JP4981624B2 - 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
- JP4981624B2 JP4981624B2 JP2007289261A JP2007289261A JP4981624B2 JP 4981624 B2 JP4981624 B2 JP 4981624B2 JP 2007289261 A JP2007289261 A JP 2007289261A JP 2007289261 A JP2007289261 A JP 2007289261A JP 4981624 B2 JP4981624 B2 JP 4981624B2
- Authority
- JP
- Japan
- Prior art keywords
- cowl
- assembly
- nacelle
- nozzle assembly
- bypass
- 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
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
-
- 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
-
- 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
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
-
- 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
-
- 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)
Description
11 ノズル組立体
12 主翼
14 航空機で使用のパイロン
16 ファン組立体
20 コアガスタービンエンジン
21 前方カウル部分
22 コアカウル
23 分割カウル組立体又は第2のカウル部分
24 ナセル
25 内面
26 ファンノズルダクト又は環状バイパスダクト
28 周囲空気
30 入口
32 燃焼部分
34 燃焼ガス
36 コアノズル
38 バイパス空気流
40 出口
41 環状コアダクト
42 オプション中心プラグ
44 長手方向軸線/中心線
46 出口
50 第1の部材
51 端縁部
54 第2の部材
55 端縁部
56 第1の部材の側壁
57 端部部分
58 第1の部材の側壁
59 端部部分
60 第2の部材の側壁
62 第2の部材の側壁
64 アーチ形ナセル部分
66 アーチ形ナセル部分
68 アーチ形カウル部分
70 アーチ形カウル部分
72 ダクト部分
74 ダクト部分
79 バルジ部分
100 線によって定まる面
101 アクチュエータ
102 ヒンジ
104 モータ
106 伸長ロッド
108 スロット
110 リンク
130 第1の作動位置
132 第2の作動位置
200 線によって定まる面
A1 ノズル組立体の上流の第1の面積
A2 第1の面積の下流の第2の面積
A3 第2の面積の下流の第3の面積
θ 全角度
Claims (10)
- ガスタービン航空機エンジン(10)用のノズル組立体(11)であって、
ナセル(24)と、
前記ナセルと共に互いにほぼ同心に整列しかつ該ナセルとの間に環状バイパスダクト(26)を形成するように少なくとも部分的に該ナセルの内部に配置されたコアカウル(22)と、
を含み、前記コアカウルが、
前記ナセルの内部に配置された第1のカウル部分(21)と、
前記第1のカウル部分から下流方向に延びる分割カウル組立体(23)と、を含み、
前記分割カウル組立体が、その各々が前記バイパスダクトの面積を変化させるように該バイパスダクトの内部で再配置可能になった一対のアーチ形部分(68、70)を含む、
ノズル組立体(11)。 - 前記バイパスダクト(26)の内部に配置されかつ前記ナセル(24)に結合され、また対向する側壁(56、58)を含む第1の部材(50)と、
前記バイパスダクトの内部に配置されかつ前記ナセルに結合され、また前記第1の部材と向かい合って位置しかつ対向する側壁(60、62)を含む第2の部材(54)と、
をさらに含む、請求項1記載のノズル組立体(11)。 - 前記第1の部材(50)が、該第1の部材の側壁(56、58)間で測定した第1の幅を有し、前記第2の部材(54)が、該第2の部材の側壁(60、62)間で測定した第2の幅を有し、前記第2の幅が、前記第1の幅よりも狭い、請求項2記載のノズル組立体(11)。
- 前記第2の部材の側壁(60、62)が、該第2の部材(54)の後方端部を形成し、前記第2の部材の後方端部(57)が三角形状を有する、請求項2記載のノズル組立体(11)。
- 該ノズル組立体が、前記アーチ形部分(68、70)を再配置して角度θを形成するように構成される、請求項1記載のノズル組立体(11)。
- 1つのアーチ形部分(68、70)によって形成された前記角度θが、0°〜6°である、請求項5記載のノズル組立体(11)。
- 前記アーチ形部分(68、70)を再配置するように構成された複数のアクチュエータ(101)をさらに含み、前記複数のアクチュエータの各々が、前記アーチ形部分(68、70)のそれぞれの1つと前記コアカウル(22)の固定部分との間で延びる、請求項1記載のノズル組立体(11)。
- 前記複数のアクチュエータ(101)の各々が、半径方向外向き方向及び半径方向内向き方向の1つの方向に前記それぞれのアーチ形部分(68、70)を可変に位置決めするように構成された伸長ロッド(106)を含む、請求項7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、
前記ナセルと共に互いにほぼ同心に整列しかつ該ナセルとの間に環状バイパスダクト(26)を形成するように少なくとも部分的に該ナセルの内部に配置されたコアカウル(22)と、
を含み、前記コアカウルが、
前記ナセルの内部に配置された第1のカウル部分(21)と、
前記第1のカウル部分から下流方向に延びる分割カウル組立体(23)と、を含み、
前記分割カウル組立体が、その各々が前記バイパスダクトの面積を変化させるように該バイパスダクトの内部で再配置可能になった一対のアーチ形部分(68、70)を含む、
ターボファンエンジン組立体(10)。 - 前記バイパスダクト(26)の内部に配置されかつ前記ナセル(24)に結合され、また対向する側壁(56、58)を含む第1の部材(50)と、
前記バイパスダクトの内部に配置されかつ前記ナセルに結合され、また前記第1の部材と向かい合って位置しかつ対向する側壁(60、62)を含む第2の部材(54)と、
