JP5181114B2 - 高圧力比後方ファン組立体及びガスタービンエンジン - Google Patents
高圧力比後方ファン組立体及びガスタービンエンジン Download PDFInfo
- Publication number
- JP5181114B2 JP5181114B2 JP2007062894A JP2007062894A JP5181114B2 JP 5181114 B2 JP5181114 B2 JP 5181114B2 JP 2007062894 A JP2007062894 A JP 2007062894A JP 2007062894 A JP2007062894 A JP 2007062894A JP 5181114 B2 JP5181114 B2 JP 5181114B2
- Authority
- JP
- Japan
- Prior art keywords
- fan
- turbine
- blade
- rotor
- blades
- 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
Links
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
- F02K3/062—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 aft fan
-
- 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
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
-
- 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)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
本発明は、添付の図面と以下の詳細な説明を参照して明らかになる。
Claims (8)
- ガスタービンエンジン(10)のファン組立体(30)において、
前記ガスタービンエンジン(10)のコア(20)後方に配設されるタービンロータ(36)と、
前記ロータ(36)により担持され、前記ロータ(36)から放射状に延伸する複合翼(38)の円周状の列と、
を備え、前記複合翼(38)の各々が、
前記ロータ(36)から先端部(52)へ延伸し、前記コア(20)により生成される加圧燃焼ガス流からエネルギーを抽出するタービン動翼(42)と、
前記タービン動翼(42)の前記先端部により担持され、該先端部から延伸してともに回転する、放射状に延伸するファン動翼(46)の軸方向に離間した少なくとも二つの列(62、72)であって、第1列および第2列の各々が2枚以上の前記ファン動翼(46)を備える、列(62、72)と、
を備え、前記ファン組立体(30)はさらに、
前記ファン動翼の前記第1及び第2列(62、72)の間に配設された静翼(90)の円周状の列を備える
ファン組立体(30)。 - 前記ファン動翼は、環状の副導管(88)内に配設されている請求項1に記載のファン組立体(30)。
- 各タービン動翼(42)は円弧状のプラットフォーム部44を含み、これらプラットフォーム部44は、相互に当接して環状のプラットフォーム(82)を画定する請求項1または2に記載のファン組立体(30)。
- 各タービン動翼(42)は、
円周上に離間し、放射状に延伸する少なくとも二つの第1ファン動翼であって、前記タービン動翼(42)の前記先端部(52)から延伸する第1ファン動翼と、
前記第1ファン動翼から下流に位置し、前記タービン動翼(42)の前記先端部(52)から延伸する、円周上に離間し放射状に延伸する少なくとも二つの第2ファン動翼(46A)と、
を担持する請求項1から3のいずれかに記載のファン組立体(30)。 - 流れの順に圧縮機、燃焼器(16)及び高圧タービンを含み、加圧燃焼ガス流を生成するコア(20)と、
請求項1から4のいずれかに記載のファン組立体(30)と
を備えるガスタービンエンジン(10)。 - 前記ファン動翼は、環状の副導管(88)内に配設されている請求項5に記載のガスタービンエンジン(10)。
- 各タービン動翼(42)は円弧状のプラットフォーム部(44)を含み、これらプラットフォーム部(44)は、相互に当接して環状のプラットフォーム(82)を画定する請求項5または6に記載のガスタービンエンジン(10)。
- 各タービン動翼(42)は、
円周上に離間し、放射状に延伸する少なくとも二つの第1ファン動翼であって、前記タービン動翼(42)の前記先端部(52)から延伸する第1ファン動翼(46A)と、
前記第1ファン動翼から下流に位置し、前記タービン動翼(42)の前記先端部(52)から延伸する、円周上に離間し放射状に延伸する少なくとも二つの第2ファン動翼(46B)と、
を担持する請求項5から7のいずれかに記載のガスタービンエンジン(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/308,219 | 2006-03-13 | ||
US11/308,219 US7631484B2 (en) | 2006-03-13 | 2006-03-13 | High pressure ratio aft fan |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2007247645A JP2007247645A (ja) | 2007-09-27 |
JP5181114B2 true JP5181114B2 (ja) | 2013-04-10 |
Family
ID=37969828
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007062894A Expired - Fee Related JP5181114B2 (ja) | 2006-03-13 | 2007-03-13 | 高圧力比後方ファン組立体及びガスタービンエンジン |
Country Status (4)
Country | Link |
---|---|
US (1) | US7631484B2 (ja) |
EP (1) | EP1835147B1 (ja) |
JP (1) | JP5181114B2 (ja) |
CN (1) | CN101037960B (ja) |
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FR2914943B1 (fr) * | 2007-04-13 | 2011-04-01 | Snecma | Aube de soufflante |
US20090092494A1 (en) * | 2007-10-04 | 2009-04-09 | General Electric Company | Disk rotor and method of manufacture |
DE102008060488A1 (de) * | 2008-12-05 | 2010-06-10 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren und Vorrichtung zum Betrieb eines mit Schubpropellern versehenen Turboprop-Flugtriebwerkes |
US20110167784A1 (en) * | 2009-09-25 | 2011-07-14 | James Edward Johnson | Method of operating a convertible fan engine |
