JP4157038B2 - 高圧タービン用ブレード冷却スクープ - Google Patents
高圧タービン用ブレード冷却スクープ Download PDFInfo
- Publication number
- JP4157038B2 JP4157038B2 JP2003538532A JP2003538532A JP4157038B2 JP 4157038 B2 JP4157038 B2 JP 4157038B2 JP 2003538532 A JP2003538532 A JP 2003538532A JP 2003538532 A JP2003538532 A JP 2003538532A JP 4157038 B2 JP4157038 B2 JP 4157038B2
- Authority
- JP
- Japan
- Prior art keywords
- turbine
- cooling air
- air
- cooling
- engine
- 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
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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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- 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
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/322—Arrangement of components according to their shape tangential
-
- 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
- F05D2250/50—Inlet or outlet
- F05D2250/51—Inlet
-
- 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
Description
Claims (8)
- ガスタービンエンジン用のタービンブレード冷却システムであり、エンジンが単段高仕事率高圧タービンを有し、冷却システムは、
エンジンに画定された高温ガス通路と、
エンジンの圧縮機セクションから得られた圧縮空気の供給源と連通する冷却空気プレナムと、
タービンアセンブリーとを有し、該アセンブリーはローターと該ローターに取り付けられた複数のタービンブレードとを有し、ブレードは冷却空気プレナムにさらされた根部と、高温ガス通路にさらされたエアフォイル部と、を有し、
根部は入口スクープ部分を備える冷却空気入口ダクトを有し、
エアフォイル部は、内部に画定された冷却空気チャンネルを有し、この冷却空気チャンネルは冷却空気入口ダクトとエンジンの高温ガス通路に連通する空気出口手段との間に延びているとともに、冷却空気プレナムから冷却空気入口ダクト中に分流された空気をチャンネルを介して空気出口手段に通過させ、かくしてタービンブレードを冷却するよう設けられており、
入口スクープ部分は、タービンブレードから冷却空気プレナム内に軸方向でかつ径方向内側に延びているとともに、根部の底面の径方向内側に位置する入口スクープ開口部を有しており、この入口スクープ開口部は、タービン回転の結果として冷却空気が冷却空気プレナムから空気入口ダクト中に分流されるようにタービンの回転方向でかつ接線方向に開口していることを特徴とするガスタービンエンジン用のタービンブレード冷却システム。 - 入口スクープ開口部は、タービンの回転軸に向かう径方向成分をさらに含むよう方向づけられている、請求項1記載のタービンブレード冷却システム。
- 冷却空気入口ダクトは根部に取り付けられている、請求項1または2に記載のタービンブレード冷却システム。
- ブレード根部はラビリンスシール部材を含む、請求項1〜3のいずれかに記載のタービンブレード冷却システム。
- さらにタービンシャフトを収容するためのベアリングギャラリーを有し、このベアリングギャラリーは、エンジンの圧縮機セクションから得られた圧縮空気の供給源に連通する冷却空気ジャケットを含み、この冷却空気ジャケットはまた冷却空気プレナムと連通しており、かくして冷却ジャケットに供給された空気は冷却空気プレナムに流れることができる、請求項1〜4のいずれかに記載のタービンブレード冷却システム。
- 前記圧縮空気がエンジンのP3空気圧より低い圧力を有する、請求項1〜5のいずれかに記載のタービンブレード冷却システム。
- 前記圧縮空気が圧縮機セクションの中間段から抽気される、請求項1〜6のいずれかに記載のタービンブレード冷却システム。
- ガスタービンエンジン内の単段高仕事率高圧タービンのタービンブレードを冷却する方法であって、
入口スクープ部分を備える冷却空気入口ダクトを設け、
冷却空気供給源から空気を分流して、この冷却空気を入口ダクトからブレード内部に画定されたチャネルに通過させ、
前記冷却空気をチャンネルからガスタービンエンジンの高温ガス通路に排出する、ことを含み、
入口スクープ部分は、タービンブレードの根部から軸方向でかつ径方向内側に延びるとともに、根部の底面の径方向内側に位置する開口部を備え、この開口部は、タービン回転の結果として冷却空気供給源から空気をすくい取るようにタービンの回転方向でかつ接線方向に開口していることを特徴とする方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/039,945 US6735956B2 (en) | 2001-10-26 | 2001-10-26 | High pressure turbine blade cooling scoop |
PCT/CA2002/001575 WO2003036048A1 (en) | 2001-10-26 | 2002-10-18 | High pressure turbine blade cooling scoop |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005506484A JP2005506484A (ja) | 2005-03-03 |
JP4157038B2 true JP4157038B2 (ja) | 2008-09-24 |
Family
ID=21908214
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2003538532A Expired - Fee Related JP4157038B2 (ja) | 2001-10-26 | 2002-10-18 | 高圧タービン用ブレード冷却スクープ |
Country Status (6)
Country | Link |
---|---|
US (1) | US6735956B2 (ja) |
EP (1) | EP1444417B1 (ja) |
JP (1) | JP4157038B2 (ja) |
CA (1) | CA2464414C (ja) |
DE (1) | DE60228301D1 (ja) |
WO (1) | WO2003036048A1 (ja) |
Families Citing this family (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1312865A1 (de) * | 2001-11-15 | 2003-05-21 | Siemens Aktiengesellschaft | Ringbrennkammer für eine Gasturbine |
FR2851010B1 (fr) * | 2003-02-06 | 2005-04-15 | Snecma Moteurs | Dispositif de ventilation d'un rotor de turbine a haute pression d'une turbomachine |
US7192245B2 (en) * | 2004-12-03 | 2007-03-20 | Pratt & Whitney Canada Corp. | Rotor assembly with cooling air deflectors and method |
US8016561B2 (en) | 2006-07-11 | 2011-09-13 | General Electric Company | Gas turbine engine fan assembly and method for assembling to same |
US8100633B2 (en) * | 2008-03-11 | 2012-01-24 | United Technologies Corp. | Cooling air manifold splash plates and gas turbines engine systems involving such splash plates |
US8221083B2 (en) * | 2008-04-15 | 2012-07-17 | United Technologies Corporation | Asymmetrical rotor blade fir-tree attachment |
