JP2013238244A - ガスタービンエンジン組立方法 - Google Patents
ガスタービンエンジン組立方法 Download PDFInfo
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- JP2013238244A JP2013238244A JP2013148092A JP2013148092A JP2013238244A JP 2013238244 A JP2013238244 A JP 2013238244A JP 2013148092 A JP2013148092 A JP 2013148092A JP 2013148092 A JP2013148092 A JP 2013148092A JP 2013238244 A JP2013238244 A JP 2013238244A
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- Prior art keywords
- low pressure
- pressure turbine
- coupling
- turbine engine
- booster compressor
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Classifications
-
- 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
- F02K3/06—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 front fan
-
- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/12—Combinations with mechanical gearing
-
- 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
-
- 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】本タービンエンジン組立体10は、高圧圧縮機、燃焼器及び高圧タービンを備えたコアガスタービンエンジンを含む。低圧タービンは、コアガスタービンエンジンに結合される。本タービンエンジン組立体はまた、ブースタ圧縮機22を含む。ギヤボックス100は、低圧タービンとブースタ圧縮機との間に結合されて該ブースタ圧縮機が該低圧タービンによって駆動されるようする。
【選択図】図2
Description
11 長手方向軸線
12 ファン組立体
13 コアガスタービンエンジン
14 高圧圧縮機
16 燃焼器
18 高圧タービン
20 低圧タービン
22 ブースタ圧縮機
24 ファンブレード
26 ロータディスク
28 吸気側
30 排気側
31 第1のロータシャフト
32 第2のロータシャフト
34 入口ガイドベーン組立体
36 (OGV)組立体
40 2つの段
42 ロータブレード
44 ブースタロータディスク
46 ガイドベーン
50 ブースタケース
100 ギヤボックス組立体
102 支持構造体
103 ギヤ
104 入力ギヤ
106 出力ギヤ
108 ギヤ
110 ファン軸受組立体
112 内側レース
114 外側レース
116 ハウジング
118 転動体
120 第2の軸受組立体
130 第3のファン軸受組立体
140 駆動シャフト延長部
142 屈曲継手
150 コーン又はディスク
160 シャフト
170 サンプ
180 発電機
182 発電機駆動シャフト
184 第1の端部
186 第2の端部
188 ベベルギヤ
190 ベベルギヤ
200 ガスタービンエンジン組立体
202 ディスク
204 延長装置
208 フレーム
210 軸受組立体
212 外側レース
214 内側レース
216 転動体
220 軸受組立体
230 軸受組立体
232 外側レース
234 内側レース
236 シャフト延長部
238 転動体
Claims (5)
- 高圧圧縮機、燃焼器、及び高圧タービンを備えたコアガスタービンエンジンを用意するステップと、
低圧タービンを前記コアガスタービンエンジンに結合するステップと、
ブースタ圧縮機をギヤボックスに結合するステップと、
前記ブースタ圧縮機が前記低圧タービンで駆動されるように、前記ギヤボックスを前記低圧タービンに結合するステップと、
駆動シャフトを前記低圧タービンに結合するステップと、
前記ブースタ圧縮機が前記低圧タービンの回転速度とは異なる回転速度で回転するように、前記ギヤボックスを前記駆動シャフトと前記ブースタ圧縮機との間に結合するステップと、
を含む、タービンエンジン組立体の組立方法。 - 高圧圧縮機、燃焼器、及び高圧タービンを備えたコアガスタービンエンジンを用意するステップと、
低圧タービンを前記コアガスタービンエンジンに結合するステップと、
ブースタ圧縮機をギヤボックスに結合するステップと、
前記ブースタ圧縮機が前記低圧タービンで駆動されるように、前記ギヤボックスを前記低圧タービンに結合するステップと、
駆動シャフトを前記低圧タービンに結合するステップと、
ファン組立体が前記低圧タービンの回転速度と同一の回転速度で回転するように、前記ファン組立体を前記駆動シャフトに結合するステップと、
前記ファン組立体及び前記低圧タービンによって生じた残留スラスト荷重が固定構造構成要素に伝達されるように、スラスト軸受組立体を前記ファン組立体及び前記低圧タービンとの間に結合するステップと、
を含む、タービンエンジン組立体の組立方法。 - 高圧圧縮機、燃焼器、及び高圧タービンを備えたコアガスタービンエンジンを用意するステップと、
低圧タービンを前記コアガスタービンエンジンに結合するステップと、
ブースタ圧縮機をギヤボックスに結合するステップと、
前記ブースタ圧縮機が前記低圧タービンで駆動されるように、前記ギヤボックスを前記低圧タービンに結合するステップと、
駆動シャフトを前記低圧タービンに結合するステップと、
前記ブースタ圧縮機によって生じた残留スラスト荷重が固定構造構成要素に伝達されるように、スラスト軸受組立体を前記ブースタ圧縮機及び前記ギヤボックスとの間に結合するステップと、
を含む、タービンエンジン組立体の組立方法。 - 高圧圧縮機、燃焼器、及び高圧タービンを備えたコアガスタービンエンジンを用意するステップと、
低圧タービンを前記コアガスタービンエンジンに結合するステップと、
ブースタ圧縮機をギヤボックスに結合するステップと、
前記ブースタ圧縮機が前記低圧タービンで駆動されるように、前記ギヤボックスを前記低圧タービンに結合するステップと、
を含み、
前記ギヤボックスが実質的に前記駆動シャフトに外接するように、前記ギヤボックスを前記低圧タービンに結合する前記ステップが、実質的にトロイダル断面輪郭をするギアボックスを前記ブースタ圧縮機と前記駆動シャフトとの間に結合するステップを含む、
タービンエンジン組立体の組立方法。 - 高圧圧縮機、燃焼器、及び高圧タービンを備えたコアガスタービンエンジンを用意するステップと、
低圧タービンを前記コアガスタービンエンジンに結合するステップと、
ブースタ圧縮機をギヤボックスに結合するステップと、
前記ブースタ圧縮機が前記低圧タービンで駆動されるように、前記ギヤボックスを前記低圧タービンに結合するステップと、
屈曲継手を前記駆動シャフトと前記ギヤボックスとの間に結合するステップと、
