EP0892152A1 - Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt - Google Patents
Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt Download PDFInfo
- Publication number
- EP0892152A1 EP0892152A1 EP98401800A EP98401800A EP0892152A1 EP 0892152 A1 EP0892152 A1 EP 0892152A1 EP 98401800 A EP98401800 A EP 98401800A EP 98401800 A EP98401800 A EP 98401800A EP 0892152 A1 EP0892152 A1 EP 0892152A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- tubes
- distributors
- gas
- networks
- housing
- 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
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
-
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
- F05D2250/141—Two-dimensional elliptical circular
Definitions
- the invention relates to a device for cooling or heating of a housing circular.
- a device already used consists of have two networks of semicircular tubes around of the casing, each of the networks therefore extending over a half circumference of the housing and being powered by a conduit, which is connected to a distributor box connected to each of the pipes in the network, in the middle of their length.
- the gas therefore disperses in the tubes of the network by traversing them towards their ends at from the middle, and leaves them by borrowing orifices directed towards the housing.
- This construction explains that these tubes are called "necklaces of shower”.
- the known device Like the known device, it includes a gas distribution network in distributors connecting to networks of tubes surrounding the casing on respective parts of the circumferences; at place where a distributor is connected in the middle of tube networks, two distributors are arranged at ends of the networks, each of these two distributors connecting to a respective group of tubes of the considered network: the gas flows through the two groups of tubes in opposite directions, which balances heat gain around the circumference, each generator of the casing being subjected to a double gas blowing, the first of which originates from one of network tube groups, is hotter as the other, from the other group, is fresher.
- conduits opening into a pair of distributors are connected to a link occupying half of their section and extending to at least one of the sockets in passing through a stop surface of said socket.
- This last duct slightly penetrates into the duct more wide of the distribution network, therefore recovers the half of the bit rate that comes out and transmits this half of flow to the distributor located beyond the socket liaison; the other half of the gas flow comes out of the distribution duct around the connecting duct and enters the other dispenser.
- the connecting pipe having a section half less than that of the duct distribution, to which it is connected with play, completes the system, the aim of which is to equalize heating or cooling.
- a possible improvement consists in provide the device with a flow control valve heating or cooling gas, which is controlled by a calculator or function of the regimes reached by the machine.
- a flow control valve heating or cooling gas which is controlled by a calculator or function of the regimes reached by the machine.
- it is particularly advantageous to reduce the gas flow blown during start-up: if a large flow is delivered from this moment, while the machine is still cold, the housing heats up much more slowly as the rotor and its blades, whose ends expand to the point of rubbing against the inner wall of the housing.
- This wall is normally filled with a layer of soft material, called abradable, which erodes under the effect of friction and prevents damage to the rotor blades, but play reappearing between them and the abradable layer now eroded is increased when the housing is heated and expanded in turn. It is therefore a question of avoiding this result.
- abradable a layer of soft material
- the device illustrated as a whole at Figure 1, has substantially the shape of a crown that we have to imagine placed around a housing cylindrical or conical shown elsewhere.
- This crown is essentially composed of three networks of tubes 1, identical and each extending over a third of the circumference of the housing thus forming an almost entirely continuous surface.
- Each of the tube networks 1 includes six parallel tubes 2 and as an extension from one network to another and is completed by two distributor boxes 3 to which branch their tubes 2, which gives three pairs distributor boxes 3 adjacent to the limits of the three tube networks 1.
- the housings distributors 3 and the tubes 2 are supplied with gas heating or cooling by a network of conduits first comprising a single conduit 4 which is splits into a first conduit 5 which goes towards a first pair of distributor boxes 3, at the top in the figure, and in a second conduit 6 which itself splits into two conduits, one of which extends over 7 the lower right of the figure and supplies a second pair of enclosures dispensers 3 at this location, while the other is not visible in the figure but extends behind one of the tube networks 1 to connect to the third pair of distributor boxes 3, also invisible but located behind the lower left of the figure.
