2013-09-19 WO PCT/FR2013/052172 patent/WO2014049239A1/fr active Application Filing
- 2013-09-19 BR BR112015006386-1A patent/BR112015006386B1/pt active IP Right Grant
- 2013-09-19 CA CA2885650A patent/CA2885650C/fr active Active
- 2013-09-19 EP EP13779269.3A patent/EP2901021B2/de active Active
- 2013-09-19 CN CN201380052857.1A patent/CN104704244B/zh active Active
- 2013-09-19 RU RU2015115673A patent/RU2727943C2/ru active
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2009174429A (ja) * | 2008-01-24 | 2009-08-06 | Hitachi Ltd | 回転機械 |
Also Published As
Publication number | Publication date |
---|---|
CA2885650C (fr) | 2020-09-15 |
BR112015006386B1 (pt) | 2022-05-24 |
CN104704244A (zh) | 2015-06-10 |
CN104704244B (zh) | 2018-03-02 |
BR112015006386A2 (pt) | 2017-07-04 |
RU2015115673A (ru) | 2016-11-20 |
US9982554B2 (en) | 2018-05-29 |
EP2901021B2 (de) | 2023-07-19 |
RU2727943C2 (ru) | 2020-07-27 |
US20150226078A1 (en) | 2015-08-13 |
CA2885650A1 (fr) | 2014-04-03 |
FR2995949A1 (fr) | 2014-03-28 |
EP2901021A1 (de) | 2015-08-05 |
WO2014049239A1 (fr) | 2014-04-03 |
JP2015531447A (ja) | 2015-11-02 |
FR2995949B1 (fr) | 2018-05-25 |
JP6382821B2 (ja) | 2018-08-29 |
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