JP5264742B2 - 摺動作動装置を備えるガスタービンエンジンファンナセル用可変面積ファンノズル - Google Patents
摺動作動装置を備えるガスタービンエンジンファンナセル用可変面積ファンノズル Download PDFInfo
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- JP5264742B2 JP5264742B2 JP2009532332A JP2009532332A JP5264742B2 JP 5264742 B2 JP5264742 B2 JP 5264742B2 JP 2009532332 A JP2009532332 A JP 2009532332A JP 2009532332 A JP2009532332 A JP 2009532332A JP 5264742 B2 JP5264742 B2 JP 5264742B2
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- fan
- nacelle
- drive ring
- fan nozzle
- flap
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- 230000008859 change Effects 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 8
- 230000007246 mechanism Effects 0.000 claims description 6
- 239000007789 gas Substances 0.000 description 9
- 239000000446 fuel Substances 0.000 description 5
- 239000000567 combustion gas Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1261—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a substantially axially movable structure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1253—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure and of a substantially axially movable external member
-
- 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
- F02K3/075—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 controlling flow ratio between flows
-
- 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
- F05D2260/50—Kinematic linkage, i.e. transmission of position
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Claims (11)
- 軸を中心に画成されたコアナセルと、
少なくとも部分的に前記コアナセルの周囲に取り付けられるとともに、該コアナセルの周囲に画成された可変面積ファンノズルを有するファンナセルであって、前記可変面積ファンノズルが該ファンナセルの後縁を画定する複数のフラップを備える、ファンナセルと、
前記ファンナセルの内部で該ファンナセルに取り付けられた摺動レールと、
前記ファンナセルの内部で前記摺動レールに沿って摺動可能な駆動リングと、
前記複数の各フラップと前記駆動リングとを連結するフラップリンク機構と、
前記複数の各フラップと前記ファンナセルとを連結するヒンジと、
前記ファンナセルの内部に配置され、かつ前記軸に沿って前記駆動リングを駆動し、前記可変面積ファンノズルによって画定されるファンノズル出口面積を変更するアクチュエータと、を有し、
前記ヒンジは、周方向のヒンジ線を画定し、前記フラップリンク機構は、前記周方向のヒンジ線から径方向にオフセットされたフラップ−リング回転軸を含み、
前記駆動リングは、複数の駆動リングセグメントに分割されており、各々のセグメントは、前記複数のフラップのうち独立して移動可能な1組のフラップをそれぞれ含むことを特徴とするガスタービンエンジン用のナセルアセンブリ。 - 前記アクチュエータは、複数のリニアアクチュエータを含むことを特徴とする請求項1記載のナセルアセンブリ。
- 前記周方向のヒンジ線は、前記フラップ−リング回転軸の径方向内側に画定されていることを特徴とする請求項1記載のナセルアセンブリ。
- 前記ファンノズル出口面積は、前記ファンナセルと前記コアナセルとの間に少なくとも部分的に環状のファンノズル出口面積を画定していることを特徴とする請求項1記載のナセルアセンブリ。
- 軸を中心に画成されたコアエンジンと、
前記コアエンジンによって駆動される歯車装置と、
前記軸を中心に前記歯車装置によって駆動されるファンと、
少なくとも部分的に前記コアエンジンの周囲に画成されたコアナセルと、
前記ファンの周囲でかつ少なくとも部分的に前記コアナセルの周囲に取り付けられ、前記ファンの下流で前記コアナセルとの間にファンノズル出口面積を画定する可変面積ファンノズルを有するファンナセルであって、前記可変面積ファンノズルが該ファンナセルの後縁を画定する複数のフラップを備える、ファンナセルと、
前記ファンナセルの内部で該ファンナセルに取り付けられた摺動レールと、
前記ファンナセルの内部で前記摺動レールに沿って摺動可能な駆動リングと、
前記複数の各フラップと前記駆動リングとを連結するフラップリンク機構と、
前記複数の各フラップと前記ファンナセルとを連結するヒンジと、
前記ファンナセルの内部に配置され、かつ前記軸に沿って前記駆動リングを駆動し、前記可変面積ファンノズルによって画定されるファンノズル出口面積を変更するアクチュエータと、を有し、
前記ヒンジは、周方向のヒンジ線を画定し、前記フラップリンク機構は、前記周方向のヒンジ線から径方向にオフセットされたフラップ−リング回転軸を含み、
