EP1288444A1 - Attachement des éléments de stator dans le carter d'une turbomachine - Google Patents
Attachement des éléments de stator dans le carter d'une turbomachine Download PDFInfo
- Publication number
- EP1288444A1 EP1288444A1 EP20020292127 EP02292127A EP1288444A1 EP 1288444 A1 EP1288444 A1 EP 1288444A1 EP 20020292127 EP20020292127 EP 20020292127 EP 02292127 A EP02292127 A EP 02292127A EP 1288444 A1 EP1288444 A1 EP 1288444A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- hooks
- rings
- stator
- casing
- envelope
- 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
- 238000007789 sealing Methods 0.000 claims description 11
- 238000007664 blowing Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 8
- 238000009413 insulation Methods 0.000 description 7
- 210000003462 vein Anatomy 0.000 description 5
- 238000009423 ventilation Methods 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000969 carrier Substances 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
- 238000003466 welding Methods 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
- F01D11/14—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 room includes hooks to support floor-bearing rings of fixed vanes.
- These hooks extend the structure of the casing close to the gas vein and so are subject to much higher temperatures than the envelope.
- the unfavorable situation of square brackets obliges to take special precautions for protect from overheating, at the cost of a great complication of the structure of the machine to this place and without complete success being achieved, hooks can still require repairs early.
- the invention relates to a housing improved, both less expensive, easier to build, more sustainable, to the structure rather simplified and which requires less protection against heat.
- stator housing comprising an envelope and stator ring hooks on an inner face of the envelope, characterized in that the hooks are separate from the envelope, joined to the envelope by means of assembly and extend only to circle sectors. It follows from this definition that the continuous structure casing is abandoned and the hooks become pieces that are brought back to the envelope.
- the hooks are of a single genus and with enlarged ends; they each support a stator ring carrying vanes fixed, and are divided into circular rows in number identical to said carrier stator rings fixed vanes; they can then understand ring ends housing grooves alternating with the stator rings fixed blade carriers.
- FIG. 1 illustrates a conception of the prior art
- the figures 2 and 3 represent two possible embodiments of the invention
- the stator of a known kind of Figure 1 has a casing 1 consisting of an envelope 2 and hooks that can be found essentially two kinds: flat hooks 3 and hooks with heel 4 alternating along the axis of the machine. All hooks 3 and 4 are circular and connected to the casing 2 by a wing 5 without structural discontinuity. They wear rings of stator 6 and sealing rings 7 alternating which together form a lining of the housing by isolating it a vein 8 gas flow of the machine. These rings 6 and 7 are composed of ring areas juxtaposed and joined by sealing tabs housed in grooves next to the sectors adjacent.
- the stator rings 6 carry vanes fixed and comprise a base plate 10 provided with hooks 11 and 12 on the front and back side outside.
- the sealing rings 7 carry seals 13 of abradable material extending in front of the ends of moving blades 14 and comprise a base plates 15 ending at the front in a hook 16 and an inner hook 17. These hooks 16 and 17 are arranged to frame the heel 18 hooks 4 while retaining the rear hooks 12 stator rings 6 on said hooks 4.
- the base plates 15 sealing rings 7 lean back on the single 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 allows to cover hooks 3 and 4 by the ends of the rings 6 and 7, without exposing them directly at the high temperature of the vein gases 8. But this protection is not enough, all the more less than hot gas leaks to the casing 1 remain possible despite the seals can provide, in particular between the angular sectors rings 6 and 7: we must in practice refresh the casing 1 by a fresh air flow of ventilation taken from another part of the machine and that is blown into the rooms delimited by the envelope 2, the hooks 3 and 4 and the rings 6 and 7.
- the casing 21 of FIG. previously an outer envelope 22 and brackets 23 and 24 of different kinds alternating the along the machine and which still serve to support stator rings 26 and sealing 27 alternating them as well ; but square brackets 23 and 24 show the particularities (reference is also made to Figure 4) of only extend over sectors of the circle, but to be divided into circular rows, and to understand each of the tenons 28 crossing respective mortises 29 of the envelope 22.
- the fixation boxes 23 and 24 to the envelope 22 is made by shrinking, welding or bolting.
- hooks 23 and 24 will be well resistant alloys well to warming up (and possibly different depending on the location of the hook considered and the temperature surrounding), which was excluded before; and the envelope 22 will be in a more ordinary alloy, less expensive and easier to shape. It is to highlight that the greater ease of manufacture offered by the separate fabrications of the envelope 22 and hooks 23 and 24 is another source of economy.
- hooks 24 may be different or not heel hooks 4 and include a pair of grooves 30 and 31 opposite; the concept of the stator rings 26 is similar to the previous 6 rings, as well as for sealing rings 27.
- the hooks 24 which replace hooks 4 are now exposed to the gases of the vein 8, but this is not harmful now that we have the ability to build them out of a material sufficiently heat resistant, such as the M509 (KC24NWTZ) for a temperature above 900 ° C or the RENE77 (NK15CADT) for a lower temperature.
- the outer shell 22 can be protected by a lining comprising an inner skin 33 and a heat insulation 34 between the inner skin 33 and the envelope 22.
