JP2012052547A5 - - Google Patents
Download PDFInfo
- Publication number
- JP2012052547A5 JP2012052547A5 JP2011223001A JP2011223001A JP2012052547A5 JP 2012052547 A5 JP2012052547 A5 JP 2012052547A5 JP 2011223001 A JP2011223001 A JP 2011223001A JP 2011223001 A JP2011223001 A JP 2011223001A JP 2012052547 A5 JP2012052547 A5 JP 2012052547A5
- Authority
- JP
- Japan
- Prior art keywords
- shroud
- nozzle
- centerbody
- diameter
- rearward
- 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.)
- Granted
Links
Claims (7)
- 長手方向軸線を有するガスタービンエンジン用のノズル(30)であって、
前記長手方向軸線に沿って後方に延び、その残余部分に比較して大きい直径のスロートセクションを含むセンタボデー(32)と、
前記センタボデーを囲み、外面とその残余部分に比較して小さい直径の少なくとも中間セクションを含む内面とを有し、前記長手方向軸線に沿って前記センタボデー(32)に対して前方及び後方方向に選択的に移動可能である内側シュラウド(34)と、
前記内側シュラウド(34)を囲み、前方端部、後方端部及び該前方端部から後方端部まで延びる内面を有し、前記センタボデー(32)に対して前方及び後方方向に移動可能である外側シュラウド(36)と、
前記センタボデー(32)に対して前方及び後方方向に前記内側及び外側シュラウド(34、36)を独立して選択的に移動させるための手段と、
を含み、
前記センタボデー(32)、前記内側シュラウド(34)の内面及び前記外側シュラウド(36)の内面が、共同して該ノズル(30)を通る流体流路を形成しており、
前記外側シュラウドの(36)の内面が、前記前方及び後方端部における該内面の直径が該前方及び後方端部間の位置における該内面の直径よりもより小さくなるようなアーチ形断面輪郭を有する
ことを特徴とする、ノズル(30)。 - 前記センタボデー(32)が、前方方向に向かってより小さい直径までテーパ状になった、前記スロートセクションの前方に位置する前方セクションと、後方方向に向かってより小さい直径までテーパ状になった、前記スロートセクションの後方に位置する後方セクションとを含む、請求項1記載のノズル(30)。
- 前記外側シュラウド(36)の内面に沿ってほぼ後方向きの補助流体流を噴射するための手段をさらに含む、請求項1記載のノズル(30)。
- 前記センタボデー、内側シュラウド(34)及び外側シュラウド(36)が、エンジンの長手方向軸線周りの回転体である、請求項1記載のノズル(30)。
- 前記内側及び外側シュラウド(34、36)の少なくとも1つが、その後方端部に配置された複数の隣接するシェブロン(170、172)を含む、請求項1記載のノズル(30)。
- 前記内側及び外側シュラウド(34、36)の各々が、そのそれぞれの後方端部に配置された複数の隣接するシェブロン(170、172)を含む、請求項6記載のノズル(30)。
- 前記内側シュラウド(34)の外面が、後方部分と、前記後方部分の直径よりも大きい直径を有する前方部分と、該外面の前方及び後方部分を結合するほぼ後方向きの壁(357)とを含み、
前記外側シュラウド(36)の内面が、後方部分と、前記後方部分の直径よりも大きい直径を有する前方部分と、該内面の前方及び後方部分を結合するほぼ前方向きの壁(365)とを含み、
前記内側及び外側シュラウド(34、36)が、前記内側シュラウド(34)の外面の後方部分が前記外側シュラウド(36)の内面の後方部分と係合しかつ前記内側シュラウド(34)の外面の前方部分が前記外側シュラウド(36)の内面の前方部分と係合するように配置されている、
請求項1記載のノズル(30)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/898,035 | 2004-07-23 | ||
US10/898,035 US7174704B2 (en) | 2004-07-23 | 2004-07-23 | Split shroud exhaust nozzle |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005147696A Division JP4875854B2 (ja) | 2004-07-23 | 2005-05-20 | 分割シュラウド型排気ノズル |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2012052547A JP2012052547A (ja) | 2012-03-15 |
JP2012052547A5 true JP2012052547A5 (ja) | 2012-11-29 |
JP5325962B2 JP5325962B2 (ja) | 2013-10-23 |
Family
ID=34941361
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005147696A Expired - Fee Related JP4875854B2 (ja) | 2004-07-23 | 2005-05-20 | 分割シュラウド型排気ノズル |
JP2011223001A Expired - Fee Related JP5325962B2 (ja) | 2004-07-23 | 2011-10-07 | 分割シュラウド型排気ノズル |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005147696A Expired - Fee Related JP4875854B2 (ja) | 2004-07-23 | 2005-05-20 | 分割シュラウド型排気ノズル |
Country Status (3)
Country | Link |
---|---|
US (1) | US7174704B2 (ja) |
EP (1) | EP1619376B1 (ja) |
JP (2) | JP4875854B2 (ja) |
Families Citing this family (68)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7305817B2 (en) * | 2004-02-09 | 2007-12-11 | General Electric Company | Sinuous chevron exhaust nozzle |