前記駆動リングは、複数の駆動リングセグメントに分割されており、各々の駆動リングセグメントは、前記軸に沿って前記駆動リングセグメントを駆動して前記可変面積ファンノズルのセグメントを変更するために、複数のフラップを含む独立して移動可能な1組のフラップと、前記アクチュエータと、をそれぞれ含むことを特徴とするガスタービンエンジン。 - 請求項1に記載のガスタービンエンジン用のナセルアセンブリのファンノズル出口面積の変更方法であって、
(A)前記ファンナセルと前記コアナセルとの間にファンノズル出口面積を画定する前記可変面積ファンノズルを設置し、
(B)前記駆動リングを軸方向に摺動させ、
(C)ステップ(B)に応じてファンノズル出口面積の少なくとも1つのセクタを変更するために、第1の位置と第2の位置との間で前記可変面積ファンノズルのフラップアセンブリの角度を調整するステップをそれぞれ含むことを特徴とするガスタービンエンジンのファンノズル出口面積の変更方法。 - ステップ(C)は、
(a)離陸時にファンノズル出口面積を増加させることをさらに含むことを特徴とする請求項6記載の方法。 - ステップ(B)は、
(a)前記ファンナセル内で前記駆動リングを前記摺動レールに沿って摺動させることをさらに含むことを特徴とする請求項6記載の方法。 - ステップ(C)は、
(a)前記可変面積ファンノズルと前記ファンナセルとの間に画定される前記周方向のヒンジ線を中心に前記フラップアセンブリを回転させることをさらに含むことを特徴とする請求項6記載の方法。 - ステップ(A)は、
(a)前記可変面積ファンノズルを前記ファンナセルの最も後方部分に設置することをさらに含むことを特徴とする請求項9記載の方法。 - ステップ(B)は、
(a)少なくとも第1のセグメントおよび第2のセグメントを含むように前記駆動リングを構成し、前記ファンナセル内で前記駆動リングの第1のセグメントを第2のセグメントに対して軸方向に移動し、
(b)前記可変面積ファンノズルによって推力の方向を変更するように、ファンノズル出口面積を非対称に調整することをさらに含むことを特徴とする請求項9記載の方法。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US2006/039936 WO2008045062A1 (en) | 2006-10-12 | 2006-10-12 | Fan variable area nozzle for a gas turbine engine fan nacelle with sliding actuation system |
Related Child Applications (1)
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JP2012042596A Division JP2012107633A (ja) | 2012-02-29 | 2012-02-29 | 摺動作動装置を備えるガスタービンエンジンファンナセル用可変面積ファンノズル |
Publications (2)
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JP2010506097A JP2010506097A (ja) | 2010-02-25 |
JP5264742B2 true JP5264742B2 (ja) | 2013-08-14 |
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JP2009532332A Active JP5264742B2 (ja) | 2006-10-12 | 2006-10-12 | 摺動作動装置を備えるガスタービンエンジンファンナセル用可変面積ファンノズル |
Country Status (4)
Country | Link |
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US (2) | US9194328B2 (ja) |
EP (1) | EP2074312B1 (ja) |
JP (1) | JP5264742B2 (ja) |
WO (1) | WO2008045062A1 (ja) |
Families Citing this family (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7721551B2 (en) | 2006-06-29 | 2010-05-25 | United Technologies Corporation | Fan variable area nozzle for a gas turbine engine fan nacelle |
EP3495650B8 (en) * | 2006-10-17 | 2021-04-14 | Raytheon Technologies Corporation | Method of varying an annular fan exit area of a gas turbine engine |
WO2008108847A1 (en) * | 2007-03-05 | 2008-09-12 | United Technologies Corporation | Fan variable area nozzle for a gas turbine engine fan nacelle with drive ring actuation system |
US9759087B2 (en) | 2007-08-08 | 2017-09-12 | Rohr, Inc. | Translating variable area fan nozzle providing an upstream bypass flow exit |
WO2009029401A2 (en) | 2007-08-08 | 2009-03-05 | Rohr, Inc. | Variable area fan nozzle with bypass flow |
US9885313B2 (en) * | 2009-03-17 | 2018-02-06 | United Technologes Corporation | Gas turbine engine bifurcation located fan variable area nozzle |
US8931281B2 (en) | 2010-06-07 | 2015-01-13 | United Technologies Corporation | External flap retaining mechanism |
KR101173228B1 (ko) | 2010-11-19 | 2012-08-10 | 국방과학연구소 | 가변노즐의 편심추력 최소화 장치 및 그 방법 |
