WO2003018962A1 - Carter de stator de turbomachine - Google Patents
Carter de stator de turbomachine Download PDFInfo
- Publication number
- WO2003018962A1 WO2003018962A1 PCT/FR2002/002948 FR0202948W WO03018962A1 WO 2003018962 A1 WO2003018962 A1 WO 2003018962A1 FR 0202948 W FR0202948 W FR 0202948W WO 03018962 A1 WO03018962 A1 WO 03018962A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- hooks
- rings
- stator
- envelope
- casing
- Prior art date
Links
- 238000007789 sealing Methods 0.000 claims abstract description 20
- 239000000463 material Substances 0.000 claims description 6
- 238000007664 blowing Methods 0.000 claims description 4
- 238000009423 ventilation Methods 0.000 abstract description 4
- 238000010276 construction Methods 0.000 abstract description 2
- 238000003754 machining Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 12
- 238000009413 insulation Methods 0.000 description 7
- 210000003462 vein Anatomy 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000013021 overheating Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000011819 refractory material Substances 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 210000002105 tongue Anatomy 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
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
- F01D25/145—Thermally insulated casings
-
- 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
- F01D25/246—Fastening of diaphragms or stator-rings
Definitions
- such a part comprises support parts, generally curved in hooks, to support rings carrying stages of fixed blades.
- These hooks extend the structure of the casing up to near the gas stream and are therefore subjected to much greater heating than the envelope.
- the unfavorable situation of the hooks makes it necessary to take special precautions to protect them from overheating, at the cost of a great complication of the structure of the machine at this location and without complete success being obtained, the hooks may still require early repairs.
- the invention relates to an improved casing, which is both less expensive, easier to build, more durable, with a rather simplified structure and which requires less protection against heat.
- stator casing comprising an envelope and ring support parts on an internal face of the envelope, the support parts being distinct from the envelope, joined to the casing by means of assembly and extending only over circular sectors, characterized in that the support parts comprise hooks provided with opposite support grooves of at least two of the rings, the rings being composed of sealing rings alternating with stator rings carrying fixed vanes, the stator rings being joined to the support pieces by portions extending on their outer side radially.
- the ring support parts being attached to the housing, can be manufactured separately at lower cost, replaced at will and made of a material other than the housing; at least some of these parts (called hooks) support both a stator ring and an adjacent seal ring, allowing direct attachment of all rings to the housing, which improves accuracy and mounting stability; finally, the attachment of the stator rings by radially outer portions makes it possible to retract the hooks of the gas stream and therefore to reduce their heating and that which they communicate to the casing.
- FIG. 1 illustrates a design of the prior art
- FIGS. 2 and 3 represent two possible embodiments of the invention
- FIG. 4 is a view in perspective of the first of these modes.
- the stator of a kind known in FIG. 1 is provided with a casing 1 composed of an outer casing 2 and of hooks of which one can find essentially two kinds: flat hooks 3 and heel hooks 4 alternating along the axis of the machine. All the hooks 3 and 4 are circular and connected to the casing 2 by a wing 5 without structural discontinuity. They carry stator rings 6 and alternating sealing rings 7 which together form a lining of the casing by isolating it from a gas flow stream 8 of the machine. These rings 6 and 7 are composed of juxtaposed ring sectors and joined by sealing tongues housed in grooves facing the adjacent sectors.
- the stator rings 6 have fixed vanes and comprise a base plate 10 provided with hooks 11 and 12 at the front and at the rear on the outside.
- the sealing rings 7 carry linings 13 of abradable material extending in front of the ends of movable blades 14 and include a base plate 15 ending at the front in an external hook 16 and an internal hook 17. These hooks 16 and 17 are arranged so as to frame the heel 18 of the hooks 4 while retaining the rear hooks 12 of the stator rings 6 on said hooks 4.
- the base plates 15 of the sealing rings 7 bear at the rear on the simple hooks 3, and this assembly is framed by the base plate 10 and the front hooks 11 of the stator rings 6.
- the assembly thus obtained is rigid but complicated; it makes it possible to cover the hooks 3 and 4 by the ends of the rings 6 and 7, without exposing them directly to the high temperature of the gases of the vein 8.
- this protection is not sufficient, especially since leaks from hot gases to the casing 1 remain .possible despite the seals that can be provided, in particular between the angular sectors of the rings 6 and 7: in practice, the casing 1 must be cooled by a flow of fresh air from the ventilated fan another part of the machine which is blown into the chambers delimited by the casing 2, the hooks 3 and 4 and the rings 6 and 7.
