JP5844959B2 - 歯車型差動速度二重反転式低圧タービン - Google Patents
歯車型差動速度二重反転式低圧タービン Download PDFInfo
- Publication number
- JP5844959B2 JP5844959B2 JP2009284639A JP2009284639A JP5844959B2 JP 5844959 B2 JP5844959 B2 JP 5844959B2 JP 2009284639 A JP2009284639 A JP 2009284639A JP 2009284639 A JP2009284639 A JP 2009284639A JP 5844959 B2 JP5844959 B2 JP 5844959B2
- Authority
- JP
- Japan
- Prior art keywords
- low pressure
- inner drum
- turbine
- rotor
- turbine blade
- 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.)
- Active
Links
- 239000007789 gas Substances 0.000 description 11
- 239000000446 fuel Substances 0.000 description 5
- 239000000567 combustion gas Substances 0.000 description 4
- 239000003570 air Substances 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000012080 ambient air Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
Images
Classifications
-
- 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
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
-
- 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
- F01D5/03—Annular blade-carrying members having blades on the inner periphery of the annulus and extending inwardly radially, i.e. inverted 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
- 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- 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
-
- 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
- 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
- F05D2260/40—Transmission of power
- F05D2260/403—Transmission of power through the shape of the drive components
- F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
- F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Retarders (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
5 周囲空気
8 エンジン中心線
9 内側バイパスダクト壁
10 ガスタービンエンジン
11 ファンケーシング
12 ファンセクション
14 単一のファンブレード列
16 ブースタ
18 高圧圧縮機
19 入口ダクト
20 燃焼器
21 バイパスダクト
23 燃焼ガス
24 高圧タービン
25 コアエンジン
26 低圧タービン
27 高圧シャフト
33 高圧ロータ
56 遊星ギヤボックス
58 遊星歯車
60 内側ドラムタービンブレード列
62 低圧内側シャフト
64 低圧外側ウェブ
66 外側シェル
68 外側ドラムロータ
70 外側ドラムタービンブレード列
72 第1段
74 低圧シャフト
78 内側ドラムロータ
80 内側ドラムタービンブレード列
84 後方端部
88 円錐形シャフト延長部
90 タービン後部フレーム
94 タービン支柱
98 翼形部
100 外側タービンケーシング
102 環状キャリヤ
104 遊星歯車
106 ピン
108 太陽歯車
110 リング歯車
112 スラスト軸受
114 外側ローラ軸受
120 内側差動ローラ軸受
Claims (8)
- ガスタービンエンジンの二重反転式低圧タービン(26)であって、
二重反転可能な環状の外側及び内側ドラムロータ(68、78)と、
前記外側ドラムロータ(68)の外側シェル(66)から半径方向内向きに延びる複数の軸方向に間隔を置いて配置された低圧外側ドラムタービンブレード列(70)と、
前記環状の低圧内側ドラムロータ(78)から半径方向外向きに延びる複数の軸方向に間隔を置いて配置された低圧内側ドラムタービンブレード列(80)と、を含み、
前記低圧外側ドラムタービンブレード列(70)が、前記低圧内側ドラムタービンブレード列(80)と交差指状に配置され、
前記外側ドラムロータ(68)が、該低圧タービン(26)からのトルク及び出力を伝達するように作動可能な単独シャフトである低圧シャフト(74)に回転可能に連結され、
前記内側ドラムロータ(78)が、遊星ギヤボックス(56)を介して歯車連結されて該内側ドラムロータ(78)によって生成されたトルク及び出力を前記低圧シャフト(74)に伝達するようになっており、
前記遊星ギヤボックス(56)が、前記外側及び内側ドラムロータ(68、78)の後方に設置された
ことを特徴とする、低圧タービン(26)。 - 前記外側及び内側ドラムロータ(68、78)間に作動可能に配置された差動スラスト軸受(112)をさらに含む、請求項1記載の低圧タービン(26)。
- 前記遊星ギヤボックス(56)が、タービン後部フレーム(90)によって支持されたピン(106)上に回転可能に取付けられた遊星歯車(104)を有する、請求項2記載の低圧タービン(26)。
- 前記遊星ギヤボックス(56)が、前記遊星歯車(104)と噛合いかつ該遊星歯車(104)の半径方向内側に回転可能に取付けられた太陽歯車(108)と、前記遊星歯車(104)と噛合いかつ該遊星歯車(104)の半径方向外側に回転可能に取付けられたリング歯車(110)とを含み、
前記外側ドラムロータ(68)が、前記リング歯車(110)に連結され、
前記内側ドラムロータ(78)が、前記太陽歯車(108)に連結される、
請求項3記載の低圧タービン(26)。 - 前記内側ドラムロータ(78)及びタービン後部フレーム(90)間に配置された半径方向外側ローラ軸受(114)と、
前記外側及び内側ドラムロータ(68、78)間に配置された半径方向内側差動ローラ軸受(120)と、
をさらに含む、請求項4記載の低圧タービン(26)。 - 航空機ガスタービンエンジン(10)であって、
単一のファンブレード列(14)を有する単一のファン段(4)を備えた単段ファンセクション(12)と、