- the inner skin 33 and the thermal insulation 34 can be easily installed by operating recesses allowing the hooks 23 and 24 of the to cross. Since hooks 23 and 24 do not form continuous circles, the inner skin 33 and the heat insulation 34 remain in one piece and can so be easily installed and maintained without special precautions even if the inner skin 33 is a fairly flexible metal sheet: you can example press it on the sealing rings 27.
- Insulation 34 offers protection passive against the heat that does not contribute to refresh hooks 23 and 24, unlike a ventilation system ; but some hooks more refractory often do not need to be refreshed, while heat insulation 34 can be easily modeled closely around hooks 23 and 24, which eliminates hot gas leaks to the envelope 22; it offers the added benefit of extend, like the inner skin 33, in front of junctions of the sectors of rings 26 and 27 and replace the seals installed there and whose we can now do without: the sectors of rings 26 and 27 will then be juxtaposed with games, their edges being simple, devoid of grooves or other means for accommodating intermediate joints, and vein gas leaks will be tolerated up to the inner skin 33.
- heat insulation 34 is a preferred means of protecting the envelope 22; he is not incompatible with a reduced refra ⁇ ch ordinance hooks 23 and 24 (by a system that will be discussed further), but we can go back to a breakdown active if insufficient: the inner skin 33 subsist to stop hot gas leaks and channel the ventilation air in the meantime now empty between it and the envelope 22.
- the housing design 39 of FIG. differs substantially from the previous one in that the brackets of two kinds are replaced by brackets 40 of a single genus each of which includes an end widened dovetail or tee to support a respective stator ring 41 which is provided on its side outside of two hooks 42 and 43 turned one towards the other and who commit to the enlargements of the end of the brackets 40.
- hooks 40 and the stator rings 41 are located at same cross-sections of the machine and that each stator ring 41 is supported by a single row of hooks 40; this solution has two times less of hooks than the previous ones, and the rings 7 and 27 are replaced by rings 44 wider, with 45 base plates without hooks and whose ends are either placed on the hooks 42 and 43 of the stator rings 41, or enter grooves 46 hooks 40.
- the hooks 40 are provided with pairs of pins 47 crossing mortises 48 corresponding to a outer casing 49 of the casing 39. It is still possible install an internal skin 50 provided with a thermal insulation 51 to isolate the envelope 49.
- a function to satisfy very often in the turbomachines is a radial game piloting so to improve the efficiency of the machine to some regimes.
- air blowing devices which consist of perforated annular ramps 52 surrounding the housing 39, and disposed at best in front of its most massive parts, here formed by the rows of hooks 40.
- Ramps 52 are powered by a distributor 53 which divides towards each of them, and the air blowing out ramps 52 to through holes 54 oriented towards the pins 47 of the hooks 40. Cooling more or less energetic operation on the casing 39 makes it possible to adjust its temperature and its corresponding dilatation, and therefore the games between the tips of the blades and the devices sealing including rings 44.
- a sheet 55 surrounding the housing 39 can be added to channel the blowing air to an outlet; if she completely covers the ramps 52, the appearance of the device is improved.
- This device designed primarily for piloting games, presents the ability to be as can be used to ventilate hooks directly 40 thanks to the blowing on the pins 47, as well as envelope 49 slipping on it; in this mode of particular achievement, it only requires a number reduced by 52 because of the decrease in the number of rows of hooks.
- a similar device could equip the embodiment of Figure 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 (8)
- Carter (21, 39) de stator comprenant une enveloppe (22, 41) et des crochets d'anneaux (26, 27, 41, 44) sur une face interne de l'enveloppe, les crochets (23, 24, 40) étant distincts de l'enveloppe, unis à l'enveloppe par des moyens d'assemblage et ne s'étendant que sur des secteurs de cercle, caractérisé en ce que les crochets sont munis de rainures opposées (30, 31) de soutien d'au moins deux des anneaux, les anneaux étant composés d'anneaux d'étanchéité alternant avec des anneaux de stator porteurs d'aubes fixes, les anneaux de stator étant unis aux crochets par des portions s'étendant sur leur côté extérieur.
- Carter de stator selon la revendication 1, caractérisé en ce que les anneaux sont assemblés à certains des crochets (24) de manière à laisser partiellement exposés lesdits crochets, une des rainures soutenant un des anneaux d'étanchéité et l'autre des rainures soutenant un des anneaux de stator.
- Carter de stator selon la revendication 1, caractérisé en ce que les crochets (40) sont d'un genre unique à extrémités élargies, soutiennent chaucun un anneau de stator (41) porteur d'aubes fixes, et sont répartis en rangées circulaires en nombre identique auxdits anneaux de stator porteurs d'aubes fixes, les anneaux d'étanchéité ayant des extrémités qui soit sont posées sur des portions des anneaux de stator soutenus par les crochets, soit engagées dans les rainures des crochets.
- Carter de stator selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les moyens d'assemblage comprennent un ou plusieurs tenons pour chaque crochet et des mortaises (48) opérées dans l'enveloppe et occupées par les tenons (47).
