JP2004076739A - 非交互嵌合二重反転式低圧タービンを備えた航空機用ガスタービンエンジン - Google Patents
非交互嵌合二重反転式低圧タービンを備えた航空機用ガスタービンエンジン Download PDFInfo
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- JP2004076739A JP2004076739A JP2003294855A JP2003294855A JP2004076739A JP 2004076739 A JP2004076739 A JP 2004076739A JP 2003294855 A JP2003294855 A JP 2003294855A JP 2003294855 A JP2003294855 A JP 2003294855A JP 2004076739 A JP2004076739 A JP 2004076739A
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- low pressure
- pressure turbine
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- turbine blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
-
- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
- F01D1/26—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like traversed by the working-fluid substantially axially
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】 第1低圧タービンブレード列(138)は、前記低圧タービン流路(28)に沿って第2低圧タービンブレード列(148)の下流に配置される。回転不能な低圧ベーン(210)の列が、低圧タービン流路(28)を横切って、第1低圧タービンブレード列(138)と第2低圧タービンブレード列(148)との間に配置される。環状のベーンなし間隙(58)が、第2低圧タービンブレード列(148)の最後列(52)と第1低圧タービンブレード列(138)の最前列(50)との間に置くことができる。
【選択図】 図3
Description
10 航空機用ガスタービンエンジン組立体
18 高圧圧縮機
20 燃焼器
29 高圧タービン
25 コアエンジン
26 低圧タービンセクション
27 高圧シャフト
28 低圧タービン流路
32 フレーム構造体
33 高圧ロータ
40 前方低圧タービン
42 後方低圧タービン
45 エンジンケーシング
60 タービン中央フレーム
130 低圧内側シャフト
138 第1低圧タービンブレード列
140 低圧外側シャフト
148 第2低圧タービンブレード列
155 タービン後方フレーム
200 低圧内側シャフトロータ
202 低圧外側シャフトロータ
218 第2の隣接対
219 第1の隣接対
Claims (12)
- 低圧タービン流路(28)と、
タンデム形非交互嵌合二重反転式前方低圧タービン(40)及び後方低圧タービン(42)とを有する低圧タービンセクション(26)と、を含み、
前記後方低圧タービン(42)が前記低圧タービン流路(28)を横切って配置された第1低圧タービンブレード列(138)を含み、
前記前方低圧タービン(40)が前記低圧タービン流路(28)を横切って配置された第2低圧タービンブレード列(148)を含み、
前記第1低圧タービンブレード列(138)が前記低圧タービン流路(28)に沿って前記第2低圧タービンブレード列(148)の下流に配置され、
回転不能な低圧ベーン(210)の列が、前記低圧タービン流路(28)を横切って前記第1低圧タービンブレード列(138)の第1の隣接対(219)の間及び前記第2低圧タービンブレード列(148)の第2の隣接対(218)の間に配置されている、
ことを特徴とするガスタービンエンジンのタービン組立体。 - 高圧シャフト(27)により高圧圧縮機(18)に駆動可能に結合され且つエンジン中心線(8)の周りで回転可能な高圧タービン(29)を含む高圧ロータ(33)と、
前記高圧ロータ(33)の後方に置かれた、低圧タービン流路(28)とタンデム形非交互嵌合二重反転式前方低圧タービン(40)及び後方低圧タービン(42)とを有する低圧タービンセクション(26)と、
を含み、
前記後方低圧タービン(42)が前記低圧タービン流路(28)を横切って配置された第1低圧タービンブレード列(138)を含み、
前記前方低圧タービン(40)が前記低圧タービン流路(28)を横切って配置された第2低圧タービンブレード列(148)を含み、
前記第1低圧タービンブレード列(138)が前記低圧タービン流路(28)に沿って前記第2低圧タービンブレード列(148)の下流に配置され、
回転不能な低圧ベーン(210)の列が、前記低圧タービン流路(28)を横切って前記第1低圧タービンブレード列(138)の第1の隣接対(219)の間及び前記第2低圧タービンブレード列(148)の第2の隣接対(218)の間に配置されている、
ことを特徴とする航空機用ガスタービンエンジン組立体(10)。 - 前記低圧タービン流路(28)に沿って前記第1低圧タービンブレード列(138)の最前列(50)の上流に置かれた前記第2低圧タービンブレード列(148)の最後列(52)と、該第2低圧タービンブレード列(148)の最後列(52)と前記第1低圧タービンブレード列(138)の最前列(50)との間の環状ベーンなし間隙(58)とを更に含むことを特徴とする、請求項1又は請求項2に記載の組立体。
- タービンノズル(220)が、前記第2低圧タービンブレード列(148)に隣接して、該第2低圧タービンブレード列の軸方向前方上流側に配置されることを特徴とする、請求項1,請求項2又は請求項3に記載の組立体。
- 同数の前記第1低圧タービンブレード列(138)と前記第2低圧タービンブレード列(148)とを更に含むことを特徴とする、請求項4に記載の組立体。
- 各々が偶数である、前記第1低圧タービンブレード列(138)と前記第2低圧タービンブレード列(148)とを更に含むことを特徴とする、請求項5に記載の組立体。
- 4つの前記第1低圧タービンブレード列(138)と4つの前記第2低圧タービンブレード列(148)とを更に含むことを特徴とする、請求項6に記載の組立体。
- 低圧内側シャフトロータ(200)の第1低圧タービンディスク(238)上に取付けられた第1低圧タービンブレード列(138)と、低圧外側シャフトロータ(202)の第2低圧タービンディスク(248)上に取付けられた第2低圧タービンブレード列(148)とを更に含むことを特徴とする請求項3又は請求項4に記載の組立体。
- タービンノズル(220)が、前記第2低圧タービンブレード列(148)に隣接して、該第2低圧タービンブレード列の軸方向前方上流側に配置されることを特徴とする、請求項8に記載の組立体。