- the ducts are chosen so that the three pairs of distributor boxes 3 are supplied by equal gas flows at the same temperature: the lengths of conduit to travel to achieve each pair of housings are all equal, the single duct 4 dividing at the junction of two networks of tubes 1, and conduit 6 in the middle of one of these two networks of tubes 1; the conduit 5 extends over about a third of the circumference of the housing, and the duct 6 on a sixth in circumference, as well as the two conduits in which it splits.
- Figure 2 shows that the tube networks 1 are composed of two corrugated sheets 8 turned over and joined so that their corrugations 9 are opposite and come face to face to form the tubes 2.
- the corrugated sheets 8 have flat portions 10 adjoining corrugations 9, in contact when the 8 sheets are assembled and riveted or united by a other way.
- the tubes 2 are provided with orifices 11 directed to casing 12 to project gas there heating or cooling. This gas builds up in an annular chamber 13 delimited by the casing 12 and tube networks 1 but can escape from it by additional orifices 14 formed through adjoining portions 10.
- Figure 3 shows that the gas distribution each lead into one of the distributor boxes 3 adjacent pairs mentioned above and their content is spreading first in this distributor box 3 before a half goes into the other distributor box 3 in passing through a cuff 17 which joins them.
- the six tubes 2 of tube networks 1 are alternately connected to one of the opposite 3 distributor boxes and located at the ends of these networks, so that the gas flows through three of tubes 2 in one direction and in the other three tubes 2 in the direction opposite: the gas heats up in tubes 2 as in the anterior device and therefore exits through the orifices 11 at increasing temperatures away from distributor boxes, but if we consider a generator of the casing 12, it receives gas from three tubes 2 having traveled a relatively long way and gas from three tubes 2 having traveled a path relatively short, i.e. both gas strongly heated and weakly heated gas and therefore a practically uniform quantity of heat: the object of the invention is thus achieved.
- the housings distributors 3 have protrusions 18 to the exterior and in extension, and that the conduits feed such as 5 and 7 end up in the alignment of these protrusions 18 and penetrate into one of them.
- the protrusions 18 each contain a socket 19 which partially delimits them, the sockets 19 being facing facing and connected by one of the cuffs 17; the cuff 17 is terminated by two spherical portions 20, open at their opposite ends 21 and which are able to roll and slide on the internal surface of sockets 19.
- Tube networks 1 and sockets 19 can therefore move mutually without producing more than a rotation or a sliding movement of the cuff 17 in sockets 19, and without sealing and even less the connection between distributor boxes 3 is broken.
- the cuff 17 must obviously be inserted sufficiently into the sockets 19 so that its extraction is impossible even if the networks of tubes 1 deviate; through elsewhere, the sockets 19 are provided with surfaces stop 22 which surround the cuff 17 and him prohibit moving indefinitely in the same direction, because it would come up against them.
- the surfaces stop 22 include a central opening 23 for allow the entry of gas into the boxes distributors 3.
- a connecting tube 24 is welded to one of these openings 23, and the other of the openings is free.
- the connecting tube 24 is connected to the conduit power supply such as 5 occupying only the half of its section, which guarantees the passage of the half of the gas flow in the distributor box 3 opposite, on the left in the figure, by the connecting tube 24, while the other half of the flow stops against the sleeve 19 and is forced back into the tubes 2 of the distributor 3 on the right.
- gas flow can be controlled by a progressive opening valve 25, controlled by a computer 26 depending on the speed reached, for adjust the gas flow rate supplied to the device and therefore the expansion undergone by the casing 12.
- the computer 26 can be informed by speed sensors, temperature, pressure, etc. who measure quantities present in the machine, and it uses these measurements using empirically established tables or formulas.
- We finally figured point 27 of sampling gas through the supply line 4 it's about usually from a point in the gas flow stream of the machine, from which part of the flow is withdrawn, in a manner widely known in the art.
