EP1607580A2 - Plattformkühlanordnung für den Leitschaufelkranz einer Gasturbine - Google Patents
Plattformkühlanordnung für den Leitschaufelkranz einer Gasturbine Download PDFInfo
- Publication number
- EP1607580A2 EP1607580A2 EP05090163A EP05090163A EP1607580A2 EP 1607580 A2 EP1607580 A2 EP 1607580A2 EP 05090163 A EP05090163 A EP 05090163A EP 05090163 A EP05090163 A EP 05090163A EP 1607580 A2 EP1607580 A2 EP 1607580A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- kühlluftausblaskanäle
- platform
- platform cooling
- arrangement according
- cooling arrangement
- 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.)
- Ceased
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- 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
- F01D25/12—Cooling
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
Definitions
- the invention relates to a platform cooling arrangement for the combustion chamber downstream vane ring a gas turbine, with at the periphery of the wall of the combustion chamber, the platforms and / or the wall of one between these arranged intermediate piece the respective wall in at least a continuous or discontinuous series or any other arrangement penetratingde Kunststoffausblaskanälen, via the compressor of the gas turbine branched cooling air for film cooling to the Main gas flow surfaces of the platforms is passed.
- DE 198 13 779 goes from a cooling air blowing called ballistic cooling in a direction corresponding to the radius, the means, in a limited by the turbine axis and the radius Level, under a relatively steep discharge angle to the turbine axis with high momentum ratios, at thede povertyausblas-openings forming the at least one row in Turbinen ownedscardi in from each other spaced groups are arranged, each on a range from the vane leading edge to the whose respective pressure side are limited towards.
- ballistic cooling in each case the pressure side of the vanes restricted area should therefore also in the area behind the three-dimensional Entry boundary layer detachment lying platform surfaces reached by the cooling medium and cooled sufficiently become.
- EP 0 615 055 A1 whose technical teaching is also based on the above-mentioned principle of film cooling or ballistic Cooling of the platforms is based on at least one, in contrast to that described in DE 198 13 779 A1 Solution not interrupted in the circumferential direction Series of blow-out channels, however, to achieve a certain mass flow distribution in the circumferential direction have different diameters to thereby as complete as possible cooling of the platform surface to effect. Also in this cooling arrangement agrees the direction of the exhaust channels, except one certain to penetrate the platform or the Combustion chamber wall required angle of attack, with the the turbine axis and the radius formed plane.
- the invention is based on the object, a platform cooling arrangement specify the type mentioned, the effective cooling of all main gas flow surfaces of the Platform guaranteed.
- the essence of the invention consists in the arrangement at least part of thede povertyausblaskanäle in one of the one formed by the turbine axis and the radius Plane by an angle ⁇ deviating direction.
- that means thede povertyausblaskanäle slanted with respect to the circumferential direction are.
- the oblique orientation the cooling air jets produces a vortex structure in which a reduced hot gas content is absorbed and the is also able to also the platform area behind the three-dimensional boundary layer detachment effectively and in all areas between the pressure side and the suction side to cool the adjacent vanes.
- the means the size of the angle in which the neighboring onesde povertyausblaskanäle are aligned, may vary be and be partially 0 °.
- the circumference ofde povertyausblaskanälen in one or several discontinuous or continuous rows or even in regular or irregular groups or also individually as well as in variable form and Size be formed. Between the adjacent rows or in the same row or group of cooling air exhaust ducts The skew of thedeluftausblaskanäle can be different be.
- the size and / or the shape of the cross section in and same row or with respect to the adjacent rows or in any other arrangement of cooling air exhaust ducts can be different.
- FIGS. 1 and 2 each show a vane 1, between an outer platform 2 and an inner Platform 3 is arranged.
- a plurality of guide vanes 1 with platforms 2, 3 forms a vane ring, the the annular gas outlet opening 5 of a combustion chamber 6 is connected downstream.
- the outer platforms 2 and the inner platforms 3 are shown in FIG. 1 immediately and As shown in FIG. 2 via an intermediate piece 7 with the wall 4 of Combustion chamber 6 connected or at the gas outlet opening 5 connected.
- a emerging from the gas outlet opening 5 Hot gas flow (arrow 8) is between the adjacent Guide vanes 1 and the platforms 2, 3 forwarded. To those due to the high gas temperature thermal loading of the blade and platform material to reduce, the vanes 1 and the platforms 2, 3 cooled.