低圧シャフト(74)によって前記単一のファン段(4)に対して駆動連結された二重反転式低圧タービン(26)と、
を含み、前記二重反転式低圧タービン(26)が、
二重反転可能な環状の外側及び内側ドラムロータ(68、78)と、
前記外側ドラムロータ(68)の外側シェル(66)から半径方向内向きに延びる複数の軸方向に間隔を置いて配置された低圧外側ドラムタービンブレード列(70)と、
前記低圧内側ドラムロータ(78)から半径方向外向きに延びる複数の軸方向に間隔を置いて配置された低圧内側ドラムタービンブレード列(80)と、を含み、
前記低圧外側ドラムタービンブレード列(70)が、前記低圧内側ドラムタービンブレード列(80)と交差指状に配置され、
前記外側ドラムロータ(68)が、前記低圧タービン(26)からのトルク及び出力を伝達するように作動可能な単独シャフトである前記低圧シャフト(74)に回転可能に連結され、
前記内側ドラムロータ(78)が、遊星ギヤボックス(56)を介して歯車連結されて該内側ドラムロータ(78)によって生成されたトルク及び出力を前記低圧シャフト(74)に伝達するようになっており、
前記遊星ギヤボックス(56)が、前記外側及び内側ドラムロータ(68、78)の後方に設置された
ことを特徴とする、エンジン。 - 前記外側及び内側ドラムロータ間に作動可能に配置された差動スラスト軸受をさらに含む、請求項6記載のエンジン。
- 航空機ガスタービンエンジンファミリであって、
異なる寸法のファン及び/又は作動設計ファン速度を有する該エンジンファミリ内の少なくとも2つの異なるエンジンモデルを含み、
前記2つの異なるエンジンモデルが、該異なるエンジンモデルの二重反転式低圧タービン(26)の外側及び内側ドラムタービンブレード列(70、80)間に同一の相対差動速度を維持するようになったそれぞれ異なる歯車比を備えた異なる遊星ギヤボックス(56)を有し、
前記エンジンモデルの各々が、単一のファンブレード列(14)並びに異なるサイズのファン及び/又は作動設計ファン速度のそれぞれ1つを有する単一のファン段(4)を備えた単段ファンセクション(12)を有する航空機ガスタービンエンジン(10)を含み、
前記二重反転式低圧タービン(26)が、低圧シャフト(74)によって前記単一のファン段(4)に対して駆動連結され、
前記外側ドラムタービンブレード列(70)が、外側ドラムロータ(68)の外側シェル(66)から半径方向内向きに延びる複数の軸方向に間隔を置いて配置された低圧外側ドラムタービンブレード列(70)を含み、
前記内側ドラムタービンブレード列(80)が、低圧内側ドラムロータ(78)から半径方向外向きに延びる複数の軸方向に間隔を置いて配置された低圧内側ドラムタービンブレード列(80)を含み、
前記低圧外側ドラムタービンブレード列(70)が、前記低圧内側ドラムタービンブレード列(80)と交差指状に配置され、
前記外側ドラムロータ(68)が、前記低圧タービン(26)からのトルク及び出力を伝達するように作動可能な単独シャフトである前記低圧シャフト(74)に回転可能に連結され、
前記内側ドラムロータ(78)が、前記遊星ギヤボックス(56)を介して歯車連結されて該内側ドラムロータ(78)によって生成されたトルク及び出力を前記低圧シャフト(74)に伝達するようになっており、
前記遊星ギヤボックス(56)が、前記外側及び内側ドラムロータ(68、78)の後方に設置された
ことを特徴とする、エンジンファミリ。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/339,731 US8191352B2 (en) | 2008-12-19 | 2008-12-19 | Geared differential speed counter-rotatable low pressure turbine |
US12/339,731 | 2008-12-19 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010144724A JP2010144724A (ja) | 2010-07-01 |
JP5844959B2 true JP5844959B2 (ja) | 2016-01-20 |
Family
ID=41405615
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2009284639A Active JP5844959B2 (ja) | 2008-12-19 | 2009-12-16 | 歯車型差動速度二重反転式低圧タービン |
Country Status (3)
Country | Link |
---|---|
US (1) | US8191352B2 (ja) |
EP (1) | EP2199568B1 (ja) |
JP (1) | JP5844959B2 (ja) |
Families Citing this family (105)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8015798B2 (en) * | 2007-12-13 | 2011-09-13 | United Technologies Corporation | Geared counter-rotating gas turbofan engine |
US8128021B2 (en) | 2008-06-02 | 2012-03-06 | United Technologies Corporation | Engine mount system for a turbofan gas turbine engine |
US20140174056A1 (en) | 2008-06-02 | 2014-06-26 | United Technologies Corporation | Gas turbine engine with low stage count low pressure turbine |
US20100192595A1 (en) * | 2009-01-30 | 2010-08-05 | Robert Joseph Orlando | Gas turbine engine assembly and methods of assembling same |
US8845277B2 (en) * | 2010-05-24 | 2014-09-30 | United Technologies Corporation | Geared turbofan engine with integral gear and bearing supports |
IT1401662B1 (it) * | 2010-08-27 | 2013-08-02 | Nuova Pignone S R L | Dispositivo espansore multistadio assiale con ingranaggi, sistema e metodo. |
FR2970746B1 (fr) * | 2011-01-20 | 2015-12-04 | Snecma | Turbomachine a turbines haute pression et basse pression imbriquees |
US9631558B2 (en) | 2012-01-03 | 2017-04-25 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
US9239012B2 (en) | 2011-06-08 | 2016-01-19 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US8667773B2 (en) * | 2011-06-28 | 2014-03-11 | United Technologies Corporation | Counter-rotating turbomachinery |