をさらに含む、請求項9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 |
---|---|---|---|
US11/559,774 US7673458B2 (en) | 2006-11-14 | 2006-11-14 | Turbofan engine nozzle assembly and method for operating the same |
US11/559,774 | 2006-11-14 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008121676A JP2008121676A (ja) | 2008-05-29 |
JP4981624B2 true JP4981624B2 (ja) | 2012-07-25 |
Family
ID=38896305
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007289261A Expired - Fee Related JP4981624B2 (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) | US7673458B2 (ja) |
JP (1) | JP4981624B2 (ja) |
CA (1) | CA2609228C (ja) |
FR (1) | FR2908466B1 (ja) |
GB (1) | GB2443947B (ja) |
Families Citing this family (16)
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 |
US10041442B2 (en) * | 2010-06-11 | 2018-08-07 | United Technologies Corporation | Variable area fan nozzle |
US9091229B2 (en) | 2011-06-14 | 2015-07-28 | Rolls-Royce North American Technologies, Inc. | Aircraft powerplant |
US9394852B2 (en) * | 2012-01-31 | 2016-07-19 | United Technologies Corporation | Variable area fan nozzle with wall thickness distribution |
JP6035946B2 (ja) * | 2012-07-26 | 2016-11-30 | 株式会社Ihi | エンジンダクト及び航空機エンジン |
US9347397B2 (en) * | 2012-08-02 | 2016-05-24 | United Technologies Corporation | Reflex annular vent nozzle |
US20140161603A1 (en) * | 2012-12-07 | 2014-06-12 | General Electric Company | Exhaust diffuser |
US20160017815A1 (en) * | 2013-03-12 | 2016-01-21 | United Technologies Corporation | Expanding shell flow control device |
US20160230675A1 (en) * | 2015-02-09 | 2016-08-11 | United Technologies Corporation | Fan flow control valve |
US10197007B2 (en) | 2016-01-14 | 2019-02-05 | General Electric Company | Method and system for controlling core cowl vent area |
GB201810887D0 (en) * | 2018-07-03 | 2018-08-15 | Rolls Royce Plc | Gas turbine engine fan arrangement |
Family Cites Families (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
GB1244292A (en) * | 1970-01-14 | 1971-08-25 | Rolls Royce | Gas turbine engine |
US3756026A (en) * | 1971-04-23 | 1973-09-04 | Rohr Corp | Propulsion flow modulating system |
US4050242A (en) * | 1975-12-01 | 1977-09-27 | General Electric Company | Multiple bypass-duct turbofan with annular flow plug nozzle and method of operating same |
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 |
GB2198999B (en) * | 1986-12-17 | 1990-08-29 | Rolls Royce Plc | Fluid propulsion engine with flow exit control device |
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 |
WO1996012881A1 (en) * | 1994-10-20 | 1996-05-02 | United Technologies Corporation | Variable area fan exhaust 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 |
JPH11159399A (ja) * | 1997-11-26 | 1999-06-15 | Tech Res & Dev Inst Of Japan Def Agency | 高バイパス比ターボファンエンジン |
US6546716B2 (en) | 2001-04-26 | 2003-04-15 | Jean-Pierre Lair | Jet engine nozzle with variable thrust vectoring and exhaust area |