FR2978125B1 (fr) * | 2011-07-22 | 2015-03-20 | Airbus Operations Sas | Nacelle pour ensemble propulsif a tuyere a section variable |
CN104040117A (zh) * | 2012-01-09 | 2014-09-10 | 联合工艺公司 | 具有齿轮传动架构的燃气涡轮发动机 |
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 |
US9816442B2 (en) * | 2012-01-31 | 2017-11-14 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
US9845726B2 (en) * | 2012-01-31 | 2017-12-19 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
US10309232B2 (en) * | 2012-02-29 | 2019-06-04 | United Technologies Corporation | Gas turbine engine with stage dependent material selection for blades and disk |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US20160017815A1 (en) * | 2013-03-12 | 2016-01-21 | United Technologies Corporation | Expanding shell flow control device |
DE102013006109A1 (de) | 2013-04-09 | 2014-10-09 | Rolls-Royce Deutschland Ltd & Co Kg | Antriebsvorrichtung einer variablen Ausströmdüse eines Fluggasturbinentriebwerks |
US20140321988A1 (en) * | 2013-04-29 | 2014-10-30 | Dresser Inc. | Device for modifying flow parameters of working fluid exiting a compressor device |
US9650991B2 (en) * | 2013-06-27 | 2017-05-16 | The Boeing Company | Pivoting ring petal actuation for variable area fan nozzle |
WO2015069350A2 (en) | 2013-08-28 | 2015-05-14 | United Technologies Corporation | Thrust reverser sliding door assembly |
US9488130B2 (en) | 2013-10-17 | 2016-11-08 | Honeywell International Inc. | Variable area fan nozzle systems with improved drive couplings |
US9951717B2 (en) | 2015-04-15 | 2018-04-24 | Hamilton Sundstrand Corporation | Asymmetric load compensation system |
US10329945B2 (en) * | 2015-04-21 | 2019-06-25 | Siemens Energy, Inc. | High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry |
FR3051228B1 (fr) | 2016-05-12 | 2020-02-14 | Herakles | Rigidification de la liaison entre volets dans une tuyere a section variable |
GB201618339D0 (en) | 2016-10-31 | 2016-12-14 | Rolls Royce Plc | Thrust vectoring nozzle |
CN113982778B (zh) * | 2021-09-22 | 2023-05-26 | 西安交通大学 | 一种用于变循环航空发动机的二维可调后涵道引射器 |
CN116378847B (zh) * | 2023-04-10 | 2023-09-29 | 南京航空航天大学 | 一种带传热和结构加强的单驱动波瓣喷管结构 |
Family Cites Families (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE526525A (ja) * | 1953-02-16 | |||
US2744381A (en) * | 1953-06-25 | 1956-05-08 | Arsene N Lucian | Jet power plant for aircraft |
US2901910A (en) * | 1957-04-22 | 1959-09-01 | Westinghouse Electric Corp | Actuating mechanism |
GB865881A (en) | 1959-12-07 | 1961-04-19 | Mini Of Nat Defence For Canada | Means for actuating a variable area jet propulsion nozzle |
FR1422203A (fr) * | 1964-11-03 | 1965-12-24 | Snecma | Perfectionnement à la régulation de section des tuyères à effet de silencieux |
US3892358A (en) * | 1971-03-17 | 1975-07-01 | Gen Electric | Nozzle seal |
US3831493A (en) * | 1972-06-19 | 1974-08-27 | Gen Electric | Propulsion nozzle and actuator system employed therein |
