JP5009586B2 - ギヤボックス及びギヤボックスを備えるガスタービンエンジン組立体 - Google Patents
ギヤボックス及びギヤボックスを備えるガスタービンエンジン組立体 Download PDFInfo
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- JP5009586B2 JP5009586B2 JP2006280907A JP2006280907A JP5009586B2 JP 5009586 B2 JP5009586 B2 JP 5009586B2 JP 2006280907 A JP2006280907 A JP 2006280907A JP 2006280907 A JP2006280907 A JP 2006280907A JP 5009586 B2 JP5009586 B2 JP 5009586B2
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- Prior art keywords
- coupled
- assembly
- fan assembly
- thrust
- turbine 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
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- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- 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
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
- F16H1/2809—Toothed gearings for conveying rotary motion with gears having orbital motion with means for equalising the distribution of load on the planet-wheels
- F16H1/2827—Toothed gearings for conveying rotary motion with gears having orbital motion with means for equalising the distribution of load on the planet-wheels by allowing limited movement of the planet carrier, e.g. relative to its shaft
-
- 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
- F05D2240/50—Bearings
- F05D2240/52—Axial thrust bearings
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/08—General details of gearing of gearings with members having orbital motion
- F16H57/082—Planet carriers
-
- 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)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
11 長手方向軸線
12 コアガスタービンエンジン
13 フレーム
14 低圧タービン
15 構造支持部材
16 回転ファン組立体
20 外側ケーシング
22 環状のコアエンジン入口
24 ブースタ圧縮機
26 駆動圧縮機
28 燃焼器
30 高圧タービン
32 第1の回転駆動シャフト
34 第2の回転駆動シャフト
36 排出ノズル
50 ファン組立体
52 第2のファン組立体
60 ロータブレード
62 ロータブレード
64 ナセル
66 ロータディスク
68 ロータディスク
70 ロータブレード
72 ロータディスク
74 入口ガイドベーン組立体
76 ガイドベーン
78 ブースタケース
80 第1の回転方向
82 第2の回転方向
84 コーン
86 第1の又は前方端部
88 第2の又は後方端部
90 コーン
92 第1の又は前方端部
94 第2の又は後方端部
100 ギヤボックス
102 ギヤボックスハウジング
103 歯車
104 入力部
106 出力部
110 スラスト軸受組立体
111 インナレース
112 軸受支持構造体
113 表面
114 内側溝
116 アウタレース
117 表面
118 外側溝
119 複数のベアリング
120 スラスト軸受組立体
122 インナレース
123 表面
124 内側溝
126 アウタレース
127 表面
128 外側溝
129 複数のベアリング
130 ローラ軸受組立体
132 インナレース
133 表面
134 内側溝
136 アウタレース
137 表面
138 外側溝
139 複数のローラ
140 ローラ軸受組立体
142 インナレース
143 表面
144 内側溝
146 アウタレース
147 表面
148 外側溝
149 複数のローラ
160 出力部構造体
168 後方ファン前方シャフト
170 サンプ
190 開口
200 スプラインシステム
202 第1のスプライン組立体
204 第2のスプライン組立体
206 第3のスプライン組立体
208 第4のスプライン組立体
210 第1の部分
212 第2の部分
230 内側部分
232 外側部分
300 太陽歯車
302 遊星歯車
320 支持構造体
330 第1の部分
332 第2の部分
334 本体部分
336 第1の端部
338 第2の端部
340 支持構造体
344 後方軸受支持構造体
346 連結部材
350 開口
352 幅
354 長さ
360 開口
362 開口
364 ファスナ
370 ばね
372 本体部分
374 第1の端部
376 第2の端部
390 複数の開口
Claims (9)
- 駆動シャフト(34)の周りで円周方向に配置されたギアボックス(100)であって、
前記駆動シャフト(34)が回転できるように該駆動シャフトに結合された入力部(104)と、
出力部(106)と、
支持構造体(320)と、
前記支持構造体内に支持され、前記入力部と結合された少なくとも1つの太陽歯車(300)と、
前記支持構造体内に結合された複数の遊星歯車(302)と、
前記駆動シャフト(34)が回転できるように該駆動シャフトに結合されたスラスト軸受組立体(110)と
を含み、
前記複数の遊星歯車(302)は、前記太陽歯車(300)と互いに噛み合うように配置され、前記出力部を介して駆動力を出力するよう構成され、
前記支持構造体が、第1の部分(330)と、第2の部分(332)と、該第1及び第2の部分間に結合されたスラストばね(370)と、を含んでほぼ円筒形状を呈し、
前記第1の部分(330)は、該第一の部分と一体に形成された複数の遊星歯車支持構造体(340)を介して前記遊星歯車(302)に対して構造的支持を与え、
前記第2の部分(332)は、前記第1の部分から軸方向後方に延び、前記スラスト軸受組立体(110)を収容し、
前記スラストばね(370)は、軸方向に延びる本体部分(372)と、該本体部分(372)から半径方向内向きに延び且つ前記第1の部分(330)と一体に形成された第1の端部(374)と、前記本体部分(372)から半径方向外向きに延びる第2の端部(376)とからなり、軸方向断面ほぼZ字形である