- the invention will especially find utility on turbomachine turbines, where the hotter gases that elsewhere make it more necessary.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
- Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
- Pipeline Systems (AREA)
- Quick-Acting Or Multi-Walled Pipe Joints (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9709137A FR2766232B1 (fr) | 1997-07-18 | 1997-07-18 | Dispositif de refroidissement ou d'echauffement d'un carter circulaire |
FR9709137 | 1997-07-18 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0892152A1 true EP0892152A1 (de) | 1999-01-20 |
EP0892152B1 EP0892152B1 (de) | 2003-07-09 |
Family
ID=9509363
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98401800A Expired - Lifetime EP0892152B1 (de) | 1997-07-18 | 1998-07-17 | Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt |
Country Status (12)
Country | Link |
---|---|
US (1) | US6149074A (de) |
EP (1) | EP0892152B1 (de) |
JP (1) | JP3474206B2 (de) |
KR (1) | KR100545340B1 (de) |
CN (1) | CN1199003C (de) |
CA (1) | CA2266343A1 (de) |
DE (1) | DE69816190T2 (de) |
ES (1) | ES2205410T3 (de) |
FR (1) | FR2766232B1 (de) |
RU (1) | RU2210674C2 (de) |
UA (1) | UA46126C2 (de) |
WO (1) | WO1999004142A1 (de) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1577501A1 (de) * | 2004-03-18 | 2005-09-21 | Snecma | Hochdruckturbinenstator einer Strömungsmaschine und deren Zusammenbauverfahren |
EP1577502A1 (de) * | 2004-03-18 | 2005-09-21 | Snecma | Einrichtung um die Spaltweite zwischen den Schaufelspitzen und dem Gehäuse einer Gasturbine zu Steuern |
FR2965010A1 (fr) * | 2010-09-17 | 2012-03-23 | Snecma | Refroidissement de la paroi exterieure d'un carter de turbine |
EP3284917A1 (de) * | 2016-08-18 | 2018-02-21 | United Technologies Corporation | Aktiver spielsteuerungskollektor für einen verteilereinsatz |
Families Citing this family (46)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1079068A3 (de) * | 1999-08-27 | 2004-01-07 | General Electric Company | Verbindungsmuffe für den Kühlkreislauf eines Turbinenrotors |
JP4274666B2 (ja) * | 2000-03-07 | 2009-06-10 | 三菱重工業株式会社 | ガスタービン |
US6454529B1 (en) * | 2001-03-23 | 2002-09-24 | General Electric Company | Methods and apparatus for maintaining rotor assembly tip clearances |
FR2829176B1 (fr) * | 2001-08-30 | 2005-06-24 | Snecma Moteurs | Carter de stator de turbomachine |
DE102005035540A1 (de) * | 2005-07-29 | 2007-02-01 | Mtu Aero Engines Gmbh | Vorrichtung zur aktiven Spaltkontrolle für eine Strömungsmaschine |
US7597537B2 (en) * | 2005-12-16 | 2009-10-06 | General Electric Company | Thermal control of gas turbine engine rings for active clearance control |
KR100674118B1 (ko) * | 2006-07-07 | 2007-01-24 | (주)씨앤스페이스 | 로켓 추진용 메탄엔진 |
US8801370B2 (en) * | 2006-10-12 | 2014-08-12 | General Electric Company | Turbine case impingement cooling for heavy duty gas turbines |
US8393855B2 (en) * | 2007-06-29 | 2013-03-12 | General Electric Company | Flange with axially curved impingement surface for gas turbine engine clearance control |
US8197186B2 (en) * | 2007-06-29 | 2012-06-12 | General Electric Company | Flange with axially extending holes for gas turbine engine clearance control |
EP2112335A1 (de) * | 2008-04-21 | 2009-10-28 | Siemens Aktiengesellschaft | Dampfturbine mit Kühlvorrichtung |
FR2977276B1 (fr) * | 2011-06-30 | 2016-12-09 | Snecma | Agencement pour le raccordement d'un conduit a un boitier de distribution d'air |