US9938898B2 (en) * | 2011-07-29 | 2018-04-10 | United Technologies Corporation | Geared turbofan bearing arrangement |
JP5896449B2 (ja) * | 2011-09-05 | 2016-03-30 | 国立研究開発法人宇宙航空研究開発機構 | ターボファンジェットエンジン |
US10125724B2 (en) | 2012-01-17 | 2018-11-13 | United Technologies Corporation | Start system for gas turbine engines |
US20130192256A1 (en) * | 2012-01-31 | 2013-08-01 | Gabriel L. Suciu | Geared turbofan engine with counter-rotating shafts |
US8935913B2 (en) | 2012-01-31 | 2015-01-20 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US10145266B2 (en) | 2012-01-31 | 2018-12-04 | United Technologies Corporation | Gas turbine engine shaft bearing arrangement |
US8887487B2 (en) | 2012-01-31 | 2014-11-18 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US10287914B2 (en) | 2012-01-31 | 2019-05-14 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section and bearing support features |
US20150345426A1 (en) | 2012-01-31 | 2015-12-03 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US9222417B2 (en) | 2012-01-31 | 2015-12-29 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US9534608B2 (en) | 2012-02-17 | 2017-01-03 | Embry-Riddle Aeronautical University, Inc. | Multi-stage axial compressor with counter-rotation |
US9011076B2 (en) | 2012-02-29 | 2015-04-21 | United Technologies Corporation | Counter-rotating low pressure turbine with gear system mounted to turbine exhaust case |
US9080512B2 (en) | 2012-02-29 | 2015-07-14 | United Technologies Corporation | Counter-rotating low pressure turbine with gear system mounted to mid turbine frame |
US9194290B2 (en) | 2012-02-29 | 2015-11-24 | United Technologies Corporation | Counter-rotating low pressure turbine without turbine exhaust case |
US9022725B2 (en) * | 2012-02-29 | 2015-05-05 | United Technologies Corporation | Counter-rotating low pressure turbine with gear system mounted to turbine exhaust case |
US20130219859A1 (en) * | 2012-02-29 | 2013-08-29 | Gabriel L. Suciu | Counter rotating low pressure compressor and turbine each having a gear system |
US9028200B2 (en) * | 2012-02-29 | 2015-05-12 | United Technologies Corporation | Counter rotating low pressure turbine with splitter gear system |
US9353754B2 (en) | 2012-03-13 | 2016-05-31 | Embry-Riddle Aeronautical University, Inc. | Multi-stage axial compressor with counter-rotation using accessory drive |
US10036351B2 (en) * | 2012-04-02 | 2018-07-31 | United Technologies Corporation | Geared turbofan with three co-rotating turbines |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US10018119B2 (en) | 2012-04-02 | 2018-07-10 | United Technologies Corporation | Geared architecture with inducer for gas turbine engine |
US20130259650A1 (en) * | 2012-04-02 | 2013-10-03 | Frederick M. Schwarz | Geared turbofan with three turbines with first two co-rotating and third rotating in an opposed direction |
US8756908B2 (en) | 2012-05-31 | 2014-06-24 | United Technologies Corporation | Fundamental gear system architecture |
US20150308351A1 (en) | 2012-05-31 | 2015-10-29 | United Technologies Corporation | Fundamental gear system architecture |
US8572943B1 (en) | 2012-05-31 | 2013-11-05 | United Technologies Corporation | Fundamental gear system architecture |
US8753065B2 (en) * | 2012-09-27 | 2014-06-17 | United Technologies Corporation | Method for setting a gear ratio of a fan drive gear system of a gas turbine engine |