- the casing 21 of FIG. 2 comprises, as previously, an outer casing 22 and hooks 23 and 24 of different kinds alternating along the machine and which also serve to support stator rings 26 and sealing rings 27 also alternating; but the hooks 23 and 24 have the particularities (we also refer to FIG. 4) of extending only over sectors of a circle, but of being distributed in circular rows, and of comprise each of the tenons 28 passing through respective mortises 29 of the envelope 22.
- the attachment of the hooks 23 and 24 to the envelope 22 is made by shrinking, welding or bolting.
- the hooks 23 and 24 are separate parts, it becomes possible to construct them from different materials: the hooks 23 and 24 will thus be made of alloys resistant to overheating (and possibly different depending on the location of the hook considered and the surrounding temperature), which was previously excluded; and the casing 22 will be of a more ordinary alloy, less expensive and easier to shape. It should be noted that the greater ease of manufacture offered by the separate manufacture of the envelope 22 and of the hooks 23 and 24 is another source of economy.
- the hooks 23 are simple hooks similar to the hooks 3, the hooks 24 are different from the heel hooks 4 and here include a pair of grooves 30 and 31 that of the opposite; the concept of the stator rings 26 is similar to the preceding rings 6, as well as that of the sealing rings 27.
- the hooks 24 which replace the hooks 4 are now exposed to the gases of the vein 8, but this is not harmful now that we can build them in a material sufficiently resistant to heat, such as M509 (KC24NWTZ) for a temperature above 900 ° C or RENE77 (NK15CADT) for a lower temperature.
- the sealing rings 27 are set back relative to the stator rings 26, that is to say that they do not extend them but are close to the outer casing 22: they no longer serve to delimit the periphery of the gas flow stream and carry simply a layer of abradable material 35 which forms a seal with circular ridges (wipers) 36 disposed outside of peripheral rings 37 which surround the moving blades 14.
- the peripheral rings 37 extend the stator rings 26, and it is therefore they which really delimit the gas flow stream, advantageously since its section varies much more continuously than in the design in FIG. 1. This effect can be attributed to the radial difference in level existing between the grooves 30 and 31 of the hooks 24. Good continuity of the vein was also achieved in the design where the stator and sealing rings were nested one inside the other, but the assembly e was more complicated and the movable blades were devoid of a peripheral ring which contributes much to their cohesion.
- the outer envelope 22 can be protected by a lining comprising an inner skin
- the internal skin 33 and the insulation 34 can be easily installed by operating recesses therein allowing the hooks 23 and 24 to pass through them. As the hooks 23 and 24 do not form continuous circles, the internal skin 33 and the insulation 34 remain in one piece and can therefore be installed easily and maintained without special precautions even if the internal skin 33 is a fairly flexible metal sheet: it can for example be pressed on the sealing rings 27.
- the insulation 34 provides passive protection against heat which does not contribute to cooling the hooks 23 and 24, unlike a ventilation system; but hooks made of more refractory material often no longer need to be refreshed, whereas the insulation 34 can be easily modeled closely around the hooks 23 and 24, which eliminates the leakage of hot gases towards the envelope 22; it has the added benefit of stretching, like the skin.
- internal 33 in front of the junctions of the sectors of the rings 26 and 27 and to make up for the seals installed there and which we can henceforth do without: the sectors of the rings 26 and 27 will then be juxtaposed with games, their edges being simple , devoid of grooves or other means of housing intermediate seals, and leakage of gases from the vein will be tolerated up to the internal skin 33.
- the insulation 34 is a preferred means of protecting the envelope 22; it is not incompatible with reduced cooling of the hooks 23 and 24 (by a system which will be discussed later), but we can revert to active ventilation if it is insufficient: the internal skin 33 will remain to stop leaks from hot gases and channel the ventilation air into the now empty space between it and the casing 22.
- the design of the housing 39 in FIG. 3 differs significantly from the previous one in that the hooks of two kinds are replaced by hooks 40 of a single kind each of which includes an enlarged dovetail or tee end to support a respective stator ring 41 which is provided on its outer side with two hooks 42 and 43 facing one another and which engage on the enlargements of the end of the hooks 40.
- hooks 40 and the stator rings 41 are located at the same cross sections of the machine and each stator ring 41 is supported by a single row of hooks 40; this solution has half the number of hooks than the previous ones, and the sealing rings 7 and 27 are replaced by larger sealing rings 44, with base plates 45 devoid of hooks and the ends of which penetrate into grooves 46 hooks 40.