を含む、タービンエンジン組立体の組立方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/553,571 US7832193B2 (en) | 2006-10-27 | 2006-10-27 | Gas turbine engine assembly and methods of assembling same |
US11/553,571 | 2006-10-27 |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
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JP2007277467A Division JP2008111437A (ja) | 2006-10-27 | 2007-10-25 | ガスタービンエンジン組立体 |
Publications (2)
Publication Number | Publication Date |
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JP2013238244A true JP2013238244A (ja) | 2013-11-28 |
JP5667668B2 JP5667668B2 (ja) | 2015-02-12 |
Family
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Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
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JP2007277467A Pending JP2008111437A (ja) | 2006-10-27 | 2007-10-25 | ガスタービンエンジン組立体 |
JP2013148092A Expired - Fee Related JP5667668B2 (ja) | 2006-10-27 | 2013-07-17 | ガスタービンエンジン組立方法 |
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Application Number | Title | Priority Date | Filing Date |
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JP2007277467A Pending JP2008111437A (ja) | 2006-10-27 | 2007-10-25 | ガスタービンエンジン組立体 |
Country Status (3)
Country | Link |
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US (1) | US7832193B2 (ja) |
EP (1) | EP1916390A3 (ja) |
JP (2) | JP2008111437A (ja) |
Families Citing this family (79)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2123884B1 (en) | 2008-05-13 | 2015-03-04 | Rolls-Royce Corporation | Dual clutch arrangement |
US20140174056A1 (en) | 2008-06-02 | 2014-06-26 | United Technologies Corporation | Gas turbine engine with low stage count low pressure turbine |
US8128021B2 (en) | 2008-06-02 | 2012-03-06 | United Technologies Corporation | Engine mount system for a turbofan gas turbine engine |
US20100005810A1 (en) * | 2008-07-11 | 2010-01-14 | Rob Jarrell | Power transmission among shafts in a turbine engine |
US8480527B2 (en) | 2008-08-27 | 2013-07-09 | Rolls-Royce Corporation | Gearing arrangement |
US8011877B2 (en) * | 2008-11-24 | 2011-09-06 | General Electric Company | Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades |
US8075438B2 (en) | 2008-12-11 | 2011-12-13 | Rolls-Royce Corporation | Apparatus and method for transmitting a rotary input into counter-rotating outputs |
US8021267B2 (en) | 2008-12-11 | 2011-09-20 | Rolls-Royce Corporation | Coupling assembly |
GB0903935D0 (en) * | 2009-03-09 | 2009-04-22 | Rolls Royce Plc | Gas turbine engine |
US10605167B2 (en) | 2011-04-15 | 2020-03-31 | United Technologies Corporation | Gas turbine engine front center body architecture |
US8366385B2 (en) * | 2011-04-15 | 2013-02-05 | United Technologies Corporation | Gas turbine engine front center body architecture |
US8777793B2 (en) | 2011-04-27 | 2014-07-15 | United Technologies Corporation | Fan drive planetary gear system integrated carrier and torque frame |
US8814503B2 (en) * | 2011-06-08 | 2014-08-26 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US9133729B1 (en) | 2011-06-08 | 2015-09-15 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US8297916B1 (en) * | 2011-06-08 | 2012-10-30 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US9239012B2 (en) | 2011-06-08 | 2016-01-19 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US8770922B2 (en) * | 2011-06-08 | 2014-07-08 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US9631558B2 (en) | 2012-01-03 | 2017-04-25 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
