JP4559751B2 - ガスタービンエンジンのタービンノズルの二又状インピンジメントバッフル - Google Patents
ガスタービンエンジンのタービンノズルの二又状インピンジメントバッフル Download PDFInfo
- Publication number
- JP4559751B2 JP4559751B2 JP2004050705A JP2004050705A JP4559751B2 JP 4559751 B2 JP4559751 B2 JP 4559751B2 JP 2004050705 A JP2004050705 A JP 2004050705A JP 2004050705 A JP2004050705 A JP 2004050705A JP 4559751 B2 JP4559751 B2 JP 4559751B2
- Authority
- JP
- Japan
- Prior art keywords
- airfoil
- segment
- turbine nozzle
- nozzle segment
- bipartite
- 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.)
- Expired - Fee Related
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
-
- 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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
-
- 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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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
- F05D2260/30—Retaining components in desired mutual position
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
4 第2段タービンノズル
6 長手方向中心軸線
9 高圧タービン第2段ロータブレード
10 ノズルセグメント
14 環状ケーシング
18 高圧タービン第1段ロータブレード
24 外側バンドセグメント
26 内側バンドセグメント
28 中空ベーン翼形部
30 二又状インピンジメントバッフル
39 二分割リブ
58 クロスオーバ孔
77 第1のシュラウド支持体
79 第2のシュラウド支持体
97 第1のシュラウド
99 第2のシュラウド
107 前方フック
110 スプーリ
112 環状プレナム
LE 翼形部前縁
TE 翼形部後縁
Claims (11)
- 半径方向外側及び内側バンドセグメント(24及び26)間で半径方向に延びる少なくとも1つの中空翼形部(28)を含み、
前記翼形部が、前記半径方向外側及び内側バンドセグメント(24及び26)の周方向に間隔を置いた正圧及び負圧側端部(33及び35)間に配置され、
前記翼形部が、正圧及び負圧側面(22及び23)を備えた翼形部壁(29)を有し、
前記翼形部壁(29)が、二分割された空洞(37)を囲み、
前記翼形部壁(29)の正圧及び負圧側面(22及び23)間で前記二分割空洞(37)を貫通して延びて、該二分割空洞(37)を前方及び後方空洞(41及び43)に分割する二分割リブ(39)が設けられ、
その間にギャップ(57)を備えた軸方向前方及び後方チャンバ(53及び55)を含む二又状インピンジメントバッフル(30)が設けられ、
それぞれ前記前方及び後方チャンバ(53及び55)の前方及び後方バッフル壁(73及び75)を貫通するインピンジメント孔(70)が設けられ、
前記前方及び後方チャンバ(53及び55)と流体流連通したプレナムチャンバ(105)が設けられ、
前記前方及び後方チャンバ(53及び55)に取付けられ、前記プレナムチャンバ(105)を囲うプレナムチャンバ囲壁(108)が設けられ、
前記前方及び後方チャンバ(53及び55)が、それぞれ前記前方及び後方空洞(41及び43)内に配置されている、
ことを特徴とするタービンノズルセグメント(10)。 - 前記プレナムチャンバ(105)への単一の冷却空気入口(114)を更に含むことを特徴とする、請求項1に記載のタービンノズルセグメント(10)。
- 前記プレナムチャンバ囲壁(108)と前記前方及び後方チャンバ(53及び55)との間に取付けられ、該プレナムチャンバ囲壁(108)と該前方及び後方チャンバ(53及び55)とに対してシールされたシールプレート(109)と、を含み、
前記シールプレート(109)が、それぞれ前記プレナムチャンバ(105)と前記前方及び後方チャンバ(53及び55)との間に配置された前方及び後方入口開口部(131及び133)を有する、
ことを特徴とする、請求項2に記載のタービンノズルセグメント(10)。 - 前記前方及び後方チャンバ(53及び55)の半径方向内端部(111)をそれぞれ塞ぐ前方及び後方端部プレート(113及び115)を更に備えることを特徴とする、請求項1に記載のタービンノズルセグメント(10)。
- 前記前方端部プレート(113)内に設けられた出口開口部(117)と、前記出口開口部(117)を貫通して配置された段間シール空洞供給管(119)とを更に備えることを特徴とする、請求項4に記載のタービンノズルセグメント(10)。
- 請求項6の一部
前記二分割リブ(39)を貫通する少なくとも1つのクロスオーバ孔(58)を更に備えることを特徴とする、請求項1に記載のタービンノズルセグメント(10)。 - 前記外側バンドセグメント(24)の半径方向外側面(62)から該半径方向外側面(62)に沿って半径方向外向きに延び、かつ該外側バンドセグメント(24)の正圧側前方コーナ部(64)から前記二分割リブ(39)まで軸方向かつ周方向向きに延びる補強リブ(60)を更に備えることを特徴とする、請求項1に記載のタービンノズルセグメント(10)。
- 前記補強リブ(60)が、前記二分割リブ(39)と軸方向かつ周方向向きに整列されていることを特徴とする、請求項7に記載のタービンノズルセグメント(10)。
- 前記二分割リブ(39)を貫通する複数のクロスオーバ孔(58)を更に含むことを特徴とする、請求項8に記載のタービンノズルセグメント(10)。
- 前記補強リブ(60)が、前記翼形部(28)に加わる合成ガス荷重の方向(63)と整列されていることを特徴とする、請求項8に記載のタービンノズルセグメント(10)。
