JP2016509153A - 逆回転一体型駆動装置及びベーンレスタービンを備えたエンジン構成 - Google Patents
逆回転一体型駆動装置及びベーンレスタービンを備えたエンジン構成 Download PDFInfo
- Publication number
- JP2016509153A JP2016509153A JP2015553777A JP2015553777A JP2016509153A JP 2016509153 A JP2016509153 A JP 2016509153A JP 2015553777 A JP2015553777 A JP 2015553777A JP 2015553777 A JP2015553777 A JP 2015553777A JP 2016509153 A JP2016509153 A JP 2016509153A
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- Japan
- Prior art keywords
- stage
- gas turbine
- turbine engine
- stage blade
- fan
- 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.)
- Pending
Links
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
- 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
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- 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
- F02C3/073—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 the compressor and turbine stages being concentric
-
- 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
- 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
- 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
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
加えて、一体型駆動装置60は、低圧タービン段の反転を可能にする。
12 エンジン入口端部
13 プロパルサー
14 圧縮機
16 燃焼器
18 ファン
20 高圧タービン
24 シャフト
26 エンジン軸線
28 シャフト
30 低圧タービン
32 ブースタ
40 反転段ブレード
50 反転段ブレード
60 駆動装置
Claims (15)
- ガスタービンエンジン(10)であって、
ファン(18)と、
圧縮機(14)と、
第1段ブレード(40)及び第2段ブレード(50)を有し、該第1段ブレードが第1の方向に回転し、前記第2段ブレードが前記第1段ブレードと反転の第2の方向に回転し、前記第1段ブレード及び前記第2段ブレードが互いに直近に位置するタービン(30)と、
前記ファンと動作可能に入力接続され、前記第1段ブレード及び前記第2段ブレードと動作可能に出力接続された駆動装置(60)と、
を備え、前記駆動装置により前記第1段ブレード及び第2段ブレードが前記ファンを駆動し、前記圧縮機がまた前記第1段ブレードによって駆動される、ガスタービンエンジン(10)。 - 前記タービンが低圧タービンである、請求項1に記載のガスタービンエンジン。
- 前記駆動装置においてアイドラー星形段(62)を更に備える、請求項1に記載のガスタービンエンジン。
- 前記アイドラー星形段(62)が、前記駆動装置の入力と出力との間にギアの少なくとも1つのペアを有する、請求項3に記載のガスタービンエンジン。
- 前記駆動装置において星形段(70)を更に備える、請求項1に記載のガスタービンエンジン。
- 前記星形段が、入力及び出力と連通した複数のギアを有する、請求項5に記載のガスタービンエンジン。
- 前記第1段ブレードの前方にベーンを更に備える、請求項1に記載のガスタービンエンジン。
- 前記ベーンが前記第1段ブレードの直ぐ前にある、請求項7に記載のガスタービンエンジン。
- 前記反転する第1及び第2段ブレードが、前記タービンの前端から1又はそれ以上の段だけ離間している、請求項7に記載のガスタービンエンジン。
- ガスタービンエンジン(10)であって、
ファン(18)と、
燃焼器(16)と流体連通した圧縮機(14)と、
前記燃焼器からの燃焼ガスと流体連通したタービン(30)と、
を備え、前記タービンが少なくとも2つの反転段ブレード(40,50)を有し、該反転段ブレードには中間ベーンが存在せず、
前記ガスタービンエンジン(10)が更に、
前記タービンと前記ファンの中間に動作可能に接続され、少なくとも2つの供給源からの動力入力を受け取る分割動力経路を有する駆動装置(60)と、
互いに独立した前記2つの反転段ブレードのファンシャフト及びシャフトと、
を備え、前記2つの反転段ブレードのうちの1つが、前記圧縮機と前記ファンに動力を供給し、前記2つの反転段ブレードのうちの他方が前記ファンに動力を供給する、ガスタービンエンジン(10)。 - 前記駆動装置が、前記タービンの2つ又はそれ以上の段の各々から動力を受け取る、請求項10に記載のガスタービンエンジン。
- 前記タービンが低圧タービンである、請求項10に記載のガスタービンエンジン。
- 前記タービンが、固定ベーンと、前記固定ベーンの下流側の第1段ブレードと、前記第1段ブレードの下流側の第2段ブレードとを有する、請求項10に記載のガスタービンエンジン。
- 前記駆動装置が、アイドラー星形段(62)と星形段(70)とを有する、請求項10に記載のガスタービンエンジン。
- 前記反転段ブレードが、前記タービンの前端から1又はそれ以上の段だけ離間している、請求項10に記載のガスタービンエンジン。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201361754086P | 2013-01-18 | 2013-01-18 | |
US61/754,086 | 2013-01-18 | ||