US8807916B2 (en) | 2012-09-27 | 2014-08-19 | United Technologies Corporation | Method for setting a gear ratio of a fan drive gear system of a gas turbine engine |
GB201219544D0 (en) * | 2012-10-31 | 2012-12-12 | Rolls Royce Deutschland | Geared compressor for gas turbine engine |
CN104937251B (zh) | 2013-01-18 | 2017-11-28 | 通用电气公司 | 具有反向旋转整体式传动器和无导叶涡轮的发动机架构 |
US8678743B1 (en) | 2013-02-04 | 2014-03-25 | United Technologies Corporation | Method for setting a gear ratio of a fan drive gear system of a gas turbine engine |
US10119475B2 (en) | 2013-02-13 | 2018-11-06 | United Technologies Corporation | Gas turbine engine geared architecture |
US8829702B1 (en) * | 2013-03-11 | 2014-09-09 | Pratt & Whitney Canada Corp | Gas turbine engine with internal electromechanical device |
US9003638B2 (en) | 2013-03-11 | 2015-04-14 | Pratt & Whitney Canada Corp. | Method of assembling an electromechanical device in a gas-turbine engine |
US9752500B2 (en) * | 2013-03-14 | 2017-09-05 | Pratt & Whitney Canada Corp. | Gas turbine engine with transmission and method of adjusting rotational speed |
US9624827B2 (en) | 2013-03-15 | 2017-04-18 | United Technologies Corporation | Thrust efficient turbofan engine |
US10724479B2 (en) | 2013-03-15 | 2020-07-28 | United Technologies Corporation | Thrust efficient turbofan engine |
US20150176484A1 (en) * | 2013-12-23 | 2015-06-25 | United Technologies Corporation | Geared turbofan with a gearbox aft of a fan drive turbine |
US9739205B2 (en) | 2013-12-23 | 2017-08-22 | United Technologies Corporation | Geared turbofan with a gearbox upstream of a fan drive turbine |
US11448123B2 (en) | 2014-06-13 | 2022-09-20 | Raytheon Technologies Corporation | Geared turbofan architecture |
US10221771B2 (en) | 2014-09-24 | 2019-03-05 | United Technologies Corporation | Fan drive gear system |
US20160178464A1 (en) * | 2014-12-19 | 2016-06-23 | Rolls-Royce Corporation | Torque sensor monitoring for gas turbine engine |
US10072571B2 (en) | 2015-01-15 | 2018-09-11 | United Technologies Corporation | Gas turbine engine split torque fan drive gear system |
US9333603B1 (en) | 2015-01-28 | 2016-05-10 | United Technologies Corporation | Method of assembling gas turbine engine section |
US9879694B2 (en) | 2015-02-03 | 2018-01-30 | United Technologies Corporation | Turbo-compressor with geared turbofan |
US11067005B2 (en) | 2015-02-03 | 2021-07-20 | Raytheon Technologies Corporation | Fan drive gear system |
US10669946B2 (en) | 2015-06-05 | 2020-06-02 | Raytheon Technologies Corporation | Geared architecture for a gas turbine engine |
US10094283B2 (en) | 2015-10-28 | 2018-10-09 | General Electric Company | Differential gas bearing for aircraft engines |
US10066734B2 (en) | 2015-12-07 | 2018-09-04 | United Technologies Corporation | Gear driven gas turbine engine assembly |
RU2628634C9 (ru) * | 2016-05-20 | 2017-10-05 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Реверсивная турбинная установка судового типа |
US9995175B2 (en) | 2016-06-29 | 2018-06-12 | General Electric Company | System and method for gas bearing support of turbine |
US10247017B2 (en) | 2016-06-29 | 2019-04-02 | General Electric Company | System and method for gas bearing support of turbine |
EP3296540B1 (en) | 2016-09-20 | 2019-01-23 | Rolls-Royce Deutschland Ltd & Co KG | Gas turbine engine with a geared turbofan arrangement |
