JP4875854B2 - 分割シュラウド型排気ノズル - Google Patents
分割シュラウド型排気ノズル Download PDFInfo
- Publication number
- JP4875854B2 JP4875854B2 JP2005147696A JP2005147696A JP4875854B2 JP 4875854 B2 JP4875854 B2 JP 4875854B2 JP 2005147696 A JP2005147696 A JP 2005147696A JP 2005147696 A JP2005147696 A JP 2005147696A JP 4875854 B2 JP4875854 B2 JP 4875854B2
- Authority
- JP
- Japan
- Prior art keywords
- shroud
- nozzle
- centerbody
- outer shroud
- section
- 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
- 239000012530 fluid Substances 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 11
- 230000008859 change Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 229910001092 metal group alloy Inorganic materials 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000003870 refractory metal Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000013519 translation Methods 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
- F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
-
- 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
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/11—Two-dimensional triangular
-
- 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
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line
-
- 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)
- Control Of Turbines (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
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 Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2011223001A Division JP5325962B2 (ja) | 2004-07-23 | 2011-10-07 | 分割シュラウド型排気ノズル |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2006037949A JP2006037949A (ja) | 2006-02-09 |
| JP4875854B2 true JP4875854B2 (ja) | 2012-02-15 |
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 After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US7174704B2 (enExample) |
| EP (1) | EP1619376B1 (enExample) |
| JP (2) | JP4875854B2 (enExample) |
Families Citing this family (70)
| 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 |
| US7769503B2 (en) * | 2006-08-01 | 2010-08-03 | 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 |
| US8578716B2 (en) * | 2008-03-22 | 2013-11-12 | United Technologies Corporation | 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 |
| US8240126B2 (en) * | 2008-03-22 | 2012-08-14 | Pratt & Whitney Rocketdyne, Inc. | 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 |
| US9163521B2 (en) * | 2011-07-09 | 2015-10-20 | Dresser-Rand Company | Gas turbine engine with supersonic compressor |
| 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 |
| US10240561B2 (en) | 2013-03-15 | 2019-03-26 | 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 |
| BR112015028453A2 (pt) * | 2013-05-31 | 2017-07-25 | Gen Electric | método para controlar fluxo de fluido, bocal para motor de turbina a gás, motor e bocal de turbina a gás |
| US10371089B2 (en) | 2015-01-20 | 2019-08-06 | United Technologies Corporation | System for actuating an exhaust cowl |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| US11286878B2 (en) | 2020-03-31 | 2022-03-29 | Rolls-Royce North American Technologies Inc. | Variable area nozzle exhaust system with integrated thrust reverser |
| US11408368B2 (en) | 2020-03-31 | 2022-08-09 | Rolls-Royce North American Technologies Inc. | Reconfigurable exhaust nozzle for a gas turbine engine |
| 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 |
| US11852077B2 (en) * | 2021-04-15 | 2023-12-26 | Rtx Corporation | Regenerative cooling and adjustable throat for rotating detonation engine |
| US11732673B2 (en) * | 2021-07-27 | 2023-08-22 | General Electric Company | Variable area exhaust nozzle system and method for control thereof |
| US12018838B2 (en) * | 2022-06-21 | 2024-06-25 | General Electric Company | Cowl assembly for a gas turbine engine |
| US12103695B2 (en) * | 2022-09-20 | 2024-10-01 | Pratt & Whitney Canada Corp. | Exhaust nozzle assembly for an aircraft propulsion system |
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| 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 |
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| 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 |
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| US6442930B1 (en) * | 2000-03-31 | 2002-09-03 | General Electric Company | Combined cycle pulse detonation turbine engine |
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| 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 |
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| 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 not_active Expired - Lifetime
-
2005
- 2005-05-18 EP EP05253058.1A patent/EP1619376B1/en not_active Ceased
- 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
Also Published As
| Publication number | Publication date |
|---|---|
| JP2006037949A (ja) | 2006-02-09 |
| US7174704B2 (en) | 2007-02-13 |
| EP1619376B1 (en) | 2013-07-31 |
| EP1619376A3 (en) | 2011-12-14 |
| JP2012052547A (ja) | 2012-03-15 |
| US20060016171A1 (en) | 2006-01-26 |
| EP1619376A2 (en) | 2006-01-25 |
| JP5325962B2 (ja) | 2013-10-23 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20080516 |
|
| A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20100727 |
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| A601 | Written request for extension of time |
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