- 前記翼形部(28)と前記外側バンドセグメント(24)との接合部の周りで延びる翼形部フィレット(91)と、前記二分割リブ(39)が前記翼形部(28)の正圧側面(22)と交わる位置における前記翼形部フィレット(91)の拡大部(93)とを更に含むことを特徴とする、請求項10に記載のタービンノズルセグメント(10)。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/375,415 US7008185B2 (en) | 2003-02-27 | 2003-02-27 | Gas turbine engine turbine nozzle bifurcated impingement baffle |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2004257390A JP2004257390A (ja) | 2004-09-16 |
JP2004257390A5 JP2004257390A5 (ja) | 2007-04-12 |
JP4559751B2 true JP4559751B2 (ja) | 2010-10-13 |
Family
ID=32771457
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2004050705A Expired - Fee Related JP4559751B2 (ja) | 2003-02-27 | 2004-02-26 | ガスタービンエンジンのタービンノズルの二又状インピンジメントバッフル |
Country Status (4)
Country | Link |
---|---|
US (1) | US7008185B2 (ja) |
EP (1) | EP1452690A3 (ja) |
JP (1) | JP4559751B2 (ja) |
CN (2) | CN1525048B (ja) |
Families Citing this family (58)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2858829B1 (fr) * | 2003-08-12 | 2008-03-14 | Snecma Moteurs | Aube refroidie de moteur a turbine a gaz |
US7270515B2 (en) * | 2005-05-26 | 2007-09-18 | Siemens Power Generation, Inc. | Turbine airfoil trailing edge cooling system with segmented impingement ribs |
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 |
US7921654B1 (en) * | 2007-09-07 | 2011-04-12 | Florida Turbine Technologies, Inc. | Cooled turbine stator vane |
FR2922597B1 (fr) * | 2007-10-19 | 2012-11-16 | Snecma | Aube refroidie de turbomachine |
US7946801B2 (en) * | 2007-12-27 | 2011-05-24 | General Electric Company | Multi-source gas turbine cooling |
US8016547B2 (en) * | 2008-01-22 | 2011-09-13 | United Technologies Corporation | Radial inner diameter metering plate |
US20090220331A1 (en) * | 2008-02-29 | 2009-09-03 | General Electric Company | Turbine nozzle with integral impingement blanket |
US8172504B2 (en) | 2008-03-25 | 2012-05-08 | General Electric Company | Hybrid impingement cooled airfoil |
US20090293495A1 (en) * | 2008-05-29 | 2009-12-03 | General Electric Company | Turbine airfoil with metered cooling cavity |
US8043062B2 (en) * | 2008-09-04 | 2011-10-25 | Mitsubishi Heavy Industries, Ltd. | Turbine rotor and turbine having the same |
US8152451B2 (en) * | 2008-11-29 | 2012-04-10 | General Electric Company | Split fairing for a gas turbine engine |
US8727725B1 (en) * | 2009-01-22 | 2014-05-20 | Florida Turbine Technologies, Inc. | Turbine vane with leading edge fillet region cooling |
JP2010190057A (ja) * | 2009-02-16 | 2010-09-02 | Ihi Corp | タービンの設計方法及びタービン |
US20110107769A1 (en) * | 2009-11-09 | 2011-05-12 | General Electric Company | Impingement insert for a turbomachine injector |
US9347324B2 (en) * | 2010-09-20 | 2016-05-24 | Siemens Aktiengesellschaft | Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles |
US20120070302A1 (en) * | 2010-09-20 | 2012-03-22 | Ching-Pang Lee | Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles |
EP2469029A1 (en) | 2010-12-22 | 2012-06-27 | Siemens Aktiengesellschaft | Impingement cooling of gas turbine blades or vanes |
US8628294B1 (en) * | 2011-05-19 | 2014-01-14 | Florida Turbine Technologies, Inc. | Turbine stator vane with purge air channel |
FR2976616B1 (fr) * | 2011-06-17 | 2015-01-09 | Snecma | Systeme de ventilation pour une pale creuse d un distributeur de turbine dans une turbomachine |