EP3296552B1 (en) | 2016-09-20 | 2019-06-05 | Rolls-Royce Deutschland Ltd & Co KG | Gas turbine engine with a geared turbofan arrangement |
EP3296524B1 (en) | 2016-09-20 | 2019-02-27 | Rolls-Royce Deutschland Ltd & Co KG | Gas turbine engine with a geared turbofan arrangement |
EP3296525B1 (en) | 2016-09-20 | 2019-11-27 | Rolls-Royce Deutschland Ltd & Co KG | Gas turbine engine with a geared turbofan arrangement |
US10465606B2 (en) | 2017-02-08 | 2019-11-05 | General Electric Company | Counter rotating turbine with reversing reduction gearbox |
US10823114B2 (en) | 2017-02-08 | 2020-11-03 | General Electric Company | Counter rotating turbine with reversing reduction gearbox |
US10801442B2 (en) * | 2017-02-08 | 2020-10-13 | General Electric Company | Counter rotating turbine with reversing reduction gear assembly |
US10876407B2 (en) * | 2017-02-16 | 2020-12-29 | General Electric Company | Thermal structure for outer diameter mounted turbine blades |
FR3067056B1 (fr) * | 2017-06-01 | 2019-07-26 | Safran Aircraft Engines | Turboreacteur du type a rotor non carene |
US10663036B2 (en) * | 2017-06-13 | 2020-05-26 | General Electric Company | Gas turbine engine with rotating reversing compound gearbox |
US11371379B2 (en) * | 2017-08-22 | 2022-06-28 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10961850B2 (en) * | 2017-09-19 | 2021-03-30 | General Electric Company | Rotatable torque frame for gas turbine engine |
US10738617B2 (en) | 2017-09-20 | 2020-08-11 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US11255221B2 (en) | 2017-09-20 | 2022-02-22 | General Electric Company | Lube system for geared turbine section |
US10914194B2 (en) * | 2017-09-20 | 2021-02-09 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10823001B2 (en) * | 2017-09-20 | 2020-11-03 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10815881B2 (en) * | 2017-09-20 | 2020-10-27 | General Electric Company | Counter rotating turbine with reversing speed reduction assembly |
US11008883B2 (en) | 2017-09-20 | 2021-05-18 | General Electric Company | Turbomachine with a gearbox and integrated electric machine assembly |
US11098592B2 (en) * | 2017-09-20 | 2021-08-24 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10781717B2 (en) * | 2017-09-20 | 2020-09-22 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10823000B2 (en) | 2017-09-20 | 2020-11-03 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10711629B2 (en) * | 2017-09-20 | 2020-07-14 | Generl Electric Company | Method of clearance control for an interdigitated turbine engine |
US10508546B2 (en) * | 2017-09-20 | 2019-12-17 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US11131244B2 (en) | 2017-11-03 | 2021-09-28 | General Electric Company | Power transmission system and gas turbine engine comprising the same |
US10644630B2 (en) * | 2017-11-28 | 2020-05-05 | General Electric Company | Turbomachine with an electric machine assembly and method for operation |
US10480322B2 (en) | 2018-01-12 | 2019-11-19 | General Electric Company | Turbine engine with annular cavity |
US11578663B2 (en) * | 2018-09-11 | 2023-02-14 | Pratt & Whitney Canada Corp. | Engine family platform design |
FR3087223B1 (fr) * | 2018-10-10 | 2020-10-23 | Safran Aircraft Engines | Turbomachine a turbine contrarotative pour un aeronef |