- the hooks 40 are provided with pairs of tenons 47 passing through mortises
- Cooling more or less energetic operated on the housing 39 makes it possible to adjust its temperature and its corresponding expansion, and therefore the clearances between the tips of the blades and the sealing devices comprising in particular the rings 44.
- a sheet 55 surrounding the housing 39 can be added to channel the supply air to an outlet; if it completely covers the ramps 52, the appearance of the device is improved.
- This device designed above all to control games, has the ability to also be used to ventilate hooks 40 directly by blowing on the pins 47, as well as the casing 49 by sliding on it; in this particular embodiment, it only requires a reduced number of ramps 52 thanks to the reduction in the number of rows of hooks.
- a similar device could equip the embodiment of FIG. 2.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Gasket Seals (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2457892A CA2457892C (fr) | 2001-08-30 | 2002-08-28 | Carter de stator de turbomachine |
JP2003523797A JP4279667B2 (ja) | 2001-08-30 | 2002-08-28 | ターボ機械ステータハウジング |
US10/486,831 US7070387B2 (en) | 2001-08-30 | 2002-08-28 | Gas turbine stator housing |
UA2004021459A UA76185C2 (uk) | 2001-08-30 | 2002-08-28 | Корпус статора газової турбіни |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR01/11232 | 2001-08-30 | ||
FR0111232A FR2829176B1 (fr) | 2001-08-30 | 2001-08-30 | Carter de stator de turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2003018962A1 true WO2003018962A1 (fr) | 2003-03-06 |
Family
ID=8866814
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2002/002948 WO2003018962A1 (fr) | 2001-08-30 | 2002-08-28 | Carter de stator de turbomachine |
Country Status (12)
Country | Link |
---|---|
US (1) | US7070387B2 (fr) |
EP (1) | EP1288444B1 (fr) |
JP (1) | JP4279667B2 (fr) |
CN (1) | CN1325765C (fr) |
CA (1) | CA2457892C (fr) |
DE (1) | DE60201718T2 (fr) |
ES (1) | ES2229067T3 (fr) |
FR (1) | FR2829176B1 (fr) |
MA (1) | MA26137A1 (fr) |
RU (1) | RU2324057C2 (fr) |
UA (1) | UA76185C2 (fr) |
WO (1) | WO2003018962A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7234920B2 (en) * | 2004-04-05 | 2007-06-26 | Snecma Moteurs | Turbine casing having refractory hooks and obtained by a powder metallurgy method |
GB2614760A (en) * | 2022-01-13 | 2023-07-19 | Rolls Royce Plc | Turbine for gas turbine engine |
Families Citing this family (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10359730A1 (de) * | 2003-12-19 | 2005-07-14 | Mtu Aero Engines Gmbh | Turbomaschine, insbesondere Gasturbine |
FR2871398B1 (fr) * | 2004-06-15 | 2006-09-29 | Snecma Moteurs Sa | Procede de fabrication d'un carter de stator de turbine |
FR2891583B1 (fr) * | 2005-09-30 | 2010-06-18 | Snecma | Turbine comportant des secteurs d'etancheite demontables par l'amont |
US20090096174A1 (en) * | 2007-02-28 | 2009-04-16 | United Technologies Corporation | Blade outer air seal for a gas turbine engine |
FR2914017B1 (fr) * | 2007-03-20 | 2011-07-08 | Snecma | Dispositif d'etancheite pour un circuit de refroidissement, carter inter-turbine en etant equipe et turboreacteur les comportant |
US7811054B2 (en) * | 2007-05-30 | 2010-10-12 | General Electric Company | Shroud configuration having sloped seal |
US8197186B2 (en) * | 2007-06-29 | 2012-06-12 | General Electric Company | Flange with axially extending holes for gas turbine engine clearance control |
US8393855B2 (en) | 2007-06-29 | 2013-03-12 | General Electric Company | Flange with axially curved impingement surface for gas turbine engine clearance control |
US8439639B2 (en) * | 2008-02-24 | 2013-05-14 | United Technologies Corporation | Filter system for blade outer air seal |
FR2933458B1 (fr) * | 2008-07-01 | 2010-09-03 | Snecma | Compresseur axialo-centrifuge a systeme de pilotage |