JP5609795B2 (ja) * | 2011-07-12 | 2014-10-22 | 株式会社デンソー | 車両用過給装置 |
US9664062B2 (en) * | 2011-12-08 | 2017-05-30 | Siemens Energy, Inc. | Gas turbine engine with multiple component exhaust diffuser operating in conjunction with an outer case ambient external cooling system |
US20130149107A1 (en) * | 2011-12-08 | 2013-06-13 | Mrinal Munshi | Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow |
US8894359B2 (en) * | 2011-12-08 | 2014-11-25 | Siemens Aktiengesellschaft | Gas turbine engine with outer case ambient external cooling system |
US10094285B2 (en) * | 2011-12-08 | 2018-10-09 | Siemens Aktiengesellschaft | Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity |
RU2495256C1 (ru) * | 2012-04-12 | 2013-10-10 | Николай Борисович Болотин | Турбина газотурбинного двигателя |
RU2506435C2 (ru) * | 2012-05-11 | 2014-02-10 | Николай Борисович Болотин | Газотурбинный двигатель и способ регулирования радиального зазора в турбине газотурбинного двигателя |
RU2499894C1 (ru) * | 2012-05-11 | 2013-11-27 | Николай Борисович Болотин | Двухконтурный газотурбинный двигатель |
RU2496991C1 (ru) * | 2012-05-21 | 2013-10-27 | Николай Борисович Болотин | Турбина двухконтурного газотурбинного двигателя |
RU2499145C1 (ru) * | 2012-05-21 | 2013-11-20 | Николай Борисович Болотин | Турбина двухконтурного газотурбинного двигателя |
ITTO20120519A1 (it) * | 2012-06-14 | 2013-12-15 | Avio Spa | Turbina a gas per motori aeronautici |
RU2501956C1 (ru) * | 2012-07-31 | 2013-12-20 | Николай Борисович Болотин | Двухконтурный газотурбинный двигатель, способ регулирования радиального зазора в турбине двухконтурного газотурбинного двигателя |
FR3002971B1 (fr) * | 2013-03-06 | 2015-04-17 | Snecma | Dispositif de ventilation d'un carter de stator d'une turbomachine, comprenant un ajustement sur des circonferences |
FR3002972B1 (fr) * | 2013-03-06 | 2015-04-17 | Snecma | Dispositif de ventilation d'un carter de stator d'une turbomachine comprenant un ajustement en direction axiale |
EP2789803A1 (de) * | 2013-04-09 | 2014-10-15 | Siemens Aktiengesellschaft | Aufprallringelementbefestigung und -abdichtung |
RU2519127C1 (ru) * | 2013-04-24 | 2014-06-10 | Николай Борисович Болотин | Турбина газотурбинного двигателя и способ регулирования радиального зазора в турбине |
EP2987966A1 (de) * | 2014-08-21 | 2016-02-24 | Siemens Aktiengesellschaft | Gasturbine mit in Ringsektoren unterteiltem Kühlringkanal |
US10378379B2 (en) | 2015-08-27 | 2019-08-13 | General Electric Company | Gas turbine engine cooling air manifolds with spoolies |
FR3041037B1 (fr) * | 2015-09-15 | 2018-08-17 | Safran Aircraft Engines | Dispositif de ventilation d'un carter de turbine d'une turbomachine |
FR3050228B1 (fr) * | 2016-04-18 | 2019-03-29 | Safran Aircraft Engines | Dispositif de refroidissement par jets d'air d'un carter de turbine |
FR3058459B1 (fr) * | 2016-11-04 | 2018-11-09 | Safran Aircraft Engines | Dispositif de refroidissement pour une turbine d'une turbomachine |
FR3067751B1 (fr) | 2017-06-15 | 2019-07-12 | Safran Aircraft Engines | Dispositif de refroidissement d'un carter annulaire externe de turbine |
US10914187B2 (en) * | 2017-09-11 | 2021-02-09 | Raytheon Technologies Corporation | Active clearance control system and manifold for gas turbine engine |
RU2673924C1 (ru) * | 2017-10-17 | 2018-12-03 | Акционерное общество "ОДК-Авиадвигатель" | Статор газовой турбины |
FR3073007B1 (fr) * | 2017-10-27 | 2019-09-27 | Safran Aircraft Engines | Dispositif de maintien d'un tube de refroidissement pour carter de turbomachine |