PCT/US2014/011434 WO2014113372A1 (en) | 2013-01-18 | 2014-01-14 | Engine architecture with reverse rotation integral drive and vaneless turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2016509153A true JP2016509153A (ja) | 2016-03-24 |
Family
ID=50030541
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2015553777A Pending JP2016509153A (ja) | 2013-01-18 | 2014-01-14 | 逆回転一体型駆動装置及びベーンレスタービンを備えたエンジン構成 |
Country Status (7)
Country | Link |
---|---|
US (1) | US10227928B2 (ja) |
EP (1) | EP2946103A1 (ja) |
JP (1) | JP2016509153A (ja) |
CN (1) | CN104937251B (ja) |
BR (1) | BR112015017110A2 (ja) |
CA (1) | CA2898464C (ja) |
WO (1) | WO2014113372A1 (ja) |
Families Citing this family (23)
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US10287976B2 (en) * | 2014-07-15 | 2019-05-14 | United Technologies Corporation | Split gear system for a gas turbine engine |
US10502160B2 (en) * | 2016-02-09 | 2019-12-10 | General Electric Company | Reverse thrust engine |
US10508546B2 (en) | 2017-09-20 | 2019-12-17 | 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 |
US10781717B2 (en) | 2017-09-20 | 2020-09-22 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10738617B2 (en) | 2017-09-20 | 2020-08-11 | 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 |
US11098592B2 (en) | 2017-09-20 | 2021-08-24 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10914194B2 (en) | 2017-09-20 | 2021-02-09 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US11085309B2 (en) | 2017-09-22 | 2021-08-10 | General Electric Company | Outer drum rotor assembly |
GB201805854D0 (en) * | 2018-04-09 | 2018-05-23 | Rolls Royce Plc | Gas turbine engine and turbine arrangment |
US11753939B2 (en) | 2019-02-20 | 2023-09-12 | 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 |
US11041462B2 (en) * | 2019-06-05 | 2021-06-22 | Raytheon Technologies Corporation | Hybrid turbofan with differential electrical and mechanical power transfer |
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2014
- 2014-01-14 US US14/761,698 patent/US10227928B2/en active Active
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- 2014-01-14 WO PCT/US2014/011434 patent/WO2014113372A1/en active Application Filing
- 2014-01-14 BR BR112015017110A patent/BR112015017110A2/pt not_active Application Discontinuation
- 2014-01-14 EP EP14702163.8A patent/EP2946103A1/en not_active Withdrawn
- 2014-01-14 JP JP2015553777A patent/JP2016509153A/ja active Pending
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US20150354502A1 (en) | 2015-12-10 |
WO2014113372A1 (en) | 2014-07-24 |
CN104937251B (zh) | 2017-11-28 |
CA2898464A1 (en) | 2014-07-24 |
CA2898464C (en) | 2017-10-10 |
CN104937251A (zh) | 2015-09-23 |
BR112015017110A2 (pt) | 2017-07-11 |
US10227928B2 (en) | 2019-03-12 |
EP2946103A1 (en) | 2015-11-25 |
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