- the cooling of the platforms, the object The present application is carried out with a Part of the branched off from the compressor (not shown), not used for the combustion process, Cooling air (arrow 9).
- Cooling air arrow 9
- the gas outlet 5 As shown in FIG. 1, in the outer platforms 2 and in the inner wall 4 of the combustion chamber 6 am Circumference distributeddeluftausblaskanäle 10 arranged.
- thedeluftausblaskanäle 10 in the outer Wall 4 of the combustion chamber 6 and in a between the inner platform 3 and the inner wall of the combustion chamber 6 arranged intermediate piece 7 is formed.
- the combustion chamber wall or the intermediate piece Other combinations are possible.
- Thede povertyausblaskanäle 10 are at the periphery of the inner or outer wall 4, the platforms 2, 3 or the intermediate piece 7 in at least one - continuous or discontinuous series (not shown) arranged and can - with several rows - in a line or be offset from each other.
- the cross-sectional area thede povertyausblaskanäle 10 is round or oval, but may also have a different shape.
- Cooling air jet 11 Based on these Cooling air jet 11 is in cooperation with the hot gas stream 8 from the combustion chamber a vortex structure formed, on the one hand, the mixing of the cooling air jets 11 minimized with the hot gas stream 8 and the others covering the entire platform surface with Cooling air, that is, also in the area 12 of the three-dimensional Boundary layer separation downstream of the boundary layer separation line 13 and in particular in the suction side 14 of the vanes 1 adjacent area ensures. This is associated with a reduction in the cooling air requirement and thus an improvement of the emission values, because a larger amount of air for combustion to Available.
- the heat protection coating account for the platform surfaces, so that the corresponding costs are reduced.
- a complex cooling system for dispensed with the acted upon by the hot gas flow surfaces or cooling the passage through the Guide vane can be avoided, so ultimately the specific fuel consumption and the costs are lowered can be.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Fig. 1
- eine Teilansicht der Brennkammer einer Gasturbine mit an die Gasaustrittsöffnung unmittelbar angeschlossenem Leitschaufelsystem;
- Fig. 2
- eine Teilansicht der Brennkammer mit einem zwischen der Gasaustrittsöffnung und dem Leitschaufelsystem angeordneten Zwischenstück;
- Fig. 3
- eine Schnittansicht von jeweils zwei benachbarten, auf einer Plattform angebrachten Leitschaufeln mit einer Gruppe von jeder Leitschaufel zugeordneten, in unterschiedlicher Winkellage in der Plattform verlaufenden Kühlluftausblaskanälen; und
- Fig. 4
- eine geometrische Darstellung der in Bezug auf die Umfangsrichtung winkligen Anordnung der Kühlluftausblaskanäle.
- 1
- Leitschaufel
- 2
- äußere Plattform
- 3
- innere Plattform
- 4
- innere/äußere Wand von 6
- 5
- Gasaustrittsöffnung
- 6
- Brennkammer
- 7
- Zwischenstück
- 8
- Heißgasstrom
- 9
- Kühlluft
- 10
- Kühlluftausblaskanal
- 11
- Kühlluftstrahl
- 12
- Bereich der Grenzschichtablösung
- 13
- Grenzschichttrennlinie
- 14
- Saugseite v. 1
- 15
- Umfangsrichtung
- X
- Turbinenachse
- r
- Radius
- α1, α2
- Ausblaswinkel in Umfangsricht. (zur r, x-Ebene)
Claims (9)
- Plattformkühlanordnung für den der Brennkammer nachgeschalteten Leitschaufelkranz einer Gasturbine, mit am Umfang der Wand der Brennkammer, der Plattformen oder eines zwischen diesen angeordneten Zwischenstücks die jeweilige Wand in mindestens einer kontinuierlichen oder diskontinuierlichen Reihe oder anderen beliebigen Anordnung durchdringenden Kühlluftausblaskanälen, über die vom Verdichter der Gasturbine abgezweigte Kühlluft zur Filmkühlung zu den Hauptgasstromflächen der Plattform geleitet wird, dadurch gekennzeichnet, dass die Kühlluftausblaskanäle (10) bezogen auf die Umfangsrichtung (15) mindestens zu einem Teil in einer um einen bestimmten Winkel (α1, α2) abgewinkelten Richtung angeordnet sind.
- Plattformkühlanordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Winkellage der Kühlluftausblaskanäle (10) in benachbarten Reihen von Kühlluftausblaskanälen gleich oder unterschiedlich ist.
- Plattformkühlanordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Winkellage der Kühlluftausblaskanäle (10) in ein und derselben Reihe gleich oder unterschiedlich ist.
- Plattformkühlanordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Winkellage der Kühlluftausblaskanäle (10) in der beliebigen Anordnung von Kühlluftausblaskanälen (10) gleich oder unterschiedlich ist.
- Plattformkühlanordnung nach Anspruch 2, 3 oder 4, dadurch gekennzeichnet, dass bei unterschiedlichen Winkellagen der Winkel α in ein und derselben Reihe teilweise oder in einer von mehreren Reihen insgesamt 0° beträgt.
- Plattformkühlanordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Kühlluftausblaskanäle (10) in ein und derselben Reihe oder in Bezug auf jeweils benachbarte Reihen versetzt zueinander angeordnet sind.
- Plattformkühlanordnung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Kühlluftausblaskanäle (10) variable Querschnittsformen und/oder - größen haben.
- Plattformkühlanordnung nach Anspruch 7, dadurch gekennzeichnet, dass die Kühlluftausblaskanäle (10) in ein und derselben Reihe bzw. Anordnung oder mit Bezug auf benachbarte Reihen voneinander unterschiedliche Querschnittsformen und/oder -größen haben.
- Plattformkühlanordnung nach Anspruch 1, dadurch gekennzeichnet, dass Hauptgasstromflächen der Plattformen ein einziger Kühlluftausblaskanal (10) vorgesehen ist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004029696 | 2004-06-15 | ||
DE102004029696A DE102004029696A1 (de) | 2004-06-15 | 2004-06-15 | Plattformkühlanordnung für den Leitschaufelkranz einer Gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1607580A2 true EP1607580A2 (de) | 2005-12-21 |
EP1607580A3 EP1607580A3 (de) | 2008-10-01 |
Family
ID=34938466
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05090163A Ceased EP1607580A3 (de) | 2004-06-15 | 2005-06-06 | Plattformkühlanordnung für den Leitschaufelkranz einer Gasturbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US7637716B2 (de) |
EP (1) | EP1607580A3 (de) |
DE (1) | DE102004029696A1 (de) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2728115A1 (de) * | 2012-11-02 | 2014-05-07 | Rolls-Royce plc | Gasturbinenmotor-Endwandkomponente und zugehöriges Verfahren |
EP2871323A1 (de) * | 2013-11-06 | 2015-05-13 | Mitsubishi Hitachi Power Systems, Ltd. | Mantelwandkühlung in einem Gasturbinenleitapparat |
CN105658913A (zh) * | 2013-10-22 | 2016-06-08 | 西门子能源公司 | 用于燃气涡轮发动机燃烧气体管道的结构安装装置 |
EP3059396A1 (de) * | 2015-02-19 | 2016-08-24 | United Technologies Corporation | Gasturbinenmotor und turbinenkonfigurationen |
EP3219918A1 (de) | 2016-03-17 | 2017-09-20 | Rolls-Royce Deutschland Ltd & Co KG | Kühleinrichtung zur kühlung von plattformen eines leitschaufelkranzes einer gasturbine |
RU192446U1 (ru) * | 2019-03-13 | 2019-09-17 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Рыбинский государственный авиационный технический университет имени П.А. Соловьева" | Блок сопловых турбинных лопаток с охлаждаемой несимметричной торцевой полкой |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7762773B2 (en) * | 2006-09-22 | 2010-07-27 | Siemens Energy, Inc. | Turbine airfoil cooling system with platform edge cooling channels |
GB2442967B (en) * | 2006-10-21 | 2011-02-16 | Rolls Royce Plc | An engine arrangement |
DE102007039175A1 (de) | 2007-08-20 | 2009-07-02 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenschaufel |
WO2009083456A2 (de) * | 2007-12-29 | 2009-07-09 | Alstom Technology Ltd | Gasturbine |
DE102008060424A1 (de) * | 2008-12-04 | 2010-06-10 | Rolls-Royce Deutschland Ltd & Co Kg | Strömungsmaschine mit Seitenwand-Grenzschicht-Barriere |
US8727726B2 (en) * | 2009-08-11 | 2014-05-20 | General Electric Company | Turbine endwall cooling arrangement |
GB0919107D0 (en) * | 2009-11-02 | 2009-12-16 | Rolls Royce Plc | A boundary layer energiser |
EP2458148A1 (de) * | 2010-11-25 | 2012-05-30 | Siemens Aktiengesellschaft | Turbomaschinenbauteil mit einer Kühlfläche |
US9234438B2 (en) * | 2012-05-04 | 2016-01-12 | Siemens Aktiengesellschaft | Turbine engine component wall having branched cooling passages |
US9091180B2 (en) | 2012-07-19 | 2015-07-28 | Siemens Energy, Inc. | Airfoil assembly including vortex reducing at an airfoil leading edge |
US20140099190A1 (en) * | 2012-10-05 | 2014-04-10 | Solar Turbines Incorporated | Gas turbine engine turbine housing with enlongated holes |
US8939711B2 (en) | 2013-02-15 | 2015-01-27 | Siemens Aktiengesellschaft | Outer rim seal assembly in a turbine engine |
US9869190B2 (en) | 2014-05-30 | 2018-01-16 | General Electric Company | Variable-pitch rotor with remote counterweights |
US9869183B2 (en) | 2014-08-01 | 2018-01-16 | United Technologies Corporation | Thermal barrier coating inside cooling channels |
US10072510B2 (en) | 2014-11-21 | 2018-09-11 | General Electric Company | Variable pitch fan for gas turbine engine and method of assembling the same |
EP3115556B1 (de) * | 2015-07-10 | 2020-09-23 | Ansaldo Energia Switzerland AG | Gasturbine |
US10100653B2 (en) | 2015-10-08 | 2018-10-16 | General Electric Company | Variable pitch fan blade retention system |
US10684014B2 (en) * | 2016-08-04 | 2020-06-16 | Raytheon Technologies Corporation | Combustor panel for gas turbine engine |
US10774662B2 (en) | 2018-07-17 | 2020-09-15 | Rolls-Royce Corporation | Separable turbine vane stage |
US11674435B2 (en) | 2021-06-29 | 2023-06-13 | General Electric Company | Levered counterweight feathering system |
US11795964B2 (en) | 2021-07-16 | 2023-10-24 | General Electric Company | Levered counterweight feathering system |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB980363A (en) | 1961-12-04 | 1965-01-13 | Jan Jerie | Improvements in or relating to gas turbines |
FR2198054A1 (de) | 1972-09-05 | 1974-03-29 | Gen Electric | |
FR2313551A1 (fr) | 1975-06-02 | 1976-12-31 | United Technologies Corp | Refroidissement d'une aube de turbine |
EP0615055A1 (de) | 1993-03-11 | 1994-09-14 | ROLLS-ROYCE plc | Leitschaufelkühlung |
EP0902164A1 (de) | 1997-09-15 | 1999-03-17 | Asea Brown Boveri AG | Plattformkühlung für Gasturbinen |
DE19813779A1 (de) | 1998-03-27 | 1999-09-30 | Bmw Rolls Royce Gmbh | Anordnung zur Kühlung der Plattformen von Leitschaufeln einer Gasturbine |
Family Cites Families (13)
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US4573865A (en) * | 1981-08-31 | 1986-03-04 | General Electric Company | Multiple-impingement cooled structure |
US4526226A (en) * | 1981-08-31 | 1985-07-02 | General Electric Company | Multiple-impingement cooled structure |
US5382135A (en) * | 1992-11-24 | 1995-01-17 | United Technologies Corporation | Rotor blade with cooled integral platform |
US5344283A (en) * | 1993-01-21 | 1994-09-06 | United Technologies Corporation | Turbine vane having dedicated inner platform cooling |
US6210111B1 (en) * | 1998-12-21 | 2001-04-03 | United Technologies Corporation | Turbine blade with platform cooling |