US3988889A (en) * | 1974-02-25 | 1976-11-02 | General Electric Company | Cowling arrangement for a turbofan engine |
GB1605260A (en) * | 1974-09-07 | 1986-11-12 | Rolls Royce | Gas turbine engines |
US4132068A (en) * | 1975-04-30 | 1979-01-02 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Variable area exhaust nozzle |
US4068469A (en) * | 1975-05-29 | 1978-01-17 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable thrust nozzle for quiet turbofan engine and method of operating same |
GB8630754D0 (en) * | 1986-12-23 | 1987-02-04 | Rolls Royce Plc | Turbofan gas turbine engine |
US4994660A (en) * | 1989-04-11 | 1991-02-19 | Hitachi, Ltd. | Axisymmetric vectoring exhaust nozzle |
US5150839A (en) * | 1991-03-14 | 1992-09-29 | General Electric Company | Nozzle load management |
EP0723075B1 (en) * | 1991-05-16 | 2001-11-21 | General Electric Company | Thermal shield for axisymmetric vectoring nozzle |
ES2136475B1 (es) | 1994-05-20 | 2000-05-16 | Sener Ing & Sist | Perfeccionamientos en toberas axisimetricas de geometria variable y orientacion del flujo destinadas a propulsores de turbina de gas. |
DE69718164T2 (de) * | 1997-08-28 | 2003-10-23 | Turbo Propulsores Ind | Zentriervorrichtung mit gekreuzten Querverbindungen für die ungesteuerten Klappen einer verstellbaren convergent-divergenten-Schubdüse |
FR2792367B1 (fr) * | 1999-04-15 | 2002-04-26 | Snecma | Tuyere d'ejection axisymetrique, convergente divergente a orientation par un anneau guide |
FR2792368B1 (fr) * | 1999-04-19 | 2001-05-25 | Snecma | Tuyere d'ejection de turboreacteur a systeme d'orientation du type cardan |
JP2001342897A (ja) * | 2000-06-01 | 2001-12-14 | Ishikawajima Harima Heavy Ind Co Ltd | ターボファンエンジンの可変バイパスノズル装置 |
GB2372779A (en) | 2001-03-03 | 2002-09-04 | Rolls Royce Plc | Gas turbine engine nozzle with noise reducing tabs |
US6415599B1 (en) * | 2001-05-11 | 2002-07-09 | General Electric Company | Engine interface for axisymmetric vectoring nozzle |
JP4736271B2 (ja) * | 2001-08-16 | 2011-07-27 | 株式会社Ihi | ジェットエンジン用排気ノズル |
US7096661B2 (en) * | 2004-03-26 | 2006-08-29 | United Technologies Corporation | Axial divergent section slot nozzle |
-
2006
- 2006-10-12 WO PCT/US2006/039936 patent/WO2008045062A1/en active Application Filing
- 2006-10-12 US US12/441,729 patent/US9194328B2/en active Active
- 2006-10-12 EP EP06850518.9A patent/EP2074312B1/en active Active
- 2006-10-12 JP JP2009532332A patent/JP5264742B2/ja active Active
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2015
- 2015-08-26 US US14/835,879 patent/US10519898B2/en active Active
Also Published As
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US20150361919A1 (en) | 2015-12-17 |
US9194328B2 (en) | 2015-11-24 |
US10519898B2 (en) | 2019-12-31 |
JP2010506097A (ja) | 2010-02-25 |
US20090266912A1 (en) | 2009-10-29 |
EP2074312B1 (en) | 2017-12-13 |
WO2008045062A1 (en) | 2008-04-17 |
EP2074312A1 (en) | 2009-07-01 |
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