- Carter de stator selon la revendication 4, caractérisé en ce que les tenons traversent l'enveloppe et qu'un système de soufflage d'air par des rampes circulaires (52) entoure l'enveloppe, les rampes (52) étant perforées (53) devant les tenons (47).
- Carter de stator selon l'une quelconque des revendications 1 à 5, caractérisé en ce que les crochets et l'enveloppe sont en matières différentes.
- Carter de stator selon l'une quelconque des revendications 1 à 6, caractérisé en ce qu'il comprend une peau (33) interne à l'enveloppe, séparée d'elle par un intervalle et formée d'une feuille continue mais traversée par les crochets à des endroits où elle est percée.
- Carter selon la revendication 7, caractérisé en ce qu'un corps de calorifugeage (34) emplit l'intervalle.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0111232 | 2001-08-30 | ||
FR0111232A FR2829176B1 (fr) | 2001-08-30 | 2001-08-30 | Carter de stator de turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1288444A1 true EP1288444A1 (fr) | 2003-03-05 |
EP1288444B1 EP1288444B1 (fr) | 2004-10-27 |
Family
ID=8866814
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02292127A Expired - Lifetime EP1288444B1 (fr) | 2001-08-30 | 2002-08-29 | Attachement des éléments de stator dans le carter d'une 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 (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2868467A1 (fr) * | 2004-04-05 | 2005-10-07 | Snecma Moteurs Sa | Carter de turbine a crochets refractaires obtenu par procede mdp |
FR2871398A1 (fr) * | 2004-06-15 | 2005-12-16 | Snecma Moteurs Sa | Procede de fabrication d'un carter de stator de turbine |
EP2009251A3 (fr) * | 2007-06-29 | 2011-01-05 | General Electric Company | Carter annulaire de turbine d'un moteur à turbine à gaz et ensemble turbine associé |
FR2965010A1 (fr) * | 2010-09-17 | 2012-03-23 | Snecma | Refroidissement de la paroi exterieure d'un carter de turbine |
US8393855B2 (en) | 2007-06-29 | 2013-03-12 | General Electric Company | Flange with axially curved impingement surface for gas turbine engine clearance control |
EP2896796A1 (fr) * | 2014-01-20 | 2015-07-22 | Techspace Aero S.A. | Stator de turbomachine axiale et turbomachine associée |
FR3098849A1 (fr) * | 2019-07-16 | 2021-01-22 | Safran Aircraft Engines | Carter amélioré de module d’aéronef |
Families Citing this family (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10359730A1 (de) * | 2003-12-19 | 2005-07-14 | Mtu Aero Engines Gmbh | Turbomaschine, insbesondere Gasturbine |
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 |
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 |
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 |
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 |
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 |
GB2614760A (en) * | 2022-01-13 | 2023-07-19 | Rolls Royce Plc | Turbine for gas turbine engine |
Citations (7)
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 |
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 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US5180281A (en) * | 1990-09-12 | 1993-01-19 | United Technologies Corporation | Case tying means for gas turbine engine |
DE4442157A1 (de) * | 1994-11-26 | 1996-05-30 | Abb Management Ag | Verfahren und Vorrichtung zur Beeinflussung des Radialspieles der Beschaufelung in axialdurchströmten Verdichtern |
US5653581A (en) | 1994-11-29 | 1997-08-05 | United Technologies Corporation | Case-tied joint for compressor stators |
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 (7)
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 |
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 |
Cited By (13)
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 |
GB2412949A (en) * | 2004-04-05 | 2005-10-12 | Snecma Moteurs | Turbine stator casing formed by hot isostatic compression |
FR2868467A1 (fr) * | 2004-04-05 | 2005-10-07 | Snecma Moteurs Sa | Carter de turbine a crochets refractaires obtenu par procede mdp |
GB2412949B (en) * | 2004-04-05 | 2008-01-09 | Snecma Moteurs | Turbine casing having refractory hooks and obtained by powder metallurgy method |
US7687021B2 (en) | 2004-06-15 | 2010-03-30 | Snecma | Method of fabricating a casing for turbine stator |
EP1607158A1 (fr) * | 2004-06-15 | 2005-12-21 | Snecma | Procédé de fabrication d'un carter de stator de turbine |
FR2871398A1 (fr) * | 2004-06-15 | 2005-12-16 | Snecma Moteurs Sa | Procede de fabrication d'un carter de stator de turbine |
EP2009251A3 (fr) * | 2007-06-29 | 2011-01-05 | General Electric Company | Carter annulaire de turbine d'un moteur à turbine à gaz et ensemble turbine associé |
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 |
FR2965010A1 (fr) * | 2010-09-17 | 2012-03-23 | Snecma | Refroidissement de la paroi exterieure d'un carter de turbine |
EP2896796A1 (fr) * | 2014-01-20 | 2015-07-22 | Techspace Aero S.A. | Stator de turbomachine axiale et turbomachine associée |
FR3098849A1 (fr) * | 2019-07-16 | 2021-01-22 | Safran Aircraft Engines | Carter amélioré de module d’aéronef |
Also Published As
Publication number | Publication date |
---|---|
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 |
WO2003018962A1 (fr) | 2003-03-06 |
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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