JP4890423B2 - ターボファンエンジンノズル組立体及びターボファンエンジン組立体 - Google Patents
ターボファンエンジンノズル組立体及びターボファンエンジン組立体 Download PDFInfo
- Publication number
- JP4890423B2 JP4890423B2 JP2007289264A JP2007289264A JP4890423B2 JP 4890423 B2 JP4890423 B2 JP 4890423B2 JP 2007289264 A JP2007289264 A JP 2007289264A JP 2007289264 A JP2007289264 A JP 2007289264A JP 4890423 B2 JP4890423 B2 JP 4890423B2
- Authority
- JP
- Japan
- Prior art keywords
- flap
- nacelle
- assembly
- nozzle assembly
- core cowl
- 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
- 230000008859 change Effects 0.000 claims description 10
- 230000007246 mechanism Effects 0.000 claims description 4
- 230000008878 coupling Effects 0.000 claims 3
- 238000010168 coupling process Methods 0.000 claims 3
- 238000005859 coupling reaction Methods 0.000 claims 3
- 239000007789 gas Substances 0.000 description 21
- 239000003570 air Substances 0.000 description 14
- 238000000034 method Methods 0.000 description 7
- 238000002485 combustion reaction Methods 0.000 description 6
- 239000000446 fuel Substances 0.000 description 6
- 238000000429 assembly Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Images
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
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
- F02K1/085—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone by transversely deforming an internal member
-
- 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
- F02K1/15—Control or regulation
-
- 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
-
- 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
-
- 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)
- Control Of Turbines (AREA)
Description
Claims (10)
- ガスタービン航空機エンジンのノズル組立体(11)において、
ナセル(24)と;
少なくとも一部分が前記ナセルの内部に配置されたコアカウル(22)であって、前記ナセルと前記コアカウルとの間に環状ファンバイパス導管(26)が規定されるように、前記コアカウル及び前記ナセルが互いにほぼ同心に整列されるコアカウル(22)と;
互いに対向する側壁(56、58)及び前記側壁の各々にヒンジ結合された第1のフラップ(80)を具備し、前記ナセルを前記コアカウルに結合する第1の部材(50)と;
前記第1の部材に対向し、互いに対向する側壁(60、62)及び前記側壁の各々にヒンジ結合された第2のフラップ(82)を具備し、前記ナセルを前記コアカウルに結合する第2の部材(54)とを具備し、前記ファンバイパス導管のスロート面積を変化させるために、前記第1のフラップ及び前記第2のフラップは、第1の動作位置(130)と第2の動作位置(132)との間で選択的に位置決め可能であるノズル組立体(11)。 - 前記第1の部材(50)及び前記第2の部材(62)は互いに関してほぼ同一平面において整列され、前記ファンバイパス導管(26)をほぼ同一の流れ面積を有する2つの導管部分(72、74)に分割する請求項1記載のノズル組立体(11)。
- 前記第1のフラップ(80)及び前記第2のフラップ(82)の各フラップは、前記ガスタービン航空機エンジンを通る中心線(44)に関して測定された0°〜20°の角度で選択的に位置決め可能である請求項1記載のノズル組立体(11)。
- 前記第1の部材(50)の前記第1のフラップ(80)は前記第2の部材(54)の前記第2のフラップ(82)より長い請求項1記載のノズル組立体(11)。
- 前記第1の部材(50)及び前記第2の部材(52)の各々は幅を有し、前記第2の部材の幅は前記第1の部材の幅より狭い請求項1記載のノズル組立体(11)。
- 前記ノズル組立体は複数のアクチュエータ(101)を更に具備し、前記アクチュエータの各々は前記フラップ(80、82)のうち1つを前記対応する側壁(56、60)に結合する請求項1記載のノズル組立体(11)。
- 各アクチュエータ(101)は作動機構と、前記作動機構を動作させることにより、前記フラップ(80、82)が移動するように、前記作動機構をリンク(110)に接続する延長ロッド(106)とを含む請求項6記載のノズル組立体(11)。
- コアガスタービンエンジン(20)と;
ナセル(24)と;
少なくとも一部分が前記ナセルの内部に配置されたコアカウル(22)であって、前記ナセルと前記コアカウルとの間に環状ファンバイパス導管(26)が規定されるように、前記コアカウル及び前記ナセルが互いにほぼ同心に整列されるコアカウル(22)と;
互いに対向する側壁(56、58)及び前記側壁の各々にヒンジ結合された第1のフラップ(80)を具備し、前記ナセルを前記コアカウルに結合する第1の部材(50)と;