US20110167792A1 (en) * | 2009-09-25 | 2011-07-14 | James Edward Johnson | Adaptive engine |
US20110120083A1 (en) * | 2009-11-20 | 2011-05-26 | Rollin George Giffin | Gas turbine engine with outer fans |
US8695324B2 (en) * | 2009-11-20 | 2014-04-15 | General Electric Co. | Multistage tip fan |
CN101881237A (zh) * | 2010-06-22 | 2010-11-10 | 季承 | 涡扇后置式发动机 |
CN102305152A (zh) * | 2011-05-20 | 2012-01-04 | 中国科学院工程热物理研究所 | 混排航空发动机 |
US9239012B2 (en) | 2011-06-08 | 2016-01-19 | 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 |
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 |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US20150330300A1 (en) * | 2013-03-14 | 2015-11-19 | United Technologies Corporation | Two spool engine core with a starter |
EP2949882B1 (en) * | 2013-06-03 | 2017-08-23 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
US9869190B2 (en) | 2014-05-30 | 2018-01-16 | General Electric Company | Variable-pitch rotor with remote counterweights |
US10072510B2 (en) | 2014-11-21 | 2018-09-11 | General Electric Company | Variable pitch fan for gas turbine engine and method of assembling the same |
US10711631B2 (en) * | 2014-12-24 | 2020-07-14 | Raytheon Technologies Corporation | Turbine engine with guide vanes forward of its fan blades |
CN106286010B (zh) * | 2015-06-26 | 2018-10-26 | 中航空天发动机研究院有限公司 | 一种反向安装核心机的齿轮传动涡扇发动机 |
CN105179089A (zh) * | 2015-09-10 | 2015-12-23 | 洛阳大智实业有限公司 | 一种推进式涡轮螺旋桨发动机 |
US10100653B2 (en) | 2015-10-08 | 2018-10-16 | General Electric Company | Variable pitch fan blade retention system |
US10287024B2 (en) | 2016-08-04 | 2019-05-14 | United Technologies Corporation | Direct drive aft fan engine |
US10352274B2 (en) | 2016-08-18 | 2019-07-16 | United Technologies Corporation | Direct drive aft fan engine |
US10823056B2 (en) | 2016-12-07 | 2020-11-03 | Raytheon Technologies Corporation | Boundary layer excitation aft fan gas turbine engine |
CN106593694B (zh) * | 2016-12-23 | 2018-03-20 | 李可 | 一种向心式涡轮风扇喷气式发动机 |
WO2020144854A1 (ja) * | 2019-01-11 | 2020-07-16 | 三菱重工エンジン&ターボチャージャ株式会社 | 回転機械 |
GB201903262D0 (en) * | 2019-03-11 | 2019-04-24 | Rolls Royce Plc | Efficient gas turbine engine installation and operation |
GB201906168D0 (en) * | 2019-05-02 | 2019-06-19 | Rolls Royce Plc | Gas turbine engine with fan outlet guide vanes |
CN112727635B (zh) * | 2020-12-31 | 2022-04-26 | 中国航空发动机研究院 | 一种双外涵发动机 |
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US11795964B2 (en) | 2021-07-16 | 2023-10-24 | General Electric Company | Levered counterweight feathering system |
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2006
- 2006-03-13 US US11/308,219 patent/US7631484B2/en not_active Expired - Fee Related
-
2007
- 2007-03-05 EP EP07103469A patent/EP1835147B1/en not_active Ceased
- 2007-03-13 CN CN2007100862997A patent/CN101037960B/zh not_active Expired - Fee Related
- 2007-03-13 JP JP2007062894A patent/JP5181114B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US20070209368A1 (en) | 2007-09-13 |
EP1835147B1 (en) | 2012-05-23 |
CN101037960A (zh) | 2007-09-19 |
JP2007247645A (ja) | 2007-09-27 |
EP1835147A2 (en) | 2007-09-19 |
US7631484B2 (en) | 2009-12-15 |
CN101037960B (zh) | 2013-12-04 |
EP1835147A3 (en) | 2011-03-23 |
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