EP2540969A1 (en) | 2011-06-27 | 2013-01-02 | Siemens Aktiengesellschaft | Impingement cooling of turbine blades or vanes |
US9169782B2 (en) * | 2012-01-04 | 2015-10-27 | General Electric Company | Turbine to operate at part-load |
US9133724B2 (en) | 2012-01-09 | 2015-09-15 | General Electric Company | Turbomachine component including a cover plate |
US8864445B2 (en) * | 2012-01-09 | 2014-10-21 | General Electric Company | Turbine nozzle assembly methods |
US9011079B2 (en) * | 2012-01-09 | 2015-04-21 | General Electric Company | Turbine nozzle compartmentalized cooling system |
US9845691B2 (en) | 2012-04-27 | 2017-12-19 | General Electric Company | Turbine nozzle outer band and airfoil cooling apparatus |
US20140004293A1 (en) * | 2012-06-30 | 2014-01-02 | General Electric Company | Ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component |
FR3000522B1 (fr) * | 2012-12-27 | 2018-11-02 | Safran Aircraft Engines | Dispositif de liaison a double tube |
CA2917765C (en) * | 2013-07-19 | 2020-09-15 | General Electric Company | Turbine nozzle with impingement baffle |
EP3060764B1 (en) * | 2013-10-21 | 2019-06-26 | United Technologies Corporation | Incident tolerant turbine vane cooling |
US9915159B2 (en) | 2014-12-18 | 2018-03-13 | General Electric Company | Ceramic matrix composite nozzle mounted with a strut and concepts thereof |
WO2016133514A1 (en) * | 2015-02-19 | 2016-08-25 | Siemens Aktiengesellschaft | Turbine airfoil with dual wall construction |
US10024172B2 (en) | 2015-02-27 | 2018-07-17 | United Technologies Corporation | Gas turbine engine airfoil |
US9845694B2 (en) * | 2015-04-22 | 2017-12-19 | United Technologies Corporation | Flow directing cover for engine component |
US10253986B2 (en) * | 2015-09-08 | 2019-04-09 | General Electric Company | Article and method of forming an article |
US11230935B2 (en) * | 2015-09-18 | 2022-01-25 | General Electric Company | Stator component cooling |
US10161257B2 (en) | 2015-10-20 | 2018-12-25 | General Electric Company | Turbine slotted arcuate leaf seal |
US10030538B2 (en) * | 2015-11-05 | 2018-07-24 | General Electric Company | Gas turbine engine with a vane having a cooling air turning nozzle |
US10428659B2 (en) | 2015-12-21 | 2019-10-01 | United Technologies Corporation | Crossover hole configuration for a flowpath component in a gas turbine engine |
WO2017125289A1 (en) * | 2016-01-19 | 2017-07-27 | Siemens Aktiengesellschaft | Aerofoil arrangement |
US10519873B2 (en) * | 2016-04-06 | 2019-12-31 | General Electric Company | Air bypass system for rotor shaft cooling |
US10634353B2 (en) | 2017-01-12 | 2020-04-28 | General Electric Company | Fuel nozzle assembly with micro channel cooling |
GB2559739A (en) * | 2017-02-15 | 2018-08-22 | Rolls Royce Plc | Stator vane section |
US20190017392A1 (en) * | 2017-07-13 | 2019-01-17 | General Electric Company | Turbomachine impingement cooling insert |
US10415428B2 (en) * | 2018-01-31 | 2019-09-17 | United Technologies Corporation | Dual cavity baffle |
US10787912B2 (en) | 2018-04-25 | 2020-09-29 | Raytheon Technologies Corporation | Spiral cavities for gas turbine engine components |