US20060150612A1 (en) * | 2005-01-12 | 2006-07-13 | Honeywell International Inc. | Thrust vector control |
GB0603285D0 (en) * | 2006-02-18 | 2006-03-29 | Rolls Royce Plc | A gas turbine engine |
FR2902839B1 (fr) * | 2006-06-21 | 2011-09-30 | Aircelle Sa | Inverseur de poussee formant une tuyere adaptative |
FR2904372B1 (fr) * | 2006-07-26 | 2008-10-31 | Snecma Sa | Tuyere d'ejection des gaz pour turbomachine a double flux ayant une section d'ejection ou de col variable par deplacement du capot secondaire |
EP2054598B1 (en) * | 2006-08-01 | 2013-05-22 | Hal Gerard Wick | Aircraft engine management for fuel conservation |
US8015819B2 (en) * | 2006-09-29 | 2011-09-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Wet active chevron nozzle for controllable jet noise reduction |
EP2074316B1 (en) * | 2006-10-12 | 2020-02-12 | United Technologies Corporation | Managing low pressure turbine maximum speed in a turbofan engine |
US7770381B2 (en) | 2006-12-18 | 2010-08-10 | General Electric Company | Duct burning mixed flow turbofan and method of operation |
FR2910937B1 (fr) * | 2007-01-02 | 2009-04-03 | Airbus France Sas | Nacelle de reacteur d'aeronef et aeronef comportant une telle nacelle |
US7963099B2 (en) * | 2007-05-21 | 2011-06-21 | General Electric Company | Fluted chevron exhaust nozzle |
US7926285B2 (en) * | 2007-07-18 | 2011-04-19 | General Electric Company | Modular chevron exhaust nozzle |
US7874160B2 (en) * | 2007-08-21 | 2011-01-25 | United Technologies Corporation | Nozzle-area ratio float bias |
US8020386B2 (en) * | 2007-08-21 | 2011-09-20 | United Technologies Corporation | Rollertrack pivoting axi-nozzle |
US20090053045A1 (en) * | 2007-08-22 | 2009-02-26 | General Electric Company | Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud |
FR2923270B1 (fr) * | 2007-11-06 | 2014-01-31 | Airbus France | Turbomoteur a tuyere de flux froid adaptee |
FR2927309B1 (fr) * | 2008-02-13 | 2010-04-16 | Aircelle Sa | Systeme de commande pour nacelle de turboreacteur |
US8141366B2 (en) * | 2008-08-19 | 2012-03-27 | United Technologies Corporation | Gas turbine engine with variable area fan nozzle |
US8286416B2 (en) * | 2008-04-02 | 2012-10-16 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US8240126B2 (en) * | 2008-03-22 | 2012-08-14 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US8402744B2 (en) * | 2008-03-22 | 2013-03-26 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US8578716B2 (en) * | 2008-03-22 | 2013-11-12 | United Technologies Corporation | Valve system for a gas turbine engine |
US9267463B2 (en) * | 2008-03-25 | 2016-02-23 | United Technologies Corp. | Gas turbine engine systems involving variable nozzles with flexible panels |
FR2929655B1 (fr) * | 2008-04-02 | 2010-04-16 | Aircelle Sa | Nacelle de turboreacteur a double flux |
US8356483B2 (en) | 2008-04-10 | 2013-01-22 | United Technologies Corp | Gas turbine engine systems involving variable nozzles with sliding doors |
US20090297339A1 (en) * | 2008-05-29 | 2009-12-03 | General Electric Company | Low noise ejector for a turbomachine |
