BR112015027342A2 - motor turbofan de aeronave - Google Patents
motor turbofan de aeronaveInfo
- Publication number
- BR112015027342A2 BR112015027342A2 BR112015027342A BR112015027342A BR112015027342A2 BR 112015027342 A2 BR112015027342 A2 BR 112015027342A2 BR 112015027342 A BR112015027342 A BR 112015027342A BR 112015027342 A BR112015027342 A BR 112015027342A BR 112015027342 A2 BR112015027342 A2 BR 112015027342A2
- Authority
- BR
- Brazil
- Prior art keywords
- stream
- air
- exhausted
- nozzle
- location
- Prior art date
Links
Classifications
-
- 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
- F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
-
- 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
- F02K1/1292—Varying effective area of jet pipe or nozzle by means of pivoted flaps of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure, the internal downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series and at their downstream ends on the downstream ends of the flaps of the external downstream series 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
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infra-red radiation suppressors
-
- 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
- F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
-
- 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
Abstract
resumo motor turbofan de aeronave trata-se de um duto de terceira corrente que produz uma terceira corrente de ar em pressão reduzida que é exaurida através de um bocal separado que é concêntrico com o bocal de motor principal ou primário. o ar de escape de terceira corrente do bocal concêntrico separado é exaurido para uma localização em que a pressão é ambiente ou subambiente. a localização em que o ar de terceira corrente é exaurido contribui para o impulso da aeronave. a corrente de ar do terceiro duto de ar é exaurida através de um bocal de escape do terceiro duto que é posicionado na interface entre a parte de popa da fuselagem e a borda dianteira dos flapes externos de motor. essa localização é uma região de pressão baixa que tem uma zona de recirculação. o escape de ar de terceira corrente para essa região de pressão baixa substancialmente reduz ou elimina essa zona de recirculação e o arrasto de cauda de embarcação associado, que dessa forma aprimora a eficiência do motor.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/889,003 US10400710B2 (en) | 2013-05-07 | 2013-05-07 | Secondary nozzle for jet engine |
PCT/US2014/035499 WO2015012920A2 (en) | 2013-05-07 | 2014-04-25 | Secondary nozzle for jet engine |
Publications (1)
Publication Number | Publication Date |
---|---|
BR112015027342A2 true BR112015027342A2 (pt) | 2017-09-12 |
Family
ID=51900512
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR112015027342A BR112015027342A2 (pt) | 2013-05-07 | 2014-04-25 | motor turbofan de aeronave |
Country Status (7)
Country | Link |
---|---|
US (1) | US10400710B2 (pt) |
EP (1) | EP2994633B1 (pt) |
JP (1) | JP6194413B2 (pt) |
CN (1) | CN105408611B (pt) |
BR (1) | BR112015027342A2 (pt) |
CA (1) | CA2910833C (pt) |
WO (1) | WO2015012920A2 (pt) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014160486A1 (en) * | 2013-03-13 | 2014-10-02 | Rolls-Royce North American Technologies, Inc. | Compact actuation system for a gas turbine engine exhaust nozzle |
US10364750B2 (en) | 2017-10-30 | 2019-07-30 | General Electric Company | Thermal management system |
US10941706B2 (en) | 2018-02-13 | 2021-03-09 | General Electric Company | Closed cycle heat engine for a gas turbine engine |
US11143104B2 (en) | 2018-02-20 | 2021-10-12 | General Electric Company | Thermal management system |
US11015534B2 (en) | 2018-11-28 | 2021-05-25 | General Electric Company | Thermal management system |
US11772783B2 (en) * | 2020-05-19 | 2023-10-03 | Lockheed Martin Corporation | Turbine engine secondary ejector system |
US11492918B1 (en) | 2021-09-03 | 2022-11-08 | General Electric Company | Gas turbine engine with third stream |
CN114151228B (zh) * | 2022-02-09 | 2022-04-22 | 中国航发四川燃气涡轮研究院 | 二元矢量喷管调节片离散式冷气分区的方法 |
US11834995B2 (en) | 2022-03-29 | 2023-12-05 | General Electric Company | Air-to-air heat exchanger potential in gas turbine engines |