US6938408B2 (en) | 2001-04-26 | 2005-09-06 | Propulsion Vectoring, L.P. | Thrust vectoring and variable exhaust area for jet engine nozzle |
BR0311164A (pt) | 2002-05-21 | 2005-08-16 | Nordam Group Inc | Bocal com turbo-ventilador bifurcado |
US6945031B2 (en) * | 2003-02-21 | 2005-09-20 | The Nordam Group, Inc. | Recessed engine nacelle |
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 |
-
2006
- 2006-11-14 US US11/559,774 patent/US7673458B2/en active Active
-
2007
- 2007-10-23 FR FR0758515A patent/FR2908466B1/fr active Active
- 2007-11-01 CA CA2609228A patent/CA2609228C/en not_active Expired - Fee Related
- 2007-11-07 JP JP2007289261A patent/JP4981624B2/ja not_active Expired - Fee Related
- 2007-11-14 GB GB0722369A patent/GB2443947B/en active Active
Also Published As
Publication number | Publication date |
---|---|
US20080110152A1 (en) | 2008-05-15 |
FR2908466B1 (fr) | 2016-09-30 |
US7673458B2 (en) | 2010-03-09 |
JP2008121676A (ja) | 2008-05-29 |
CA2609228C (en) | 2014-12-30 |
FR2908466A1 (fr) | 2008-05-16 |
GB2443947B (en) | 2011-09-07 |
GB0722369D0 (en) | 2007-12-27 |
CA2609228A1 (en) | 2008-05-14 |
GB2443947A (en) | 2008-05-21 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4981624B2 (ja) | 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 | |
US11391240B2 (en) | Gas turbine engine bifurcation located fan variable area nozzle | |
US11396847B2 (en) | Flutter sensing and control system for a gas turbine engine | |
US7726116B2 (en) | Turbofan engine nozzle assembly and method of operating same | |
US8418471B2 (en) | Gas turbine engine having variable flow through a bifurcation having an intake with multiple louvers | |
US3879941A (en) | Variable cycle gas turbine engine | |
EP2157305B1 (en) | Gas turbine engine with variable area fan nozzle | |
US8662417B2 (en) | Gas turbine engine fan variable area nozzle with swivable insert system | |
EP2069630B1 (en) | Nacelle assembly and corresponding method | |
CA2853694C (en) | Gas turbine engine with geared architecture | |
US10550704B2 (en) | High performance convergent divergent nozzle | |
US20200182193A1 (en) | Method and system for a stowable bell-mouth scoop | |
EP2809936B1 (en) | Gas turbine engine with improved fuel efficiency |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20101101 |
|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20101101 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20111110 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20111115 |
|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20120215 |
|
TRDD | Decision of grant or rejection written | ||
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20120403 |
|
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20120420 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20150427 Year of fee payment: 3 |
|
R150 | Certificate of patent or registration of utility model |
Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
LAPS | Cancellation because of no payment of annual fees |