FR3088968B1 (fr) * | 2018-11-27 | 2021-12-03 | Safran Aircraft Engines | Agencement de turboréacteur double flux à réducteur épicycloïdal ou planétaire |
FR3088966B1 (fr) * | 2018-11-27 | 2020-11-06 | Safran Aircraft Engines | Agencement de turboréacteur double flux à réducteur épicycloïdal ou planétaire |
FR3088967B1 (fr) * | 2018-11-27 | 2020-11-06 | Safran Aircraft Engines | Agencement de turboréacteur double flux à réducteur épicycloïdal ou planétaire |
US11118506B2 (en) | 2018-12-21 | 2021-09-14 | General Electric Company | Gear assembly for a turbo machine |
US11156097B2 (en) * | 2019-02-20 | 2021-10-26 | General Electric Company | Turbomachine having an airflow management assembly |
US11021970B2 (en) * | 2019-02-20 | 2021-06-01 | General Electric Company | Turbomachine with alternatingly spaced rotor blades |
US11118535B2 (en) | 2019-03-05 | 2021-09-14 | General Electric Company | Reversing gear assembly for a turbo machine |
US11136899B2 (en) * | 2019-06-14 | 2021-10-05 | Raytheon Technologies Corporation | Integrated electro-aero-thermal turbine engine |
IT201900013218A1 (it) * | 2019-07-29 | 2021-01-29 | Ge Avio Srl | Fascia interna per motore a turbina. |
US11319882B2 (en) | 2019-09-10 | 2022-05-03 | Raytheon Technologies Corporation | Gear and electric amplification of generator motor compressor and turbine drives |
FR3104205B1 (fr) * | 2019-12-10 | 2021-11-19 | Safran Aircraft Engines | Pressurisation d’enceintes de lubrification dans une turbomachine a turbine contrarotative |
FR3107938B1 (fr) * | 2020-03-09 | 2022-02-04 | Safran Aircraft Engines | Reducteur de vitesse equipe d’une machine electrique |
US20220090512A1 (en) * | 2020-09-18 | 2022-03-24 | Ge Avio Srl | Turbomachine |
US11725590B2 (en) | 2020-10-22 | 2023-08-15 | General Electric Company | Turbomachine and gear assembly |
FR3118093B1 (fr) * | 2020-12-17 | 2023-01-27 | Safran Aircraft Engines | Aube de turbine, en particulier destinée à une turbine contrarotative |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3673802A (en) * | 1970-06-18 | 1972-07-04 | Gen Electric | Fan engine with counter rotating geared core booster |
US4251987A (en) * | 1979-08-22 | 1981-02-24 | General Electric Company | Differential geared engine |
GB8630754D0 (en) * | 1986-12-23 | 1987-02-04 | Rolls Royce Plc | Turbofan gas turbine engine |
US4916894A (en) * | 1989-01-03 | 1990-04-17 | General Electric Company | High bypass turbofan engine having a partially geared fan drive turbine |
US4969325A (en) * | 1989-01-03 | 1990-11-13 | General Electric Company | Turbofan engine having a counterrotating partially geared fan drive turbine |
US5010729A (en) * | 1989-01-03 | 1991-04-30 | General Electric Company | Geared counterrotating turbine/fan propulsion system |
US5361580A (en) * | 1993-06-18 | 1994-11-08 | General Electric Company | Gas turbine engine rotor support system |
US6158210A (en) * | 1998-12-03 | 2000-12-12 | General Electric Company | Gear driven booster |
US6711887B2 (en) * | 2002-08-19 | 2004-03-30 | General Electric Co. | Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines |
US7063505B2 (en) * | 2003-02-07 | 2006-06-20 | General Electric Company | Gas turbine engine frame having struts connected to rings with morse pins |
US7246484B2 (en) * | 2003-08-25 | 2007-07-24 | General Electric Company | FLADE gas turbine engine with counter-rotatable fans |
GB0406174D0 (en) * | 2004-03-19 | 2004-04-21 | Rolls Royce Plc | Turbine engine arrangement |