US8459036B2 (en) | 2008-12-26 | 2013-06-11 | Rolls-Royce Corporation | Aircraft nozzle having actuators capable of changing a flow area of the aircraft nozzle |
US8443586B2 (en) * | 2009-11-24 | 2013-05-21 | United Technologies Corporation | Variable area fan nozzle bearing track |
US20110120078A1 (en) * | 2009-11-24 | 2011-05-26 | Schwark Jr Fred W | Variable area fan nozzle track |
US8844262B2 (en) * | 2009-12-29 | 2014-09-30 | Rolls-Royce North American Technologies, Inc. | Exhaust for a gas turbine engine |
FR2957979B1 (fr) * | 2010-03-25 | 2012-03-30 | Aircelle Sa | Dispositif d'inversion de poussee |
US10041442B2 (en) * | 2010-06-11 | 2018-08-07 | United Technologies Corporation | Variable area fan nozzle |
FR2972224B1 (fr) * | 2011-03-04 | 2018-04-20 | Safran Aircraft Engines | Tuyere avec noyau aval presentant une forte courbure |
US8613398B2 (en) * | 2011-06-17 | 2013-12-24 | General Electric Company | Apparatus and methods for linear actuation of flow altering components of jet engine nozzle |
CN203114427U (zh) * | 2011-07-09 | 2013-08-07 | 拉姆金动力系统有限责任公司 | 燃气涡轮发动机 |
US9353704B2 (en) | 2011-08-19 | 2016-05-31 | Gulfstream Aerospace Corporation | Air inlet arrangement and method of making the same |
US9121369B2 (en) * | 2011-08-19 | 2015-09-01 | Gulfstream Aerospace Corporation | Nozzle arrangement and method of making the same |
FR2983917B1 (fr) * | 2011-12-07 | 2013-12-27 | Snecma | Tuyere convergente-divergente de turbomachine |
US9260974B2 (en) | 2011-12-16 | 2016-02-16 | General Electric Company | System and method for active clearance control |
US8869508B2 (en) * | 2012-01-31 | 2014-10-28 | United Technologies Corporation | Gas turbine engine variable area fan nozzle control |
US20140037439A1 (en) * | 2012-08-02 | 2014-02-06 | General Electric Company | Turbomachine exhaust diffuser |
FR3000994A1 (fr) * | 2013-01-16 | 2014-07-18 | Aircelle Sa | Tuyere de nacelle a dispositifs de regulation de pression |
JP6129580B2 (ja) * | 2013-02-22 | 2017-05-17 | 三菱重工業株式会社 | ガスタービン |
US9856824B2 (en) * | 2013-03-07 | 2018-01-02 | Rolls-Royce North American Technologies Inc. | Aircraft nozzle system |
WO2014197030A2 (en) * | 2013-03-12 | 2014-12-11 | United Technologies Corporation | Expanding shell flow control device |
WO2014151673A1 (en) | 2013-03-15 | 2014-09-25 | United Technologies Corporation | Aerodynamic track fairing for a gas turbine engine fan nacelle |
US10040563B1 (en) * | 2013-04-11 | 2018-08-07 | Geoffrey P. Pinto | Dual panel actuator system for jet engines |
CA2913054A1 (en) | 2013-05-31 | 2015-02-26 | General Electric Company | Dual-mode plug nozzle |
US9856956B2 (en) * | 2015-01-20 | 2018-01-02 | United Technologies Corporation | Rod-and-bracket connector system for securing a pivoting member to a guide anchor moveably secured within a guide track |
US10371089B2 (en) | 2015-01-20 | 2019-08-06 | United Technologies Corporation | System for actuating an exhaust cowl |
US10495006B2 (en) * | 2015-02-06 | 2019-12-03 | United Technologies Corporation | Variable geometry gas turbine engine for use in inclement weather |