FR3082872B1 (fr) | 2018-06-25 | 2021-06-04 | Safran Aircraft Engines | Dispositif de refroidissement d'un carter de turbomachine |
FR3085719B1 (fr) * | 2018-09-06 | 2021-04-16 | Safran Aircraft Engines | Boitier d'alimentation en air sous pression d'un dispositif de refroidissement par jets d'air |
FR3089545B1 (fr) * | 2018-12-07 | 2021-01-29 | Safran Aircraft Engines | Dispositif de refroidissement d’un carter de turbine pour une turbomachine |
FR3096084B1 (fr) * | 2019-05-16 | 2021-04-16 | Safran Aircraft Engines | Procédé et dispositif d’estimation d’une zone morte d’une vanne de décharge de turbomachine |
FR3101104B1 (fr) * | 2019-09-23 | 2021-09-03 | Safran Aircraft Engines | Dispositif de refroidissement par jets d’air d’un carter de turbine |
US11255264B2 (en) | 2020-02-25 | 2022-02-22 | General Electric Company | Frame for a heat engine |
US11560843B2 (en) | 2020-02-25 | 2023-01-24 | General Electric Company | Frame for a heat engine |
US11326519B2 (en) | 2020-02-25 | 2022-05-10 | General Electric Company | Frame for a heat engine |
FR3112811B1 (fr) * | 2020-07-23 | 2022-07-22 | Safran Aircraft Engines | Turbine à cavités pressurisées |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2402841A (en) * | 1944-06-26 | 1946-06-25 | Allis Chalmers Mfg Co | Elastic fluid turbine apparatus |
US4019320A (en) * | 1975-12-05 | 1977-04-26 | United Technologies Corporation | External gas turbine engine cooling for clearance control |
US4280792A (en) * | 1979-02-09 | 1981-07-28 | Avco Corporation | Air-cooled turbine rotor shroud with restraints |
EP0492865A1 (de) * | 1990-12-21 | 1992-07-01 | General Electric Company | Regelungssystem für das Schaufelspitzenspiel einer Turbine |
EP0541325A1 (de) * | 1991-11-04 | 1993-05-12 | General Electric Company | Thermische Steuerung eines Gehäuses eines Gasturbinentriebwerks |
EP0559420A1 (de) * | 1992-03-06 | 1993-09-08 | General Electric Company | Thermisch gesteuerter Regelflansch für eine Gasturbine |
US5399066A (en) * | 1993-09-30 | 1995-03-21 | General Electric Company | Integral clearance control impingement manifold and environmental shield |
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US2801821A (en) * | 1953-02-05 | 1957-08-06 | Bbc Brown Boveri & Cie | Cooled turbine casing |
US3218799A (en) * | 1963-02-05 | 1965-11-23 | Thiokol Chemical Corp | Rocket thrust chamber construction |
US4412782A (en) * | 1979-03-28 | 1983-11-01 | United Technologies Corporation | Full hoop bleed manifolds for longitudinally split compressor cases |
US4525998A (en) * | 1982-08-02 | 1985-07-02 | United Technologies Corporation | Clearance control for gas turbine engine |
US4643638A (en) * | 1983-12-21 | 1987-02-17 | United Technologies Corporation | Stator structure for supporting an outer air seal in a gas turbine engine |
FR2766231B1 (fr) * | 1997-07-18 | 1999-08-20 | Snecma | Dispositif d'echauffement ou de refroidissement d'un carter circulaire |
-
1997
- 1997-07-18 FR FR9709137A patent/FR2766232B1/fr not_active Expired - Fee Related
-
1998
- 1998-07-17 US US09/147,829 patent/US6149074A/en not_active Expired - Fee Related
- 1998-07-17 CN CNB988010046A patent/CN1199003C/zh not_active Expired - Fee Related
- 1998-07-17 RU RU99107657/06A patent/RU2210674C2/ru not_active IP Right Cessation
- 1998-07-17 UA UA99041974A patent/UA46126C2/uk unknown
- 1998-07-17 WO PCT/FR1998/001572 patent/WO1999004142A1/fr active IP Right Grant