US9523422B2 (en) | 2011-06-08 | 2016-12-20 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US8935923B2 (en) * | 2011-10-25 | 2015-01-20 | United Technologies Corporation | Gas turbine engine with intercooling turbine section and intercooling turbine section bypass |
US9003808B2 (en) | 2011-11-02 | 2015-04-14 | United Technologies Corporation | Turbofan with gear-driven compressor and fan-driven core |
US9169728B2 (en) | 2011-12-08 | 2015-10-27 | General Electric Company | Dynamic load reduction system |
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 |
US8887487B2 (en) | 2012-01-31 | 2014-11-18 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US10400629B2 (en) | 2012-01-31 | 2019-09-03 | United Technologies Corporation | Gas turbine engine shaft bearing configuration |
US8863491B2 (en) | 2012-01-31 | 2014-10-21 | United Technologies Corporation | Gas turbine engine shaft bearing configuration |
US9038366B2 (en) | 2012-01-31 | 2015-05-26 | United Technologies Corporation | LPC flowpath shape with gas turbine engine shaft bearing configuration |
US10145266B2 (en) * | 2012-01-31 | 2018-12-04 | United Technologies Corporation | Gas turbine engine shaft bearing arrangement |
US20150345426A1 (en) | 2012-01-31 | 2015-12-03 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US8935913B2 (en) | 2012-01-31 | 2015-01-20 | 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 |
US8402741B1 (en) * | 2012-01-31 | 2013-03-26 | United Technologies Corporation | Gas turbine engine shaft bearing configuration |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US9476323B2 (en) | 2012-05-31 | 2016-10-25 | United Technologies Corporation | Turbine gear assembly support having symmetrical removal features |
US8572943B1 (en) | 2012-05-31 | 2013-11-05 | United Technologies Corporation | Fundamental gear system architecture |
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 |
US9228535B2 (en) | 2012-07-24 | 2016-01-05 | United Technologies Corporation | Geared fan with inner counter rotating compressor |
US10036316B2 (en) * | 2012-10-02 | 2018-07-31 | United Technologies Corporation | Geared turbofan engine with high compressor exit temperature |
US9249685B2 (en) * | 2012-12-17 | 2016-02-02 | United Technologies Corporation | Fan drive gear system assembly guide |
BR112015017110A2 (pt) * | 2013-01-18 | 2017-07-11 | Gen Electric | motor de turbina a gás |
EP3961016A1 (en) * | 2013-02-13 | 2022-03-02 | Raytheon Technologies Corporation | Gas turbine engine geared architecture |
WO2014204526A2 (en) * | 2013-02-17 | 2014-12-24 | United Technologies Corporation | Family of geared turbo fan engines |
EP2971698B1 (en) * | 2013-03-12 | 2021-04-21 | Raytheon Technologies Corporation | Flexible coupling for geared turbine engine |
US10724479B2 (en) | 2013-03-15 | 2020-07-28 | United Technologies Corporation | Thrust efficient turbofan engine |
US9624827B2 (en) | 2013-03-15 | 2017-04-18 | United Technologies Corporation | Thrust efficient turbofan engine |
GB2513621B (en) | 2013-05-01 | 2015-09-23 | Trevor Harold Speak | Compressor system |
FR3005693B1 (fr) * | 2013-05-16 | 2017-12-22 | Snecma | Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie |
US9347373B2 (en) | 2013-12-19 | 2016-05-24 | Pratt & Whitney Canada Corp. | Gas turbine engine with transmission |
US9869190B2 (en) | 2014-05-30 | 2018-01-16 | General Electric Company | Variable-pitch rotor with remote counterweights |
EP3018300B1 (de) | 2014-11-10 | 2017-12-06 | MTU Aero Engines GmbH | Gasturbine |
DE102014222870A1 (de) | 2014-11-10 | 2016-05-12 | MTU Aero Engines AG | Gasturbine |
US10072510B2 (en) | 2014-11-21 | 2018-09-11 | General Electric Company | Variable pitch fan for gas turbine engine and method of assembling the same |
US11225913B2 (en) | 2015-02-19 | 2022-01-18 | Raytheon Technologies Corporation | Method of providing turbine engines with different thrust ratings |
US20160245184A1 (en) * | 2015-02-19 | 2016-08-25 | United Technologies Corporation | Geared turbine engine |
FR3034140B1 (fr) * | 2015-03-26 | 2018-09-07 | Safran Aircraft Engines | Turbomachine d’aeronef a reducteur planetaire ou epicycloidal |
CA2934668C (en) * | 2015-07-09 | 2018-11-06 | General Electric Company | Bearing assembly for supporting a rotor shaft of a gas turbine engine |
US10100653B2 (en) | 2015-10-08 | 2018-10-16 | General Electric Company | Variable pitch fan blade retention system |
US10539076B2 (en) * | 2015-11-10 | 2020-01-21 | General Electric Company | Self-contained lubrication cooling system with heat exchanger integrated with sump |
US10208676B2 (en) | 2016-03-29 | 2019-02-19 | General Electric Company | Gas turbine engine dual sealing cylindrical variable bleed valve |
GB2550397B (en) * | 2016-05-19 | 2018-11-21 | Derwent Aviation Consulting Ltd | A turbo machine comprising a compressor system |
US20170363098A1 (en) * | 2016-06-20 | 2017-12-21 | United Technologies Corporation | Booster compressor with speed change system |
US10274017B2 (en) | 2016-10-21 | 2019-04-30 | General Electric Company | Method and system for elastic bearing support |
US10876407B2 (en) * | 2017-02-16 | 2020-12-29 | General Electric Company | Thermal structure for outer diameter mounted turbine blades |
US10746188B2 (en) | 2017-03-14 | 2020-08-18 | Pratt & Whitney Canada Corp. | Inter-shaft bearing connected to a compressor boost system |
US11008883B2 (en) | 2017-09-20 | 2021-05-18 | General Electric Company | Turbomachine with a gearbox and integrated electric machine assembly |
US10823001B2 (en) * | 2017-09-20 | 2020-11-03 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
FR3082875B1 (fr) * | 2018-06-22 | 2020-07-03 | Safran Aircraft Engines | Turbomachine d'aeronef a au moins deux corps et prelevement de puissance |
GB201811219D0 (en) | 2018-07-09 | 2018-08-29 | Rolls Royce Plc | Apparatus for gas turbine engines |
US11156128B2 (en) | 2018-08-22 | 2021-10-26 | General Electric Company | Embedded electric machine |
US11118506B2 (en) | 2018-12-21 | 2021-09-14 | General Electric Company | Gear assembly for a turbo machine |
US11420755B2 (en) | 2019-08-08 | 2022-08-23 | General Electric Company | Shape memory alloy isolator for a gas turbine engine |
US11105223B2 (en) | 2019-08-08 | 2021-08-31 | General Electric Company | Shape memory alloy reinforced casing |
US11274557B2 (en) | 2019-11-27 | 2022-03-15 | General Electric Company | Damper assemblies for rotating drum rotors of gas turbine engines |
US11280219B2 (en) | 2019-11-27 | 2022-03-22 | General Electric Company | Rotor support structures for rotating drum rotors of gas turbine engines |