US10443539B2 (en) | 2015-11-23 | 2019-10-15 | Rolls-Royce North American Technologies Inc. | Hybrid exhaust nozzle |
RU177799U1 (ru) * | 2016-05-13 | 2018-03-13 | Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК - УМПО") | Выходное устройство газотурбинного двигателя с раздельным истечением потоков |
CN106593696A (zh) * | 2016-12-21 | 2017-04-26 | 南京航空航天大学 | 能够改善后体流场的对称及非对称排气系统及其方法 |
DE102017104036A1 (de) | 2017-02-27 | 2018-08-30 | Rolls-Royce Deutschland Ltd & Co Kg | Konvergent-divergente Schubdüse für ein Turbofan-Triebwerk eines Überschallflugzeugs und Verfahren zur Einstellung der Düsenhalsfläche in einer Schubdüse eines Turbofan-Triebwerks |
US20210025352A1 (en) * | 2019-07-25 | 2021-01-28 | Gulfstream Aerospace Corporation | Propulsion system for an aircraft and method of manufacturing a propulsion system for an aircraft |
US11274631B2 (en) | 2020-02-27 | 2022-03-15 | Rolls-Royce North American Technologies Inc. | Methodology for minimizing aerodynamic buzz in an exhaust nozzle |
US11319832B2 (en) | 2020-02-27 | 2022-05-03 | Rolls-Royce North American Technologies Inc. | Single movement convergent and convergent-divergent nozzle |
US11274630B2 (en) * | 2020-02-27 | 2022-03-15 | Rolls-Royce North American Technologies Inc. | Exhaust nozzle with vane support structure for a gas turbine engine |
US11313320B2 (en) | 2020-02-27 | 2022-04-26 | Rolls-Royce North American Technologies Inc. | Exhaust nozzle with centerbody support structure for a gas turbine engine |
US11326551B1 (en) | 2020-02-27 | 2022-05-10 | Rolls-Royce North American Technologies Inc. | Exhaust nozzle having a compliant shell for a gas turbine engine |
US11408368B2 (en) | 2020-03-31 | 2022-08-09 | Rolls-Royce North American Technologies Inc. | Reconfigurable exhaust nozzle for a gas turbine engine |
US11286878B2 (en) | 2020-03-31 | 2022-03-29 | Rolls-Royce North American Technologies Inc. | Variable area nozzle exhaust system with integrated thrust reverser |
US11834189B2 (en) * | 2020-04-09 | 2023-12-05 | Gulfstream Aerospace Corporation | Exhaust nozzle assembly, propulsion system employing the exhaust nozzle assembly, and aircraft employing the propulsion system |
GB2595482A (en) * | 2020-05-28 | 2021-12-01 | Rolls Royce Plc | Aircraft propulsor |
EP4015796A3 (en) * | 2020-12-18 | 2022-08-17 | The Boeing Company | Systems and methods for expanding an operating speed range of a high speed flight vehicle |
US11732673B2 (en) * | 2021-07-27 | 2023-08-22 | General Electric Company | Variable area exhaust nozzle system and method for control thereof |
US20240092496A1 (en) * | 2022-09-20 | 2024-03-21 | Pratt & Whitney Canada Corp. | Exhaust nozzle assembly for an aircraft propulsion system |
Family Cites Families (41)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2683961A (en) * | 1949-05-27 | 1954-07-20 | Phillips Petroleum Co | Variable frequency pulse jet engine |
GB1008322A (en) | 1964-08-04 | 1965-10-27 | Rolls Royce | Gas turbine engine |
FR1458200A (fr) * | 1965-06-09 | 1966-03-04 | Snecma | Tuyère à corps central pour propulseur à réaction |