- 同数の前記第1低圧タービンブレード列(138)と前記第2低圧タービンブレード列(148)とを更に含むことを特徴とする、請求項9に記載の組立体。
- 各々が偶数である、前記第1低圧タービンブレード列(138)と前記第2低圧タービンブレード列(148)とを更に含むことを特徴とする、請求項10に記載の組立体。
- 4つの前記第1低圧タービンブレード列(138)と4つの前記第2低圧タービンブレード列(148)とを更に含むことを特徴とする、請求項11に記載の組立体。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/223,163 US6711887B2 (en) | 2002-08-19 | 2002-08-19 | Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2004076739A true JP2004076739A (ja) | 2004-03-11 |
JP2004076739A5 JP2004076739A5 (ja) | 2006-09-28 |
JP4588306B2 JP4588306B2 (ja) | 2010-12-01 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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JP2003294855A Expired - Fee Related JP4588306B2 (ja) | 2002-08-19 | 2003-08-19 | 非交互嵌合二重反転式低圧タービンを備えた航空機用ガスタービンエンジン |
Country Status (6)
Country | Link |
---|---|
US (1) | US6711887B2 (ja) |
EP (1) | EP1394385B1 (ja) |
JP (1) | JP4588306B2 (ja) |
CN (1) | CN1333165C (ja) |
CA (1) | CA2436664C (ja) |
DE (1) | DE60300804T2 (ja) |
Cited By (5)
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JP2007113584A (ja) * | 2005-10-19 | 2007-05-10 | General Electric Co <Ge> | ガスタービンエンジンアセンブリ |
JP2007113574A (ja) * | 2005-10-19 | 2007-05-10 | General Electric Co <Ge> | ガスタービンエンジン組立体及びそれを組み立てる方法 |
JP2008115858A (ja) * | 2006-10-31 | 2008-05-22 | General Electric Co <Ge> | ターボファンエンジンアセンブリ |
JP2010144724A (ja) * | 2008-12-19 | 2010-07-01 | General Electric Co <Ge> | 歯車型差動速度二重反転式低圧タービン |
JP2011508135A (ja) * | 2007-12-20 | 2011-03-10 | ボルボ エアロ コーポレイション | ガスタービンエンジン |
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2002
- 2002-08-19 US US10/223,163 patent/US6711887B2/en not_active Expired - Fee Related
-
2003
- 2003-08-06 DE DE60300804T patent/DE60300804T2/de not_active Expired - Lifetime
- 2003-08-06 EP EP03254886A patent/EP1394385B1/en not_active Expired - Fee Related
- 2003-08-07 CA CA002436664A patent/CA2436664C/en not_active Expired - Fee Related
- 2003-08-19 CN CNB031548059A patent/CN1333165C/zh not_active Expired - Fee Related
- 2003-08-19 JP JP2003294855A patent/JP4588306B2/ja not_active Expired - Fee Related
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Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2007113584A (ja) * | 2005-10-19 | 2007-05-10 | General Electric Co <Ge> | ガスタービンエンジンアセンブリ |
JP2007113574A (ja) * | 2005-10-19 | 2007-05-10 | General Electric Co <Ge> | ガスタービンエンジン組立体及びそれを組み立てる方法 |
JP2008115858A (ja) * | 2006-10-31 | 2008-05-22 | General Electric Co <Ge> | ターボファンエンジンアセンブリ |
JP2011508135A (ja) * | 2007-12-20 | 2011-03-10 | ボルボ エアロ コーポレイション | ガスタービンエンジン |
JP2010144724A (ja) * | 2008-12-19 | 2010-07-01 | General Electric Co <Ge> | 歯車型差動速度二重反転式低圧タービン |
Also Published As
Publication number | Publication date |
---|---|
CA2436664A1 (en) | 2004-02-19 |
JP4588306B2 (ja) | 2010-12-01 |
US6711887B2 (en) | 2004-03-30 |
CN1485535A (zh) | 2004-03-31 |
CN1333165C (zh) | 2007-08-22 |
EP1394385A1 (en) | 2004-03-03 |
US20040031260A1 (en) | 2004-02-19 |
DE60300804D1 (de) | 2005-07-14 |
EP1394385B1 (en) | 2005-06-08 |
DE60300804T2 (de) | 2006-03-23 |
CA2436664C (en) | 2009-09-22 |
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