US11828235B2 (en) | 2020-12-08 | 2023-11-28 | General Electric Company | Gearbox for a gas turbine engine utilizing shape memory alloy dampers |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
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 (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6023A (en) * | 1849-01-09 | Body-brace | ||
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 |
JPH02245454A (ja) * | 1989-01-03 | 1990-10-01 | General Electric Co <Ge> | ターボファンエンジン |
EP0558769A1 (de) * | 1992-02-29 | 1993-09-08 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Turbofantriebwerk mit Niederdruckverdichter ( Booster ) |
JPH08501370A (ja) * | 1993-07-06 | 1996-02-13 | ロールス‐ロイス、パブリック、リミテッド、カンパニー | ガスタービンエンジンにおける軸力の伝達 |
JP2006144794A (ja) * | 2004-11-19 | 2006-06-08 | Snecma | 駆動軸の第1および第2の軸受に共通の分断装置を備えるターボ機械、分断装置を備える圧縮機、および分断装置 |
Family Cites Families (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1309721A (en) * | 1971-01-08 | 1973-03-14 | Secr Defence | Fan |
US3792586A (en) * | 1973-01-22 | 1974-02-19 | Avco Corp | Bearing assembly systems |
DE2745131A1 (de) * | 1977-10-07 | 1979-04-12 | Motoren Turbinen Union | Kombinationsgasturbinentriebwerk fuer fluggeraete mit v/stol eigenschaften |
GB2195712B (en) * | 1986-10-08 | 1990-08-29 | Rolls Royce Plc | A turbofan gas turbine engine |
GB8630754D0 (en) * | 1986-12-23 | 1987-02-04 | Rolls Royce Plc | Turbofan gas turbine engine |
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 |
DE4122008A1 (de) | 1991-07-03 | 1993-01-14 | Mtu Muenchen Gmbh | Propfantriebwerk mit gegenlaeufigem niederdruckverdichter (booster) |
US5388964A (en) * | 1993-09-14 | 1995-02-14 | General Electric Company | Hybrid rotor blade |
FR2759734B1 (fr) * | 1997-02-20 | 1999-04-09 | Snecma | Turbomachine a systeme de compression optimise |
FR2761412B1 (fr) * | 1997-03-27 | 1999-04-30 | Snecma | Groupe turbopropulseur double corps a regulation isodrome |
US6158210A (en) * | 1998-12-03 | 2000-12-12 | General Electric Company | Gear driven booster |
USH2032H1 (en) | 1999-10-01 | 2002-07-02 | The United States Of America As Represented By The Secretary Of The Air Force | Integrated fan-core twin spool counter-rotating turbofan gas turbine engine |
FR2826052B1 (fr) * | 2001-06-19 | 2003-12-19 | Snecma Moteurs | Dispositif de secours au rallumage d'un turboreacteur en autorotation |
US6732502B2 (en) | 2002-03-01 | 2004-05-11 | General Electric Company | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor |
US6739120B2 (en) | 2002-04-29 | 2004-05-25 | General Electric Company | Counterrotatable booster compressor assembly for a gas turbine engine |
FR2842565B1 (fr) * | 2002-07-17 | 2005-01-28 | Snecma Moteurs | Demarreur-generateur integre pour turbomachine |
US6711887B2 (en) | 2002-08-19 | 2004-03-30 | General Electric Co. | Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines |
US6763653B2 (en) | 2002-09-24 | 2004-07-20 | General Electric Company | Counter rotating fan aircraft gas turbine engine with aft booster |
US6763652B2 (en) | 2002-09-24 | 2004-07-20 | General Electric Company | Variable torque split aircraft gas turbine engine counter rotating low pressure turbines |
US6763654B2 (en) | 2002-09-30 | 2004-07-20 | General Electric Co. | Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans |
FR2864997B1 (fr) * | 2004-01-08 | 2006-04-28 | Snecma Moteurs | Turbomachine a turbine semi-liee entrainant un recepteur pilote de maniere a conserver une vitesse de rotation sensiblement constante |
US20050183540A1 (en) * | 2004-02-25 | 2005-08-25 | Miller Guy W. | Apparatus for driving an accessory gearbox in a gas turbine engine |
GB2411437B (en) * | 2004-02-28 | 2007-10-24 | Rolls Royce Plc | Aircraft gas turbine engines |
US7234916B2 (en) * | 2004-09-16 | 2007-06-26 | General Electric Company | Method and apparatus for balancing gas turbine engines |
US7140174B2 (en) | 2004-09-30 | 2006-11-28 | General Electric Company | Methods and apparatus for assembling a gas turbine engine |
US7186073B2 (en) | 2004-10-29 | 2007-03-06 | General Electric Company | Counter-rotating gas turbine engine and method of assembling same |
FR2878286B1 (fr) * | 2004-11-25 | 2009-05-22 | Snecma Moteurs Sa | Turbomachine comportant un generateur de courant electrique integre |
FR2882096B1 (fr) * | 2005-02-11 | 2012-04-20 | Snecma Moteurs | Turbomoteur a double corps avec des moyens de prise de mouvement sur les rotors basse pression et haute pression, module de prise de mouvement pour le turbomoteur et procede de montage du turbomoteur |
DE102005018139A1 (de) * | 2005-04-20 | 2006-10-26 | Mtu Aero Engines Gmbh | Stahltriebwerk |
US7493754B2 (en) * | 2005-10-19 | 2009-02-24 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7490461B2 (en) * | 2005-10-19 | 2009-02-17 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7493753B2 (en) * | 2005-10-19 | 2009-02-24 | General Electric Company | Gas turbine engine 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 |
US7726113B2 (en) * | 2005-10-19 | 2010-06-01 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7603844B2 (en) * | 2005-10-19 | 2009-10-20 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7526913B2 (en) * | 2005-10-19 | 2009-05-05 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7513103B2 (en) * | 2005-10-19 | 2009-04-07 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
-
2006
- 2006-10-27 US US11/553,571 patent/US7832193B2/en not_active Expired - Fee Related
-
2007
- 2007-10-18 EP EP07118743A patent/EP1916390A3/en not_active Withdrawn
- 2007-10-25 JP JP2007277467A patent/JP2008111437A/ja active Pending
-
2013
- 2013-07-17 JP JP2013148092A patent/JP5667668B2/ja not_active Expired - Fee Related
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6023A (en) * | 1849-01-09 | Body-brace | ||
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 |
JPH02245454A (ja) * | 1989-01-03 | 1990-10-01 | General Electric Co <Ge> | ターボファンエンジン |
EP0558769A1 (de) * | 1992-02-29 | 1993-09-08 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Turbofantriebwerk mit Niederdruckverdichter ( Booster ) |
JPH08501370A (ja) * | 1993-07-06 | 1996-02-13 | ロールス‐ロイス、パブリック、リミテッド、カンパニー | ガスタービンエンジンにおける軸力の伝達 |
JP2006144794A (ja) * | 2004-11-19 | 2006-06-08 | Snecma | 駆動軸の第1および第2の軸受に共通の分断装置を備えるターボ機械、分断装置を備える圧縮機、および分断装置 |
Also Published As
Publication number | Publication date |
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EP1916390A3 (en) | 2012-03-28 |
JP5667668B2 (ja) | 2015-02-12 |
US20080098713A1 (en) | 2008-05-01 |
US7832193B2 (en) | 2010-11-16 |
JP2008111437A (ja) | 2008-05-15 |
EP1916390A2 (en) | 2008-04-30 |
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