ことを特徴とする、ギヤボックス(100)。 - 前記第1の部分(330)、第2の部分(332)及びスラストばね(370)が、単体構造に形成される、請求項1記載のギヤボックス(100)。
- 前記入力部(104)がガスタービンエンジン(12)の低圧タービン(14)に結合されており、
前記出力部(106)が二重反転ファン組立体(16)に結合されており、
前記スラストばね(370)が、前記二重反転ファン組立体によって発生したスラストを少なくとも部分的に吸収するように構成される、
請求項1記載のギヤボックス(100)。 - 前記スラストばね(370)が、該スラストばねを貫通する複数の開口(190)を含み、前記開口の数量及び該開口の寸法の少なくとも1つが、前記スラストばねによって吸収されるスラストに基づいている、請求項1記載のギヤボックス(100)。
- 前記ギヤボックスが、前記支持構造体(112)内に結合されたスラスト軸受(110)をさらに含む、請求項1記載のギヤボックス(100)。
- 前記スラスト軸受(110)が、ガスタービンエンジン(12)のフレーム(13)に結合されたアウタレース(116)と、前記二重反転ファン組立体(16)に結合された半径方向内側レース(111)とを含む、請求項1記載のギヤボックス(100)。
- コアタービンエンジン(12)と、
前記コアタービンエンジンに結合された低圧タービン(14)と、
前記低圧タービンに結合された請求項1に記載のギヤボックス(100)と、
前記ギヤボックスに結合された二重反転ファン組立体(16)と、
を含む、タービンエンジン組立体(10)。 - 前記第1の部分(210)、第2の部分(212)及びスラストばね(370)が、単体構造に形成される、請求項7記載のタービンエンジン組立体(10)。
- 前記入力部(104)が前記低圧タービン(14)に結合され、
前記出力部(106)が前記二重反転ファン組立体(16)に結合され、
前記スラストばね(370)が、前記二重反転ファン組立体によって発生したスラストを少なくとも部分的に吸収するように構成される、
請求項7記載のタービンエンジン組立体(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/253,935 US7490460B2 (en) | 2005-10-19 | 2005-10-19 | Gas turbine engine assembly and methods of assembling same |
US11/253,935 | 2005-10-19 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2007113581A JP2007113581A (ja) | 2007-05-10 |
JP5009586B2 true JP5009586B2 (ja) | 2012-08-22 |
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Application Number | Title | Priority Date | Filing Date |
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JP2006280907A Expired - Fee Related JP5009586B2 (ja) | 2005-10-19 | 2006-10-16 | ギヤボックス及びギヤボックスを備えるガスタービンエンジン組立体 |
Country Status (5)
Country | Link |
---|---|
US (1) | US7490460B2 (ja) |
EP (1) | EP1783344B1 (ja) |
JP (1) | JP5009586B2 (ja) |
CN (1) | CN1952435B (ja) |
DE (1) | DE602006011409D1 (ja) |
Families Citing this family (80)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7490460B2 (en) * | 2005-10-19 | 2009-02-17 | 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 |
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US8667775B1 (en) * | 2009-08-05 | 2014-03-11 | The Boeing Company | Reverse flow engine core having a ducted fan with integrated secondary flow blades |
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US10145266B2 (en) * | 2012-01-31 | 2018-12-04 | United Technologies Corporation | Gas turbine engine shaft bearing arrangement |
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US9011076B2 (en) * | 2012-02-29 | 2015-04-21 | United Technologies Corporation | Counter-rotating low pressure turbine with gear system mounted to 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 |
WO2014011245A2 (en) * | 2012-03-23 | 2014-01-16 | United Technologies Corporation | Planetary gear system arrangement with auxiliary oil system |
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US20130269479A1 (en) * | 2012-04-11 | 2013-10-17 | General Electric Company | Gearbox and support apparatus for gearbox carrier |
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EP2901033A4 (en) * | 2012-09-28 | 2016-05-25 | United Technologies Corp | ASSEMBLY PROCESS FOR A FAN DRIVE GEARBOX SYSTEM |
WO2014151785A1 (en) | 2013-03-15 | 2014-09-25 | United Technologies Corporation | Turbofan engine bearing and gearbox arrangement |
WO2014204633A1 (en) * | 2013-06-21 | 2014-12-24 | United Technologies Corporation | Nonlinear rolling bearing radial support stiffness |