CN101809252B (zh) * | 2008-08-11 | 2014-11-05 | 三菱重工业株式会社 | 蒸气轮机设备 |
EP2184445A1 (fr) * | 2008-11-05 | 2010-05-12 | Siemens Aktiengesellschaft | Support d'aubes statorique axialement segmenté d'une turbine à gaz |
US8939715B2 (en) * | 2010-03-22 | 2015-01-27 | General Electric Company | Active tip clearance control for shrouded gas turbine blades and related method |
US8668431B2 (en) * | 2010-03-29 | 2014-03-11 | United Technologies Corporation | Seal clearance control on non-cowled gas turbine engines |
FR2965010B1 (fr) * | 2010-09-17 | 2015-02-20 | Snecma | Refroidissement de la paroi exterieure d'un carter de turbine |
ITCO20110060A1 (it) * | 2011-12-12 | 2013-06-13 | Nuovo Pignone Spa | Turbina a vapore, paletta e metodo |
FR2984428B1 (fr) * | 2011-12-19 | 2018-12-07 | Safran Aircraft Engines | Redresseur de compresseur pour turbomachine. |
EP2647796A1 (fr) * | 2012-04-04 | 2013-10-09 | MTU Aero Engines GmbH | Système d'étanchéité pour turbomachine |
US9291061B2 (en) * | 2012-04-13 | 2016-03-22 | General Electric Company | Turbomachine blade tip shroud with parallel casing configuration |
ITTO20120519A1 (it) * | 2012-06-14 | 2013-12-15 | Avio Spa | Turbina a gas per motori aeronautici |
EP2896796B1 (fr) * | 2014-01-20 | 2019-09-18 | Safran Aero Boosters SA | Stator de turbomachine axiale et turbomachine associée |
EP3141705B1 (fr) * | 2015-09-08 | 2018-12-26 | Ansaldo Energia Switzerland AG | Couvercle de rotor de turbine à gaz |
FR3041037B1 (fr) * | 2015-09-15 | 2018-08-17 | Safran Aircraft Engines | Dispositif de ventilation d'un carter de turbine d'une turbomachine |
US10975721B2 (en) | 2016-01-12 | 2021-04-13 | Pratt & Whitney Canada Corp. | Cooled containment case using internal plenum |
US10815824B2 (en) * | 2017-04-04 | 2020-10-27 | General Electric | Method and system for rotor overspeed protection |
US11098649B2 (en) * | 2018-07-19 | 2021-08-24 | The Boeing Company | Self-regulating back-side pressurization system for thermal insulation blankets |
US11015475B2 (en) * | 2018-12-27 | 2021-05-25 | Rolls-Royce Corporation | Passive blade tip clearance control system for gas turbine engine |
RU190280U1 (ru) * | 2019-01-09 | 2019-06-25 | Публичное Акционерное Общество "Одк-Сатурн" | Устройство для фиксации сегментов сопловых лопаток в силовом корпусе статора турбины |
FR3098849B1 (fr) * | 2019-07-16 | 2022-10-14 | Safran Aircraft Engines | Carter amélioré de module d’aéronef |
CN112302729B (zh) * | 2019-07-31 | 2022-10-11 | 中国航发商用航空发动机有限责任公司 | 航空发动机涡轮静子组件及航空发动机 |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
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US4131388A (en) * | 1977-05-26 | 1978-12-26 | United Technologies Corporation | Outer air seal |
GB2076071A (en) * | 1980-05-16 | 1981-11-25 | United Technologies Corp | Flow directing assembly for a gas turbine engine |
GB2115487A (en) * | 1982-02-19 | 1983-09-07 | Gen Electric | Double wall compressor casing |
US5145316A (en) * | 1989-12-08 | 1992-09-08 | Rolls-Royce Plc | Gas turbine engine blade shroud assembly |
US5180281A (en) * | 1990-09-12 | 1993-01-19 | United Technologies Corporation | Case tying means for gas turbine engine |
FR2683851A1 (fr) * | 1991-11-20 | 1993-05-21 | Snecma | Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor. |
EP0618349A1 (fr) * | 1993-03-31 | 1994-10-05 | ROLLS-ROYCE plc | Boîtier de turbine pour turbine à gaz |
EP0651139A1 (fr) * | 1993-10-27 | 1995-05-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator |
US5653581A (en) * | 1994-11-29 | 1997-08-05 | United Technologies Corporation | Case-tied joint for compressor stators |
Family Cites Families (9)
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GB1501916A (en) * | 1975-06-20 | 1978-02-22 | Rolls Royce | Matching thermal expansions of components of turbo-machines |
US4019320A (en) * | 1975-12-05 | 1977-04-26 | United Technologies Corporation | External gas turbine engine cooling for clearance control |