US3970252A (en) * | 1967-09-28 | 1976-07-20 | General Motors Corporation | Cooled exhaust duct |
US3581841A (en) * | 1970-07-27 | 1971-06-01 | Rohr Corp | Thrust reversing and noise suppressing apparatus for a jet engine |
US3779010A (en) * | 1972-08-17 | 1973-12-18 | Gen Electric | Combined thrust reversing and throat varying mechanism for a gas turbine engine |
US4039146A (en) * | 1975-12-01 | 1977-08-02 | General Electric Company | Variable cycle plug nozzle and flap and method of operating same |
US4043508A (en) * | 1975-12-01 | 1977-08-23 | General Electric Company | Articulated plug nozzle |
US4088270A (en) | 1976-03-31 | 1978-05-09 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Two dimensional wedge/translating shroud nozzle |
US4295611A (en) | 1978-12-11 | 1981-10-20 | United Technologies Corporation | Two-dimensional nozzle |
US4340178A (en) * | 1980-05-05 | 1982-07-20 | Rohr Industries, Inc. | Thrust reverser - cascade type |
US4373328A (en) * | 1980-10-22 | 1983-02-15 | United Technologies Corporation | Thrust reverser |
US4537026A (en) | 1982-04-07 | 1985-08-27 | Rolls-Royce Inc. | Variable area nozzles for turbomachines |
US4527388A (en) | 1982-07-12 | 1985-07-09 | The Garrett Corporation | Jet propulsion apparatus and methods |
US4802629A (en) | 1982-10-22 | 1989-02-07 | The Boeing Company | Plug-type exhaust nozzle having a variable centerbody and translating shroud |
US4592508A (en) | 1983-10-27 | 1986-06-03 | The Boeing Company | Translating jet engine nozzle plug |
DE4012212A1 (de) | 1990-04-14 | 1991-10-24 | Mtu Muenchen Gmbh | Duese fuer ein hyperschalltriebwerk |
US5778659A (en) | 1994-10-20 | 1998-07-14 | United Technologies Corporation | Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems |
US5694766A (en) | 1995-03-28 | 1997-12-09 | Mcdonnell Douglas Corporation | Method and apparatus for controlling the throat area, expansion ratio and thrust vector angle of an aircraft turbine engine exhaust nozzle using regions of locally separated flow |
US5706649A (en) * | 1995-04-03 | 1998-01-13 | Boeing North American, Inc. | Multi axis thrust vectoring for turbo fan engines |
US5924632A (en) | 1996-05-02 | 1999-07-20 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Jet nozzle having centerbody for enhanced exit area mixing |
US6082635A (en) | 1996-06-12 | 2000-07-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Undulated nozzle for enhanced exit area mixing |
US5806302A (en) | 1996-09-24 | 1998-09-15 | Rohr, Inc. | Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser |
JP2000018096A (ja) * | 1998-07-02 | 2000-01-18 | Ishikawajima Harima Heavy Ind Co Ltd | ジェットエンジンのテイルコーン支持装置 |
FR2788564B1 (fr) * | 1999-01-14 | 2001-02-16 | Snecma | Tuyere d'ejection de turboreacteur a reverse integree |
US6195983B1 (en) * | 1999-02-12 | 2001-03-06 | General Electric Company | Leaned and swept fan outlet guide vanes |
US6318070B1 (en) * | 2000-03-03 | 2001-11-20 | United Technologies Corporation | Variable area nozzle for gas turbine engines driven by shape memory alloy actuators |