US9739173B2 (en) * | 2013-10-01 | 2017-08-22 | United Technologies Corporation | Gas turbine lubrication systems |
EP3084181B1 (en) | 2013-12-20 | 2021-11-03 | Raytheon Technologies Corporation | Geared turbofan with improved gear system maintainability |
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US9562602B2 (en) | 2014-07-07 | 2017-02-07 | Solar Turbines Incorporated | Tri-lobe bearing for a gearbox |
US9909453B2 (en) | 2015-05-19 | 2018-03-06 | General Electric Company | Lubrication system for a turbine engine |
GB201516571D0 (en) * | 2015-09-18 | 2015-11-04 | Rolls Royce Plc | A Coupling for a Geared Turbo Fan |
GB201516570D0 (en) * | 2015-09-18 | 2015-11-04 | Rolls Royce Plc | A Shafting Arrangement |
US10415429B2 (en) | 2015-09-25 | 2019-09-17 | General Electric Company | Planet gearbox with cylindrical roller bearing with high density roller packing |
US10234018B2 (en) | 2015-10-19 | 2019-03-19 | General Electric Company | Planet gearbox with cylindrical roller bearing with under race lube scheme |
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US10113633B2 (en) | 2016-01-28 | 2018-10-30 | General Electric Company | Gearbox planet squeeze film damper |
US10274071B2 (en) | 2016-01-28 | 2019-04-30 | General Electric Company | Gearbox planet squeeze film damper |
US9677659B1 (en) | 2016-01-28 | 2017-06-13 | General Electric Company | Gearbox planet attenuation spring damper |
GB201614366D0 (en) * | 2016-08-23 | 2016-10-05 | Rolls Royce Plc | A mounting arrangement for a planet gear |
EP3354847B1 (en) * | 2017-01-30 | 2023-03-08 | GE Avio S.r.l. | Flexible coupling shaft for turbine engine |
US11105200B2 (en) | 2017-07-13 | 2021-08-31 | General Electric Company | Counter rotating power turbine with reduction gearbox |
US11131244B2 (en) | 2017-11-03 | 2021-09-28 | General Electric Company | Power transmission system and gas turbine engine comprising the same |
US10724445B2 (en) | 2018-01-03 | 2020-07-28 | Raytheon Technologies Corporation | Method of assembly for fan drive gear system with rotating carrier |
EP3587774A1 (en) * | 2018-06-27 | 2020-01-01 | Rolls-Royce plc | Gas turbine |
FR3092885B1 (fr) | 2019-02-20 | 2021-09-24 | Safran Trans Systems | Solaire pour un reducteur mecanique de turbomachine d’aeronef |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
CN115614155B (zh) * | 2022-08-30 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | 一种引气支板及含有引气支板的中介机匣 |
Family Cites Families (35)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1207148A (en) | 1967-12-01 | 1970-09-30 | Und Eisengiesserei Dassau Veb | Planet wheel gearing |
GB1350431A (en) * | 1971-01-08 | 1974-04-18 | Secr Defence | Gearing |
US3922852A (en) * | 1973-10-17 | 1975-12-02 | Gen Electric | Variable pitch fan for gas turbine engine |
US3866415A (en) * | 1974-02-25 | 1975-02-18 | Gen Electric | Fan blade actuator using pressurized air |
CA1100785A (en) | 1978-04-27 | 1981-05-12 | Willis E. Windish | Clutch assemblies for use in planetary transmissions |
GB2195712B (en) * | 1986-10-08 | 1990-08-29 | Rolls Royce Plc | A turbofan gas turbine engine |
US4744214A (en) * | 1987-06-29 | 1988-05-17 | United Technologies Corporation | Engine modularity |
US5010729A (en) * | 1989-01-03 | 1991-04-30 | General Electric Company | Geared counterrotating turbine/fan propulsion system |
US4969325A (en) * | 1989-01-03 | 1990-11-13 | General Electric Company | Turbofan engine having a counterrotating partially geared fan drive turbine |