前記第1の部材に対向し、互いに対向する側壁(60、62)及び前記側壁の各々にヒンジ結合された第2のフラップ(82)を具備し、前記ナセルを前記コアカウルに結合する第2の部材(54)とを具備し、前記ファンバイパス導管のスロート面積を変化させるために、前記第1のフラップ及び前記第2のフラップは第1の動作位置(130)と第2の動作位置(132)との間で選択的に位置決め可能であるターボファンエンジン組立体(10)。 - 前記第1の部材(50)及び前記第2の部材(54)は互いに関してほぼ同一平面において整列され、前記ファンバイパス導管(26)をほぼ同一の流れ面積を有する2つの導管部分(72、74)に分割する請求項8記載のターボファンエンジン組立体(10)。
- 前記第1のフラップ(80)及び前記第2のフラップ(82)の各フラップは、前記ターボファンエンジン組立体を通る中心線(44)に関して測定された約0°〜約20°の角度で選択的に位置決め可能である請求項8記載のターボファンエンジン組立体(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/559,748 | 2006-11-14 | ||
US11/559,748 US7726116B2 (en) | 2006-11-14 | 2006-11-14 | Turbofan engine nozzle assembly and method of operating same |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008121678A JP2008121678A (ja) | 2008-05-29 |
JP4890423B2 true JP4890423B2 (ja) | 2012-03-07 |
Family
ID=38896304
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007289264A Expired - Fee Related JP4890423B2 (ja) | 2006-11-14 | 2007-11-07 | ターボファンエンジンノズル組立体及びターボファンエンジン組立体 |
Country Status (5)
Country | Link |
---|---|
US (1) | US7726116B2 (ja) |
JP (1) | JP4890423B2 (ja) |
CA (1) | CA2609294C (ja) |
FR (1) | FR2908470B1 (ja) |
GB (1) | GB2443946B (ja) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8534074B2 (en) | 2008-05-13 | 2013-09-17 | Rolls-Royce Corporation | Dual clutch arrangement and method |
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 |
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 |
US8667802B2 (en) * | 2010-05-06 | 2014-03-11 | Spirit Aerosystems, Inc. | Variable fan duct nozzle translatable core/inner cowl including two overlapping portions made of different materials |
JP5724391B2 (ja) * | 2011-01-07 | 2015-05-27 | 株式会社Ihi | エンジン排気ノズル及び航空機エンジン |
US10060390B2 (en) | 2012-02-29 | 2018-08-28 | United Technologies Corporation | Bypass duct with angled drag links |
US9309835B2 (en) | 2012-11-16 | 2016-04-12 | Woodward Hrt, Inc. | Engine and thrust reverser actuation system |
US10040560B2 (en) * | 2015-09-30 | 2018-08-07 | The Boeing Company | Trailing edge core compartment vent for an aircraft engine |
US10604255B2 (en) | 2017-06-03 | 2020-03-31 | Dennis S. Lee | Lifting system machine with methods for circulating working fluid |
CN112922744B (zh) * | 2021-03-05 | 2023-01-06 | 中国空气动力研究与发展中心空天技术研究所 | 一种壁面嵌入式的飞行器燃料输送装置 |
Family Cites Families (25)
Publication number | Priority date | Publication date | Assignee | Title |
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US3015936A (en) * | 1957-06-03 | 1962-01-09 | Curtiss Wright Corp | Thrust reversers |
US3018620A (en) * | 1959-05-22 | 1962-01-30 | United Aircraft Corp | Thrust reverser tailoring tabs |
US4043508A (en) * | 1975-12-01 | 1977-08-23 | General Electric Company | Articulated plug nozzle |
US4077206A (en) * | 1976-04-16 | 1978-03-07 | The Boeing Company | Gas turbine mixer apparatus for suppressing engine core noise and engine fan noise |
US6253540B1 (en) * | 1982-07-08 | 2001-07-03 | General Electric Company | Removable baffle infrared suppressor |
US5746047A (en) * | 1982-07-08 | 1998-05-05 | Gereral Electric Company | Infrared suppressor |
FR2676779B1 (fr) * | 1991-05-21 | 1994-06-03 | Lair Jean Pierre | Tuyere a section variable. |