US8282354B2 (en) * | 2008-04-16 | 2012-10-09 | United Technologies Corporation | Reduced weight blade for a gas turbine engine |
US8464835B2 (en) * | 2008-08-15 | 2013-06-18 | Rolls-Royce Corporation | Lubricant scoop |
CN101832154B (zh) * | 2009-03-11 | 2013-03-27 | 中国科学院工程热物理研究所 | 一种航空发动机涡轮叶片气膜冷却方法 |
US8113784B2 (en) * | 2009-03-20 | 2012-02-14 | Hamilton Sundstrand Corporation | Coolable airfoil attachment section |
EP2236746A1 (en) * | 2009-03-23 | 2010-10-06 | Alstom Technology Ltd | Gas turbine |
WO2011005858A2 (en) * | 2009-07-09 | 2011-01-13 | Frontline Aerospace, Inc. | Compressor cooling for turbine engines |
DE102009055880A1 (de) * | 2009-11-26 | 2011-06-01 | Rolls-Royce Deutschland Ltd & Co Kg | Fluggasturbine mit flammengesicherter Lageranordnung |
CH703827A1 (de) | 2010-09-20 | 2012-03-30 | Alstom Technology Ltd | Gasturbinenanordnung mit einer Ringdichtungsanordnung für einen Ringraum zwischen wenigstens einer stationären Komponente und einer Rotoreinheit. |
US9091173B2 (en) | 2012-05-31 | 2015-07-28 | United Technologies Corporation | Turbine coolant supply system |
EP2725191B1 (en) * | 2012-10-23 | 2016-03-16 | Alstom Technology Ltd | Gas turbine and turbine blade for such a gas turbine |
US10247098B2 (en) | 2013-05-10 | 2019-04-02 | United Technologies Corporation | Diffuser case strut for a turbine engine |
US10167723B2 (en) | 2014-06-06 | 2019-01-01 | United Technologies Corporation | Thermally isolated turbine section for a gas turbine engine |
US10634055B2 (en) | 2015-02-05 | 2020-04-28 | United Technologies Corporation | Gas turbine engine having section with thermally isolated area |
US9920652B2 (en) | 2015-02-09 | 2018-03-20 | United Technologies Corporation | Gas turbine engine having section with thermally isolated area |
US9957897B2 (en) | 2015-03-19 | 2018-05-01 | United Technologies Corporation | Gimbal tube systems for tangential onboard injectors |
US9850760B2 (en) | 2015-04-15 | 2017-12-26 | Honeywell International Inc. | Directed cooling for rotating machinery |
DE102015111746A1 (de) * | 2015-07-20 | 2017-01-26 | Rolls-Royce Deutschland Ltd & Co Kg | Gekühltes Turbinenlaufrad, insbesondere für ein Flugtriebwerk |
US10107109B2 (en) | 2015-12-10 | 2018-10-23 | United Technologies Corporation | Gas turbine engine component cooling assembly |
US10260523B2 (en) | 2016-04-06 | 2019-04-16 | Rolls-Royce North American Technologies Inc. | Fluid cooling system integrated with outlet guide vane |
CN107448240A (zh) * | 2016-05-31 | 2017-12-08 | 中国航发商用航空发动机有限责任公司 | 核心机和涡轮发动机 |
FR3067387B1 (fr) * | 2017-06-07 | 2019-06-28 | Safran Aircraft Engines | Ecope d'alimentation en air pour l'alimentation d'un systeme de refroidissement et de controle des jeux d'une turbine |
US10662812B2 (en) * | 2017-10-20 | 2020-05-26 | United Technologies Corporation | Lubricant scoop |
US10808572B2 (en) * | 2018-04-02 | 2020-10-20 | General Electric Company | Cooling structure for a turbomachinery component |
US11220922B1 (en) * | 2020-06-17 | 2022-01-11 | Honeywell International Inc. | Monolithic diffuser and deswirl flow structure for gas turbine engine |
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-
2001
- 2001-10-26 US US10/039,945 patent/US6735956B2/en not_active Expired - Lifetime
-
2002
- 2002-10-18 EP EP02801822A patent/EP1444417B1/en not_active Expired - Fee Related
- 2002-10-18 DE DE60228301T patent/DE60228301D1/de not_active Expired - Lifetime
- 2002-10-18 JP JP2003538532A patent/JP4157038B2/ja not_active Expired - Fee Related
- 2002-10-18 CA CA2464414A patent/CA2464414C/en not_active Expired - Fee Related
- 2002-10-18 WO PCT/CA2002/001575 patent/WO2003036048A1/en active IP Right Grant
Also Published As
Publication number | Publication date |
---|---|
JP2005506484A (ja) | 2005-03-03 |
DE60228301D1 (de) | 2008-09-25 |
WO2003036048A1 (en) | 2003-05-01 |
US6735956B2 (en) | 2004-05-18 |
US20030079478A1 (en) | 2003-05-01 |
EP1444417A1 (en) | 2004-08-11 |
CA2464414A1 (en) | 2003-05-01 |
CA2464414C (en) | 2010-05-11 |
EP1444417B1 (en) | 2008-08-13 |
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