US11834954B2 (en) | 2022-04-11 | 2023-12-05 | General Electric Company | Gas turbine engine with third stream |
US11680530B1 (en) | 2022-04-27 | 2023-06-20 | General Electric Company | Heat exchanger capacity for one or more heat exchangers associated with a power gearbox of a turbofan engine |
US11834992B2 (en) | 2022-04-27 | 2023-12-05 | General Electric Company | Heat exchanger capacity for one or more heat exchangers associated with an accessory gearbox of a turbofan engine |
Family Cites Families (57)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3296800A (en) | 1967-01-10 | Gas turbine power plant | ||
US2940252A (en) | 1956-02-07 | 1960-06-14 | Boeing Co | Gas stream thrust reaction propulsion engines with noise-suppression and thrust-reversing nozzle means |
US3210934A (en) | 1964-11-30 | 1965-10-12 | Gen Motors Corp | Jet engine exhaust |
US4026472A (en) | 1965-12-08 | 1977-05-31 | General Electric Company | Convergent-divergent plug nozzle |
US3970252A (en) | 1967-09-28 | 1976-07-20 | General Motors Corporation | Cooled exhaust duct |
US3449914A (en) | 1967-12-21 | 1969-06-17 | United Aircraft Corp | Variable flow turbofan engine |
US4004416A (en) | 1970-03-16 | 1977-01-25 | United Technologies Corporation | Infra-red suppressor for use with turbo-shaft engine |
US3990638A (en) | 1970-06-08 | 1976-11-09 | General Motors Corporation | Radiation suppression |
US3854286A (en) | 1971-11-08 | 1974-12-17 | Boeing Co | Variable bypass engines |
US3792584A (en) | 1972-02-16 | 1974-02-19 | Boeing Co | Increased or variable bypass ratio engines |
US4136518A (en) | 1972-05-03 | 1979-01-30 | Avco Corporation | Infrared radiation suppressor for a gas turbine engine |
GB1436796A (en) * | 1972-08-22 | 1976-05-26 | Mtu Muenchen Gmbh | Gas turbine ducted fan engines of multi-shaft and multi-flow construction |
US3841091A (en) | 1973-05-21 | 1974-10-15 | Gen Electric | Multi-mission tandem propulsion system |
US3879941A (en) | 1973-05-21 | 1975-04-29 | Gen Electric | Variable cycle gas turbine engine |
FR2241695B1 (pt) | 1973-08-21 | 1978-03-17 | Bertin & Cie | |
US3915413A (en) | 1974-03-25 | 1975-10-28 | Gen Electric | Variable air inlet system for a gas turbine engine |
US3981143A (en) | 1974-08-15 | 1976-09-21 | The United States Of America As Represented By The Secretary Of The Army | Infrared suppressor |
US3979065A (en) * | 1974-10-31 | 1976-09-07 | United Technologies Corporation | Cooling liner for an exhaust nozzle |
US4043121A (en) | 1975-01-02 | 1977-08-23 | General Electric Company | Two-spool variable cycle engine |
US4069661A (en) | 1975-06-02 | 1978-01-24 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Variable mixer propulsion cycle |
US4064692A (en) * | 1975-06-02 | 1977-12-27 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable cycle gas turbine engines |
US4010608A (en) | 1975-06-16 | 1977-03-08 | General Electric Company | Split fan work gas turbine engine |
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 |
US4086761A (en) | 1976-04-26 | 1978-05-02 | The Boeing Company | Stator bypass system for turbofan engine |
US4095417A (en) | 1976-08-23 | 1978-06-20 | Avco Corporation | Apparatus for and method of suppressing infrared radiation emitted from gas turbine engine |
US4066214A (en) | 1976-10-14 | 1978-01-03 | The Boeing Company | Gas turbine exhaust nozzle for controlled temperature flow across adjoining airfoils |
US4081137A (en) * | 1977-01-05 | 1978-03-28 | The United States Of America As Represented By The Secretary Of The Air Force | Finned surface cooled nozzle |
US4214441A (en) | 1978-09-12 | 1980-07-29 | The United States Of America As Represented By The Secretary Of The Navy | Infrared suppressor device |
US4290262A (en) | 1978-12-11 | 1981-09-22 | United Technologies Corporation | Two-dimensional plug nozzle |
US4791783A (en) | 1981-11-27 | 1988-12-20 | General Electric Company | Convertible aircraft engine |
US4544098A (en) * | 1982-12-27 | 1985-10-01 | United Technologies Corporation | Cooled exhaust nozzle flaps |
US5054288A (en) | 1988-10-24 | 1991-10-08 | The Boeing Company | Bypass duct for a hypersonic propulsion system |
US5074118A (en) | 1989-01-09 | 1991-12-24 | United Technologies Corporation | Air turbo-ramjet engine |
US4993663A (en) | 1989-06-01 | 1991-02-19 | General Electric Company | Hybrid laminar flow nacelle |