US7334392B2 (en) * | 2004-10-29 | 2008-02-26 | General Electric Company | Counter-rotating gas turbine engine and method of assembling same |
US7752836B2 (en) * | 2005-10-19 | 2010-07-13 | General Electric Company | Gas turbine assembly and methods of assembling same |
US7490460B2 (en) * | 2005-10-19 | 2009-02-17 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7966806B2 (en) * | 2006-10-31 | 2011-06-28 | General Electric Company | Turbofan engine assembly and method of assembling same |
US7841165B2 (en) * | 2006-10-31 | 2010-11-30 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US8015798B2 (en) * | 2007-12-13 | 2011-09-13 | United Technologies Corporation | Geared counter-rotating gas turbofan engine |
-
2008
- 2008-12-19 US US12/339,731 patent/US8191352B2/en active Active
-
2009
- 2009-12-04 EP EP09177975.1A patent/EP2199568B1/en not_active Not-in-force
- 2009-12-16 JP JP2009284639A patent/JP5844959B2/ja active Active
Also Published As
Publication number | Publication date |
---|---|
US20100154384A1 (en) | 2010-06-24 |
JP2010144724A (ja) | 2010-07-01 |
EP2199568A2 (en) | 2010-06-23 |
EP2199568A3 (en) | 2016-06-01 |
US8191352B2 (en) | 2012-06-05 |
EP2199568B1 (en) | 2017-10-11 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP5844959B2 (ja) | 歯車型差動速度二重反転式低圧タービン | |
JP4846511B2 (ja) | 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 | |
JP5667668B2 (ja) | ガスタービンエンジン組立方法 | |
JP5689067B2 (ja) | 回転可能な半径方向内側に延びるブレードおよび回転しないベーンを備えるガスタービンエンジンブースタ | |
JP5814559B2 (ja) | 遊星ギヤ装置 | |
JP4906311B2 (ja) | 二重反転ガスタービンエンジン及びそれを組立てる方法 | |
US7526913B2 (en) | Gas turbine engine assembly and methods of assembling same | |
JP4346375B2 (ja) | 低圧タービンを二重反転させるための制御ベーンを備えた航空機用ガスタービンエンジン | |
EP1921290B1 (en) | Turbofan engine assembly | |
CA2440527C (en) | Variable torque split aircraft gas turbine engine counter rotating low pressure turbines | |
CN109386384A (zh) | 燃气涡轮发动机 | |
US8292570B2 (en) | Low pressure turbine with counter-rotating drives for single spool | |
JP2012132462A (ja) | ガスタービンエンジンアセンブリ | |
JP2007113576A (ja) | 二重反転ファン組立体及びそれを含むガスタービンエンジン組立体 | |
JP2007332951A (ja) | ガスタービンエンジンおよびガスタービンエンジンを運転する方法 | |
JP2007113582A (ja) | 二重反転ファン組立体及び二重反転ファン組立体を備えるガスタービンエンジン組立体 | |
JP2010174887A (ja) | ガスタービエンジン組立体及びそれを組立てる方法 | |
WO2013130296A1 (en) | Gas turbine engine driving multiple fans | |
JP2013053561A (ja) | ターボファンジェットエンジン | |
CN115506916A (zh) | 对转桨尖双驱动涡扇发动机 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20121205 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20131008 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20140107 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20140110 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20140404 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20141007 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20150206 |
|
A911 | Transfer to examiner for re-examination before appeal (zenchi) |
Free format text: JAPANESE INTERMEDIATE CODE: A911 Effective date: 20150323 |
|
A912 | Re-examination (zenchi) completed and case transferred to appeal board |
Free format text: JAPANESE INTERMEDIATE CODE: A912 Effective date: 20150703 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20151120 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 5844959 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
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 |