US6442930B1 (en) * | 2000-03-31 | 2002-09-03 | General Electric Company | Combined cycle pulse detonation turbine engine |
US6666018B2 (en) * | 2000-03-31 | 2003-12-23 | General Electric Company | Combined cycle pulse detonation turbine engine |
US6502383B1 (en) * | 2000-08-31 | 2003-01-07 | General Electric Company | Stub airfoil exhaust nozzle |
GB0105349D0 (en) * | 2001-03-03 | 2001-04-18 | Rolls Royce Plc | Gas turbine engine exhaust nozzle |
US6532729B2 (en) * | 2001-05-31 | 2003-03-18 | General Electric Company | Shelf truncated chevron exhaust nozzle for reduction of exhaust noise and infrared (IR) signature |
US6868665B2 (en) * | 2001-12-21 | 2005-03-22 | General Electric Company | Methods and apparatus for operating gas turbine engines |
US6658839B2 (en) * | 2002-02-28 | 2003-12-09 | The Boeing Company | Convergent/divergent segmented exhaust nozzle |
GB0205701D0 (en) * | 2002-03-12 | 2002-04-24 | Rolls Royce Plc | Variable area nozzle |
FR2840030B1 (fr) * | 2002-05-21 | 2005-03-04 | Eads Launch Vehicles | Moteur a tuyere a noyau central pour lanceur spatial |
US7055329B2 (en) * | 2003-03-31 | 2006-06-06 | General Electric Company | Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air |
US7093442B2 (en) * | 2003-04-30 | 2006-08-22 | United Technologies Corporation | Augmentor |
US7395657B2 (en) * | 2003-10-20 | 2008-07-08 | General Electric Company | Flade gas turbine engine with fixed geometry inlet |
US6948317B2 (en) * | 2003-10-31 | 2005-09-27 | General Electric Company | Methods and apparatus for flade engine nozzle |
US7305817B2 (en) * | 2004-02-09 | 2007-12-11 | General Electric Company | Sinuous chevron exhaust nozzle |
-
2004
- 2004-07-23 US US10/898,035 patent/US7174704B2/en active Active
-
2005
- 2005-05-18 EP EP05253058.1A patent/EP1619376B1/en not_active Expired - Fee Related
- 2005-05-20 JP JP2005147696A patent/JP4875854B2/ja not_active Expired - Fee Related
-
2011
- 2011-10-07 JP JP2011223001A patent/JP5325962B2/ja not_active Expired - Fee Related
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP2012052547A5 (ja) | ||
JP2011075271A5 (ja) | ||
JP6866146B2 (ja) | 多重壁ブレードのための冷却回路 | |
JP2015063994A5 (ja) | ||
WO2015026417A3 (en) | Dual-mode plug nozzle | |
EP2631434A3 (en) | Low-ductility turbine shroud | |
JP2014092359A5 (ja) | ||
JP2014092153A5 (ja) | ||
JP2014181701A5 (ja) | ||
JP2011012682A5 (ja) | ||
JP2014509710A5 (ja) | ||
JP2011226478A5 (ja) | ||
RU2012158292A (ru) | Устройство охлаждения платформы рабочей лопатки турбины и способ создания этого устройства охлаждения | |
GB201302344D0 (en) | Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle | |
JP2014163664A5 (ja) | ||
JP2015017607A5 (ja) | ||
JP2013142324A5 (ja) | ||
JP2011045877A5 (ja) | ||
RU2010109411A (ru) | Противошумовой шеврон для сопла, а также сопло и турбовальный двигатель, оснащенные таким шевроном | |
JP2014181898A5 (ja) | ||
JP2013139770A5 (ja) | ||
DE602008002737D1 (de) | Lavaldüse eines raketenantriebs | |
CN109139301A (zh) | 一种热防护结构一体化的固体火箭发动机喷管 | |
CN108026863A (zh) | 反推装置组件 | |
CN104033284B (zh) | 一种二元喷管 |