US4522559A (en) * | 1982-02-19 | 1985-06-11 | General Electric Company | Compressor casing |
GB2117843B (en) * | 1982-04-01 | 1985-11-06 | Rolls Royce | Compressor shrouds |
FR2635562B1 (fr) * | 1988-08-18 | 1993-12-24 | Snecma | Anneau de stator de turbine associe a un support de liaison au carter de turbine |
GB2226365B (en) * | 1988-12-22 | 1993-03-10 | Rolls Royce Plc | Turbomachine clearance control |
DE4442157A1 (de) * | 1994-11-26 | 1996-05-30 | Abb Management Ag | Verfahren und Vorrichtung zur Beeinflussung des Radialspieles der Beschaufelung in axialdurchströmten Verdichtern |
FR2766232B1 (fr) * | 1997-07-18 | 1999-08-20 | Snecma | Dispositif de refroidissement ou d'echauffement d'un carter circulaire |
US6179560B1 (en) * | 1998-12-16 | 2001-01-30 | United Technologies Corporation | Turbomachinery module with improved maintainability |
-
2001
- 2001-08-30 FR FR0111232A patent/FR2829176B1/fr not_active Expired - Fee Related
-
2002
- 2002-08-28 CA CA2457892A patent/CA2457892C/fr not_active Expired - Fee Related
- 2002-08-28 RU RU2004109232/06A patent/RU2324057C2/ru not_active IP Right Cessation
- 2002-08-28 WO PCT/FR2002/002948 patent/WO2003018962A1/fr active Application Filing
- 2002-08-28 UA UA2004021459A patent/UA76185C2/uk unknown
- 2002-08-28 CN CNB02816816XA patent/CN1325765C/zh not_active Expired - Fee Related
- 2002-08-28 US US10/486,831 patent/US7070387B2/en not_active Expired - Lifetime
- 2002-08-28 JP JP2003523797A patent/JP4279667B2/ja not_active Expired - Fee Related
- 2002-08-29 EP EP02292127A patent/EP1288444B1/fr not_active Expired - Lifetime
- 2002-08-29 DE DE60201718T patent/DE60201718T2/de not_active Expired - Lifetime
- 2002-08-29 ES ES02292127T patent/ES2229067T3/es not_active Expired - Lifetime
-
2004
- 2004-02-17 MA MA27534A patent/MA26137A1/fr unknown
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4131388A (en) * | 1977-05-26 | 1978-12-26 | United Technologies Corporation | Outer air seal |
GB2076071A (en) * | 1980-05-16 | 1981-11-25 | United Technologies Corp | Flow directing assembly for a gas turbine engine |
GB2115487A (en) * | 1982-02-19 | 1983-09-07 | Gen Electric | Double wall compressor casing |
US5145316A (en) * | 1989-12-08 | 1992-09-08 | Rolls-Royce Plc | Gas turbine engine blade shroud assembly |
US5180281A (en) * | 1990-09-12 | 1993-01-19 | United Technologies Corporation | Case tying means for gas turbine engine |
FR2683851A1 (fr) * | 1991-11-20 | 1993-05-21 | Snecma | Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor. |
EP0618349A1 (fr) * | 1993-03-31 | 1994-10-05 | ROLLS-ROYCE plc | Boîtier de turbine pour turbine à gaz |
EP0651139A1 (fr) * | 1993-10-27 | 1995-05-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator |
US5653581A (en) * | 1994-11-29 | 1997-08-05 | United Technologies Corporation | Case-tied joint for compressor stators |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7234920B2 (en) * | 2004-04-05 | 2007-06-26 | Snecma Moteurs | Turbine casing having refractory hooks and obtained by a powder metallurgy method |
GB2614760A (en) * | 2022-01-13 | 2023-07-19 | Rolls Royce Plc | Turbine for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
EP1288444A1 (fr) | 2003-03-05 |
JP4279667B2 (ja) | 2009-06-17 |
CN1325765C (zh) | 2007-07-11 |
FR2829176B1 (fr) | 2005-06-24 |
ES2229067T3 (es) | 2005-04-16 |
DE60201718D1 (de) | 2004-12-02 |
MA26137A1 (fr) | 2004-04-01 |
US20040184912A1 (en) | 2004-09-23 |
CA2457892C (fr) | 2011-02-08 |
EP1288444B1 (fr) | 2004-10-27 |
US7070387B2 (en) | 2006-07-04 |
CN1549887A (zh) | 2004-11-24 |
UA76185C2 (uk) | 2006-07-17 |
CA2457892A1 (fr) | 2003-03-06 |
FR2829176A1 (fr) | 2003-03-07 |
JP2005501192A (ja) | 2005-01-13 |
DE60201718T2 (de) | 2006-02-09 |
RU2324057C2 (ru) | 2008-05-10 |
RU2004109232A (ru) | 2005-05-20 |
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