US5058617A (en) | 1990-07-23 | 1991-10-22 | General Electric Company | Nacelle inlet for an aircraft gas turbine engine |
US5720434A (en) * | 1991-11-05 | 1998-02-24 | General Electric Company | Cooling apparatus for aircraft gas turbine engine exhaust nozzles |
US5402963A (en) | 1992-09-15 | 1995-04-04 | General Electric Company | Acoustically shielded exhaust system for high thrust jet engines |
US5261227A (en) | 1992-11-24 | 1993-11-16 | General Electric Company | Variable specific thrust turbofan engine |
US5404713A (en) * | 1993-10-04 | 1995-04-11 | General Electric Company | Spillage drag and infrared reducing flade engine |
DK174632B1 (da) * | 1998-07-10 | 2003-07-28 | Toepholm & Westermann | Ørevoksfang til i-øret-høreapparat samt hjælpemiddel til brug ved dets isætning og udtagning |
US6502383B1 (en) * | 2000-08-31 | 2003-01-07 | General Electric Company | Stub airfoil exhaust nozzle |
SE0104346L (sv) * | 2001-12-21 | 2003-06-22 | Akzo Nobel Nv | Process för kontinuerlig kvartärnering av tertiära aminer med en alkylhalid |
US7010905B2 (en) * | 2003-02-21 | 2006-03-14 | The Nordam Group, Inc. | Ventilated confluent exhaust nozzle |
US6971229B2 (en) * | 2003-02-26 | 2005-12-06 | The Nordam Group, Inc. | Confluent exhaust nozzle |
US6966175B2 (en) * | 2003-05-09 | 2005-11-22 | The Nordam Group, Inc. | Rotary adjustable exhaust nozzle |
US7246484B2 (en) | 2003-08-25 | 2007-07-24 | General Electric Company | FLADE gas turbine engine with counter-rotatable fans |
US7134271B2 (en) * | 2004-11-05 | 2006-11-14 | General Electric Company | Thrust vectoring aft FLADE engine |
DE102005002486A1 (de) * | 2005-01-18 | 2006-07-27 | Henkel Kgaa | Tensidhaltiges Reinigungsmittel mit speziellen Proteinen |
US20070000232A1 (en) * | 2005-06-29 | 2007-01-04 | General Electric Company | Gas turbine engine and method of operating same |
US7614210B2 (en) * | 2006-02-13 | 2009-11-10 | General Electric Company | Double bypass turbofan |
US7758303B1 (en) | 2006-07-31 | 2010-07-20 | General Electric Company | FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween |
KR100871446B1 (ko) * | 2006-12-05 | 2008-12-03 | 한국전자통신연구원 | 유효 임피던스를 이용한 반사파 해석 방법 |
US7926290B2 (en) | 2006-12-18 | 2011-04-19 | General Electric Company | Turbine engine with modulated flow fan and method of operation |
US7770381B2 (en) * | 2006-12-18 | 2010-08-10 | General Electric Company | Duct burning mixed flow turbofan and method of operation |
GB0820174D0 (en) * | 2008-11-05 | 2008-12-10 | Rolls Royce Plc | A gas turbine engine variable area exhaust nozzle |
US8984891B2 (en) | 2010-12-30 | 2015-03-24 | General Electric Company | Flade discharge in 2-D exhaust nozzle |
US10001084B2 (en) * | 2011-06-14 | 2018-06-19 | Rolls-Royce North American Technologies Inc. | Aircraft powerplant with moveable nozzle member |
-
2013
- 2013-05-07 US US13/889,003 patent/US10400710B2/en active Active
-
2014
- 2014-04-25 CN CN201480026254.9A patent/CN105408611B/zh active Active
- 2014-04-25 EP EP14799060.0A patent/EP2994633B1/en active Active
- 2014-04-25 JP JP2016512929A patent/JP6194413B2/ja not_active Expired - Fee Related
- 2014-04-25 WO PCT/US2014/035499 patent/WO2015012920A2/en active Application Filing
- 2014-04-25 CA CA2910833A patent/CA2910833C/en not_active Expired - Fee Related
- 2014-04-25 BR BR112015027342A patent/BR112015027342A2/pt not_active Application Discontinuation
Also Published As
Publication number | Publication date |
---|---|
WO2015012920A2 (en) | 2015-01-29 |
CA2910833C (en) | 2018-01-09 |
US10400710B2 (en) | 2019-09-03 |
WO2015012920A3 (en) | 2015-03-26 |
EP2994633B1 (en) | 2019-06-05 |
CN105408611B (zh) | 2017-11-28 |
CA2910833A1 (en) | 2015-01-29 |
EP2994633A2 (en) | 2016-03-16 |
JP2016517928A (ja) | 2016-06-20 |
US20140345254A1 (en) | 2014-11-27 |
CN105408611A (zh) | 2016-03-16 |
JP6194413B2 (ja) | 2017-09-06 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B06F | Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette] | ||
B06U | Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette] | ||
B11B | Dismissal acc. art. 36, par 1 of ipl - no reply within 90 days to fullfil the necessary requirements | ||
B350 | Update of information on the portal [chapter 15.35 patent gazette] |