US5251435A (en) * | 1991-10-30 | 1993-10-12 | General Electric Company | Reverser inner cowl with integral bifurcation walls and core cowl |
US5372006A (en) * | 1993-02-08 | 1994-12-13 | Aeronautical Concept Of Exhaust, Ltd. | Turbine engine equipped with thrust reverser |
US5655360A (en) * | 1995-05-31 | 1997-08-12 | General Electric Company | Thrust reverser with variable nozzle |
FR2736390B1 (fr) * | 1995-07-05 | 1997-08-08 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a une coquille |
FR2738597B1 (fr) * | 1995-09-13 | 1997-10-03 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a portes associees a un panneau primaire |
FR2742482B1 (fr) * | 1995-12-19 | 1998-02-06 | Hurel Dubois Avions | Inverseur de poussee a tuyere a section reglable pour moteur d'avion a reaction |
US5833140A (en) * | 1996-12-12 | 1998-11-10 | United Technologies Corporation | Variable geometry exhaust nozzle for a turbine engine |
FR2764643B1 (fr) * | 1997-06-12 | 1999-07-16 | Hispano Suiza Sa | Inverseur de poussee a portes de turboreacteur a section variable d'ejection |
US6502383B1 (en) * | 2000-08-31 | 2003-01-07 | General Electric Company | Stub airfoil exhaust nozzle |
US6938408B2 (en) * | 2001-04-26 | 2005-09-06 | Propulsion Vectoring, L.P. | Thrust vectoring and variable exhaust area for jet engine nozzle |
US6546716B2 (en) * | 2001-04-26 | 2003-04-15 | Jean-Pierre Lair | Jet engine nozzle with variable thrust vectoring and exhaust area |
BR0306781B1 (pt) * | 2002-01-09 | 2013-01-22 | bocal de exaustço de turbofan e mÉtodo para reduzir ruÍdo em um motor turbofan possuindo um bocal de exaustço de turbofan. | |
CA2486175A1 (en) * | 2002-05-21 | 2003-12-04 | The Nordam Group, Inc. | Bifurcated turbofan exhaust nozzle |
US6945031B2 (en) * | 2003-02-21 | 2005-09-20 | The Nordam Group, Inc. | Recessed engine nacelle |
US6966175B2 (en) * | 2003-05-09 | 2005-11-22 | The Nordam Group, Inc. | Rotary adjustable exhaust nozzle |
FR2866070B1 (fr) * | 2004-02-05 | 2008-12-05 | Snecma Moteurs | Turboreacteur a fort taux de dilution |
US7886518B2 (en) * | 2006-11-14 | 2011-02-15 | General Electric Company | Turbofan engine cowl assembly and method of operating the same |
US8087250B2 (en) * | 2008-06-26 | 2012-01-03 | General Electric Company | Duplex tab exhaust nozzle |
-
2006
- 2006-11-14 US US11/559,748 patent/US7726116B2/en active Active
-
2007
- 2007-10-30 FR FR0758674A patent/FR2908470B1/fr not_active Expired - Fee Related
- 2007-11-01 CA CA2609294A patent/CA2609294C/en not_active Expired - Fee Related
- 2007-11-07 JP JP2007289264A patent/JP4890423B2/ja not_active Expired - Fee Related
- 2007-11-14 GB GB0722368A patent/GB2443946B/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
GB2443946B (en) | 2011-07-20 |
GB0722368D0 (en) | 2007-12-27 |
FR2908470B1 (fr) | 2014-02-14 |
CA2609294A1 (en) | 2008-05-14 |
US20080110154A1 (en) | 2008-05-15 |
US7726116B2 (en) | 2010-06-01 |
JP2008121678A (ja) | 2008-05-29 |
GB2443946A (en) | 2008-05-21 |
CA2609294C (en) | 2015-06-16 |
FR2908470A1 (fr) | 2008-05-16 |
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