US10697309B2 (en) | 2018-04-25 | 2020-06-30 | Raytheon Technologies Corporation | Platform cover plates for gas turbine engine components |
US10767493B2 (en) * | 2019-02-01 | 2020-09-08 | Rolls-Royce Plc | Turbine vane assembly with ceramic matrix composite vanes |
US10883376B2 (en) * | 2019-02-01 | 2021-01-05 | Rolls-Royce Plc | Turbine vane assembly with ceramic matrix composite vanes |
FR3099793B1 (fr) * | 2019-08-06 | 2022-07-29 | Safran Aircraft Engines | tronçon de distributeur de turbine comportant un chemisage interne |
US11572801B2 (en) | 2019-09-12 | 2023-02-07 | General Electric Company | Turbine engine component with baffle |
US11268392B2 (en) | 2019-10-28 | 2022-03-08 | Rolls-Royce Plc | Turbine vane assembly incorporating ceramic matrix composite materials and cooling |
US11319822B2 (en) | 2020-05-06 | 2022-05-03 | Rolls-Royce North American Technologies Inc. | Hybrid vane segment with ceramic matrix composite airfoils |
CN112196627A (zh) * | 2020-09-25 | 2021-01-08 | 中国航发沈阳发动机研究所 | 一种具有冷气导管的涡轮气冷叶片 |
US11536147B2 (en) * | 2021-03-30 | 2022-12-27 | Raytheon Technologies Corporation | Vane arc segment with flange and gusset |
US11746675B2 (en) | 2021-11-23 | 2023-09-05 | Rolls-Royce Corporation | Vane ring assembly for a gas turbine engine with dedicated through-flow vanes |
US11732596B2 (en) | 2021-12-22 | 2023-08-22 | Rolls-Royce Plc | Ceramic matrix composite turbine vane assembly having minimalistic support spars |
WO2024018750A1 (ja) * | 2022-07-19 | 2024-01-25 | 三菱重工業株式会社 | ガスタービン静翼及びガスタービン |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH05156901A (ja) * | 1991-12-02 | 1993-06-22 | Hitachi Ltd | ガスタービン冷却静翼 |
JPH0610704A (ja) * | 1992-04-27 | 1994-01-18 | General Electric Co <Ge> | エアホイル装置 |
JPH0693801A (ja) * | 1992-09-17 | 1994-04-05 | Hitachi Ltd | ガスタービン翼 |
JPH11270353A (ja) * | 1998-03-25 | 1999-10-05 | Hitachi Ltd | ガスタービン及びガスタービンの静翼 |
JP2001098905A (ja) * | 1999-10-01 | 2001-04-10 | General Electric Co <Ge> | 熱電対ガイドチューブを持つタービンノズル段 |
JP2001193408A (ja) * | 1999-12-28 | 2001-07-17 | Toshiba Corp | タービン冷却翼 |
JP2001214706A (ja) * | 2000-02-01 | 2001-08-10 | Mitsubishi Heavy Ind Ltd | ガスタービン蒸気冷却静翼 |
JP2002522683A (ja) * | 1998-08-06 | 2002-07-23 | シーメンス ウエスチングハウス パワー コーポレイション | ガスタービンの蒸気冷却型静翼 |
JP2002256811A (ja) * | 2001-02-16 | 2002-09-11 | General Electric Co <Ge> | ガスタービンのノズル羽根インサート及びその取り付け方法 |
Family Cites Families (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3540810A (en) * | 1966-03-17 | 1970-11-17 | Gen Electric | Slanted partition for hollow airfoil vane insert |
BE755567A (fr) * | 1969-12-01 | 1971-02-15 | Gen Electric | Structure d'aube fixe, pour moteur a turbines a gaz et arrangement de reglage de temperature associe |
BE767972A (fr) * | 1970-06-04 | 1971-12-02 | Westinghouse Electric Corp | Piece encastree pour le refroidissement d'une aube de turbine |
US3715170A (en) * | 1970-12-11 | 1973-02-06 | Gen Electric | Cooled turbine blade |
US4153386A (en) * | 1974-12-11 | 1979-05-08 | United Technologies Corporation | Air cooled turbine vanes |