DE3933776A1 (de) * | 1989-10-10 | 1991-04-18 | Mtu Muenchen Gmbh | Propfan-turbotriebwerk |
US5394967A (en) * | 1993-02-12 | 1995-03-07 | Warn Industries, Inc. | Connect/disconnect mechanism for a vehicle drive train |
US5433674A (en) * | 1994-04-12 | 1995-07-18 | United Technologies Corporation | Coupling system for a planetary gear train |
US5809772A (en) * | 1996-03-29 | 1998-09-22 | General Electric Company | Turbofan engine with a core driven supercharged bypass duct |
US5806303A (en) * | 1996-03-29 | 1998-09-15 | General Electric Company | Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle |
US5867980A (en) | 1996-12-17 | 1999-02-09 | General Electric Company | Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner |
US5813214A (en) * | 1997-01-03 | 1998-09-29 | General Electric Company | Bearing lubrication configuration in a turbine engine |
DE19828562B4 (de) * | 1998-06-26 | 2005-09-08 | Mtu Aero Engines Gmbh | Triebwerk mit gegenläufig drehenden Rotoren |
US6158210A (en) * | 1998-12-03 | 2000-12-12 | General Electric Company | Gear driven booster |
US6619030B1 (en) * | 2002-03-01 | 2003-09-16 | General Electric Company | Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors |
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 |
US6684626B1 (en) * | 2002-07-30 | 2004-02-03 | General Electric Company | Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines |
US6711887B2 (en) * | 2002-08-19 | 2004-03-30 | General Electric Co. | Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines |
US6763652B2 (en) * | 2002-09-24 | 2004-07-20 | General Electric Company | Variable torque split aircraft gas turbine engine 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 |
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 |
GB0406174D0 (en) | 2004-03-19 | 2004-04-21 | Rolls Royce Plc | Turbine engine arrangement |
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 |
US7685808B2 (en) * | 2005-10-19 | 2010-03-30 | 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 |
US7603844B2 (en) * | 2005-10-19 | 2009-10-20 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US20080000322A1 (en) * | 2006-06-30 | 2008-01-03 | Hillyer Harold G | Dual shaft power take-off |
US7841165B2 (en) * | 2006-10-31 | 2010-11-30 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7716914B2 (en) * | 2006-12-21 | 2010-05-18 | General Electric Company | Turbofan engine assembly and method of assembling same |
-
2005
- 2005-10-19 US US11/253,935 patent/US7490460B2/en not_active Expired - Fee Related
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2006
- 2006-10-16 DE DE602006011409T patent/DE602006011409D1/de active Active
- 2006-10-16 EP EP06255322A patent/EP1783344B1/en not_active Expired - Fee Related
- 2006-10-16 JP JP2006280907A patent/JP5009586B2/ja not_active Expired - Fee Related
- 2006-10-19 CN CN2006101355533A patent/CN1952435B/zh not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
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CN1952435B (zh) | 2011-04-06 |
DE602006011409D1 (de) | 2010-02-11 |
EP1783344A1 (en) | 2007-05-09 |
JP2007113581A (ja) | 2007-05-10 |
US20070084187A1 (en) | 2007-04-19 |
US7490460B2 (en) | 2009-02-17 |
EP1783344B1 (en) | 2009-12-30 |
CN1952435A (zh) | 2007-04-25 |
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