DE10009655C1 (de) * | 2000-02-29 | 2001-05-23 | Mtu Aero Engines Gmbh | Kühlluftsystem |
US6341939B1 (en) * | 2000-07-31 | 2002-01-29 | General Electric Company | Tandem cooling turbine blade |
US6468032B2 (en) * | 2000-12-18 | 2002-10-22 | Pratt & Whitney Canada Corp. | Further cooling of pre-swirl flow entering cooled rotor aerofoils |
JP4508432B2 (ja) * | 2001-01-09 | 2010-07-21 | 三菱重工業株式会社 | ガスタービンの冷却構造 |
EP1245806B1 (de) * | 2001-03-30 | 2005-08-03 | Siemens Aktiengesellschaft | Gekühlte Gasturbinenschaufel |
US6568187B1 (en) * | 2001-12-10 | 2003-05-27 | Power Systems Mfg, Llc | Effusion cooled transition duct |
US6945749B2 (en) * | 2003-09-12 | 2005-09-20 | Siemens Westinghouse Power Corporation | Turbine blade platform cooling system |
US6887033B1 (en) * | 2003-11-10 | 2005-05-03 | General Electric Company | Cooling system for nozzle segment platform edges |
-
2004
- 2004-06-15 DE DE102004029696A patent/DE102004029696A1/de not_active Withdrawn
-
2005
- 2005-06-06 EP EP05090163A patent/EP1607580A3/de not_active Ceased
- 2005-06-15 US US11/152,791 patent/US7637716B2/en not_active Expired - Fee Related
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB980363A (en) | 1961-12-04 | 1965-01-13 | Jan Jerie | Improvements in or relating to gas turbines |
FR2198054A1 (de) | 1972-09-05 | 1974-03-29 | Gen Electric | |
FR2313551A1 (fr) | 1975-06-02 | 1976-12-31 | United Technologies Corp | Refroidissement d'une aube de turbine |
EP0615055A1 (de) | 1993-03-11 | 1994-09-14 | ROLLS-ROYCE plc | Leitschaufelkühlung |
EP0902164A1 (de) | 1997-09-15 | 1999-03-17 | Asea Brown Boveri AG | Plattformkühlung für Gasturbinen |
DE19813779A1 (de) | 1998-03-27 | 1999-09-30 | Bmw Rolls Royce Gmbh | Anordnung zur Kühlung der Plattformen von Leitschaufeln einer Gasturbine |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2728115A1 (de) * | 2012-11-02 | 2014-05-07 | Rolls-Royce plc | Gasturbinenmotor-Endwandkomponente und zugehöriges Verfahren |
US9512782B2 (en) | 2012-11-02 | 2016-12-06 | Rolls-Royce Plc | Gas turbine engine end-wall component |
CN105658913A (zh) * | 2013-10-22 | 2016-06-08 | 西门子能源公司 | 用于燃气涡轮发动机燃烧气体管道的结构安装装置 |
EP2871323A1 (de) * | 2013-11-06 | 2015-05-13 | Mitsubishi Hitachi Power Systems, Ltd. | Mantelwandkühlung in einem Gasturbinenleitapparat |
US9790799B2 (en) | 2013-11-06 | 2017-10-17 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine airfoil |
EP3059396A1 (de) * | 2015-02-19 | 2016-08-24 | United Technologies Corporation | Gasturbinenmotor und turbinenkonfigurationen |
EP3219918A1 (de) | 2016-03-17 | 2017-09-20 | Rolls-Royce Deutschland Ltd & Co KG | Kühleinrichtung zur kühlung von plattformen eines leitschaufelkranzes einer gasturbine |
DE102016104957A1 (de) | 2016-03-17 | 2017-09-21 | Rolls-Royce Deutschland Ltd & Co Kg | Kühleinrichtung zur Kühlung von Plattformen eines Leitschaufelkranzes einer Gasturbine |
US10669886B2 (en) | 2016-03-17 | 2020-06-02 | Rolls-Royce Deutschland Ltd & Co Kg | Cooling device for cooling platforms of a guide vane ring of a gas turbine |
RU192446U1 (ru) * | 2019-03-13 | 2019-09-17 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Рыбинский государственный авиационный технический университет имени П.А. Соловьева" | Блок сопловых турбинных лопаток с охлаждаемой несимметричной торцевой полкой |
Also Published As
Publication number | Publication date |
---|---|
US20060078417A1 (en) | 2006-04-13 |
EP1607580A3 (de) | 2008-10-01 |
DE102004029696A1 (de) | 2006-01-05 |
US7637716B2 (en) | 2009-12-29 |
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