US4257734A (en) * | 1978-03-22 | 1981-03-24 | Rolls-Royce Limited | Guide vanes for gas turbine engines |
US4297077A (en) * | 1979-07-09 | 1981-10-27 | Westinghouse Electric Corp. | Cooled turbine vane |
IN163070B (ja) * | 1984-11-15 | 1988-08-06 | Westinghouse Electric Corp | |
JP3142850B2 (ja) * | 1989-03-13 | 2001-03-07 | 株式会社東芝 | タービンの冷却翼および複合発電プラント |
US5090866A (en) * | 1990-08-27 | 1992-02-25 | United Technologies Corporation | High temperature leading edge vane insert |
US5516260A (en) * | 1994-10-07 | 1996-05-14 | General Electric Company | Bonded turbine airfuel with floating wall cooling insert |
US5645397A (en) * | 1995-10-10 | 1997-07-08 | United Technologies Corporation | Turbine vane assembly with multiple passage cooled vanes |
US5630700A (en) * | 1996-04-26 | 1997-05-20 | General Electric Company | Floating vane turbine nozzle |
US5813832A (en) * | 1996-12-05 | 1998-09-29 | General Electric Company | Turbine engine vane segment |
JP3495579B2 (ja) * | 1997-10-28 | 2004-02-09 | 三菱重工業株式会社 | ガスタービン静翼 |
DE59906024D1 (de) * | 1998-08-31 | 2003-07-24 | Siemens Ag | Turbinenleitschaufel |
US6158955A (en) * | 1999-06-03 | 2000-12-12 | General Electric Company | Welding method and assembly therefor |
JP3794868B2 (ja) * | 1999-06-15 | 2006-07-12 | 三菱重工業株式会社 | ガスタービン静翼 |
US6227798B1 (en) * | 1999-11-30 | 2001-05-08 | General Electric Company | Turbine nozzle segment band cooling |
US6375415B1 (en) * | 2000-04-25 | 2002-04-23 | General Electric Company | Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment |
US6435814B1 (en) * | 2000-05-16 | 2002-08-20 | General Electric Company | Film cooling air pocket in a closed loop cooled airfoil |
US6468031B1 (en) * | 2000-05-16 | 2002-10-22 | General Electric Company | Nozzle cavity impingement/area reduction insert |
US6382906B1 (en) * | 2000-06-16 | 2002-05-07 | General Electric Company | Floating spoolie cup impingement baffle |
EP1191189A1 (de) * | 2000-09-26 | 2002-03-27 | Siemens Aktiengesellschaft | Gasturbinenschaufel |
US6494677B1 (en) * | 2001-01-29 | 2002-12-17 | General Electric Company | Turbine nozzle segment and method of repairing same |
US6761529B2 (en) * | 2002-07-25 | 2004-07-13 | Mitshubishi Heavy Industries, Ltd. | Cooling structure of stationary blade, and gas turbine |
-
2003
- 2003-02-27 US US10/375,415 patent/US7008185B2/en not_active Expired - Lifetime
-
2004
- 2004-02-26 JP JP2004050705A patent/JP4559751B2/ja not_active Expired - Fee Related
- 2004-02-26 EP EP04251073A patent/EP1452690A3/en not_active Withdrawn
- 2004-02-27 CN CN2004100076473A patent/CN1525048B/zh not_active Expired - Lifetime
- 2004-02-27 CN CN201110170693.5A patent/CN102251814B/zh not_active Expired - Lifetime
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH05156901A (ja) * | 1991-12-02 | 1993-06-22 | Hitachi Ltd | ガスタービン冷却静翼 |
JPH0610704A (ja) * | 1992-04-27 | 1994-01-18 | General Electric Co <Ge> | エアホイル装置 |
JPH0693801A (ja) * | 1992-09-17 | 1994-04-05 | Hitachi Ltd | ガスタービン翼 |
JPH11270353A (ja) * | 1998-03-25 | 1999-10-05 | Hitachi Ltd | ガスタービン及びガスタービンの静翼 |
JP2002522683A (ja) * | 1998-08-06 | 2002-07-23 | シーメンス ウエスチングハウス パワー コーポレイション | ガスタービンの蒸気冷却型静翼 |