- 1998-07-17 JP JP50659799A patent/JP3474206B2/ja not_active Expired - Fee Related
- 1998-07-17 CA CA002266343A patent/CA2266343A1/en not_active Abandoned
- 1998-07-17 ES ES98401800T patent/ES2205410T3/es not_active Expired - Lifetime
- 1998-07-17 KR KR1019997002266A patent/KR100545340B1/ko not_active IP Right Cessation
- 1998-07-17 DE DE69816190T patent/DE69816190T2/de not_active Expired - Fee Related
- 1998-07-17 EP EP98401800A patent/EP0892152B1/de not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2402841A (en) * | 1944-06-26 | 1946-06-25 | Allis Chalmers Mfg Co | Elastic fluid turbine apparatus |
US4019320A (en) * | 1975-12-05 | 1977-04-26 | United Technologies Corporation | External gas turbine engine cooling for clearance control |
US4280792A (en) * | 1979-02-09 | 1981-07-28 | Avco Corporation | Air-cooled turbine rotor shroud with restraints |
EP0492865A1 (de) * | 1990-12-21 | 1992-07-01 | General Electric Company | Regelungssystem für das Schaufelspitzenspiel einer Turbine |
EP0541325A1 (de) * | 1991-11-04 | 1993-05-12 | General Electric Company | Thermische Steuerung eines Gehäuses eines Gasturbinentriebwerks |
EP0559420A1 (de) * | 1992-03-06 | 1993-09-08 | General Electric Company | Thermisch gesteuerter Regelflansch für eine Gasturbine |
US5399066A (en) * | 1993-09-30 | 1995-03-21 | General Electric Company | Integral clearance control impingement manifold and environmental shield |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1577501A1 (de) * | 2004-03-18 | 2005-09-21 | Snecma | Hochdruckturbinenstator einer Strömungsmaschine und deren Zusammenbauverfahren |
EP1577502A1 (de) * | 2004-03-18 | 2005-09-21 | Snecma | Einrichtung um die Spaltweite zwischen den Schaufelspitzen und dem Gehäuse einer Gasturbine zu Steuern |
FR2867805A1 (fr) * | 2004-03-18 | 2005-09-23 | Snecma Moteurs | Stator de turbine haute-pression de turbomachine et procede d'assemblage |
FR2867806A1 (fr) * | 2004-03-18 | 2005-09-23 | Snecma Moteurs | Dispositif de pilotage de jeu de turbine a gaz a equilibrage des debits d'air |
US7309209B2 (en) | 2004-03-18 | 2007-12-18 | Snecma Moteurs | Device for tuning clearance in a gas turbine, while balancing air flows |
US7360987B2 (en) | 2004-03-18 | 2008-04-22 | Snecma | Stator of a high-pressure turbine of a turbomachine, and a method of assembling it |
FR2965010A1 (fr) * | 2010-09-17 | 2012-03-23 | Snecma | Refroidissement de la paroi exterieure d'un carter de turbine |
EP3284917A1 (de) * | 2016-08-18 | 2018-02-21 | United Technologies Corporation | Aktiver spielsteuerungskollektor für einen verteilereinsatz |
EP3757353A1 (de) * | 2016-08-18 | 2020-12-30 | Raytheon Technologies Corporation | Einsatz für einen kollektor eines aktiven spielsteuerungskollektor eines flugzeugmotors |
Also Published As
Publication number | Publication date |
---|---|
JP2001500947A (ja) | 2001-01-23 |
UA46126C2 (uk) | 2002-05-15 |
DE69816190D1 (de) | 2003-08-14 |
WO1999004142A1 (fr) | 1999-01-28 |
RU2210674C2 (ru) | 2003-08-20 |
US6149074A (en) | 2000-11-21 |
DE69816190T2 (de) | 2004-05-27 |
KR20000068582A (ko) | 2000-11-25 |
JP3474206B2 (ja) | 2003-12-08 |
FR2766232A1 (fr) | 1999-01-22 |
KR100545340B1 (ko) | 2006-01-24 |
FR2766232B1 (fr) | 1999-08-20 |
CA2266343A1 (en) | 1999-01-28 |
CN1234847A (zh) | 1999-11-10 |
CN1199003C (zh) | 2005-04-27 |
EP0892152B1 (de) | 2003-07-09 |
ES2205410T3 (es) | 2004-05-01 |
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