JP2001098905A (ja) * | 1999-10-01 | 2001-04-10 | General Electric Co <Ge> | 熱電対ガイドチューブを持つタービンノズル段 |
JP2001193408A (ja) * | 1999-12-28 | 2001-07-17 | Toshiba Corp | タービン冷却翼 |
JP2001214706A (ja) * | 2000-02-01 | 2001-08-10 | Mitsubishi Heavy Ind Ltd | ガスタービン蒸気冷却静翼 |
JP2002256811A (ja) * | 2001-02-16 | 2002-09-11 | General Electric Co <Ge> | ガスタービンのノズル羽根インサート及びその取り付け方法 |
Also Published As
Publication number | Publication date |
---|---|
JP2004257390A (ja) | 2004-09-16 |
CN1525048A (zh) | 2004-09-01 |
EP1452690A2 (en) | 2004-09-01 |
US20040170498A1 (en) | 2004-09-02 |
CN1525048B (zh) | 2012-01-04 |
EP1452690A3 (en) | 2007-02-28 |
CN102251814B (zh) | 2015-03-11 |
US7008185B2 (en) | 2006-03-07 |
CN102251814A (zh) | 2011-11-23 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4559751B2 (ja) | ガスタービンエンジンのタービンノズルの二又状インピンジメントバッフル | |
JP4000121B2 (ja) | 二分割空洞を有する単一の中空ベーンを備えたガスタービンエンジンのタービンノズルセグメント | |
JP4049754B2 (ja) | タービンノズルセグメントの片持ち式支持 | |
JP4513000B2 (ja) | ガスタービンエンジンを組立てるための方法及び装置 | |
JP4658584B2 (ja) | 内側寄り冷却式ノズルダブレット | |
CN106545365B (zh) | 喷嘴节段、喷嘴组件和燃气涡轮发动机 | |
JP4719122B2 (ja) | 逆冷却タービンノズル | |
US5358379A (en) | Gas turbine vane | |
JP4785507B2 (ja) | ブルノーズ段部付きタービンノズル | |
US4126405A (en) | Turbine nozzle | |
US20020159889A1 (en) | Turbine blade having a cooled tip shroud | |
JP2009108857A (ja) | 可撓性翼弦ヒンジシールを有するガスタービン | |
JP2001303905A (ja) | 循環式流体冷却されるガスタービンノズル段セグメントのフック支持体 | |
JP2012102726A (ja) | タービンロータブレードのプラットフォーム領域を冷却するための装置、システム、及び方法 | |
JP5965633B2 (ja) | タービンロータブレードのプラットフォーム領域を冷却するための装置及び方法 | |
CN110832168B (zh) | 用于冲击冷却的涡轮组件及组装方法 | |
JP4341231B2 (ja) | ガスタービンノズルを冷却するための方法と装置 | |
JP2011157962A (ja) | 熱的分離を改善したタービンノズルの保持リング | |
WO2021186796A1 (ja) | 静翼及びガスタービン | |
KR20170128127A (ko) | 에어포일 선행 에지 통로의 후미에서 외벽에 걸쳐 있는 중간 중앙 통로 | |
JP7419014B2 (ja) | 収集プレナムと連通する冷却通路を含むタービンシュラウド | |
CN113710875B (zh) | 涡轮发动机叶片、相关涡轮发动机分配器和涡轮发动机 | |
US11795828B2 (en) | Blade for a turbine engine, associated turbine engine distributor and turbine engine | |
US11572803B1 (en) | Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method | |
JP2022061204A (ja) | ガスタービン静翼 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20070222 |
|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20070222 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20090818 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20091112 |
|
RD02 | Notification of acceptance of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7422 Effective date: 20091112 |
|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20091112 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20091203 |
|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20100215 |
|
TRDD | Decision of grant or rejection written | ||
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20100629 |
|
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20100723 |
|
R150 | Certificate of patent or registration of utility model |
Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130730 Year of fee payment: 3 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
LAPS | Cancellation because of no payment of annual fees |