BR0311164A - Bocal com turbo-ventilador bifurcado - Google Patents
Bocal com turbo-ventilador bifurcadoInfo
- Publication number
- BR0311164A BR0311164A BR0311164-4A BR0311164A BR0311164A BR 0311164 A BR0311164 A BR 0311164A BR 0311164 A BR0311164 A BR 0311164A BR 0311164 A BR0311164 A BR 0311164A
- Authority
- BR
- Brazil
- Prior art keywords
- fan
- duct
- nozzle
- turbocharged
- fork
- Prior art date
Links
- 238000005192 partition Methods 0.000 abstract 2
- 210000002445 nipple Anatomy 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
-
- 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
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed 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
- F02K1/38—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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
-
- 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
- F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
- F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position
-
- 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
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/327—Application in turbines in gas turbines to drive shrouded, high solidity propeller
-
- 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
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
"BOCAL COM TURBO-VENTILADOR BIFURCADO". Um bocal de escapamento com turbo-ventilador (28) inclui um conduto de ventilador (40) definido entre uma nacela de ventilador (23) e uma capota de motor de núcleo (30). O conduto de ventilador (40) inclui uma parede de extremidade longitudinal (48) e uma partição afastada dela de modo a se definir um conduto de fluxo secundário (52). O conduto de ventilador (40) inclui também uma saída primária (42), e o conduto secundário (52) inclui uma saída secundária (54). A partição (50) entre os dois condutos inclui uma abertura (56) coberta por um flape seletivamente móvel (58).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US38239702P | 2002-05-21 | 2002-05-21 | |
PCT/US2003/015644 WO2003099654A2 (en) | 2002-05-21 | 2003-05-19 | Bifurcated turbofan exhaust nozzle |
Publications (1)
Publication Number | Publication Date |
---|---|
BR0311164A true BR0311164A (pt) | 2005-08-16 |
Family
ID=29584407
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR0311164-4A BR0311164A (pt) | 2002-05-21 | 2003-05-19 | Bocal com turbo-ventilador bifurcado |
Country Status (5)
Country | Link |
---|---|
US (1) | US6820410B2 (pt) |
EP (1) | EP1509447A4 (pt) |
BR (1) | BR0311164A (pt) |
CA (1) | CA2486175A1 (pt) |
WO (1) | WO2003099654A2 (pt) |
Families Citing this family (50)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8997454B2 (en) * | 2002-03-20 | 2015-04-07 | The Regents Of The University Of California | Turbofan engine noise suppression using fan flow deflector |
US7802752B2 (en) * | 2002-03-20 | 2010-09-28 | The Regents Of The University Of California | Jet engine noise suppressor |
GB0505184D0 (en) * | 2005-03-14 | 2005-04-20 | Rolls Royce Plc | Thrust reverser mounting structure |
US20110101158A1 (en) * | 2005-03-29 | 2011-05-05 | The Boeing Company | Thrust Reversers Including Monolithic Components |
US7721551B2 (en) * | 2006-06-29 | 2010-05-25 | United Technologies Corporation | Fan variable area nozzle for a gas turbine engine fan nacelle |
FR2905734B1 (fr) * | 2006-09-07 | 2012-07-13 | Airbus France | Dispositif permettant d'ameliorer l'efficacite des traitements acoustiques dans un conduit d'une motorisation d'aeronef |
US8015797B2 (en) | 2006-09-21 | 2011-09-13 | Jean-Pierre Lair | Thrust reverser nozzle for a turbofan gas turbine engine |
EP2074313B1 (en) * | 2006-10-12 | 2014-07-09 | United Technologies Corporation | Fan variable area nozzle with electromechanical actuator |
EP2074298B1 (en) | 2006-10-12 | 2013-03-13 | United Technologies Corporation | Variable area nozzle assisted gas turbine engine restarting |
EP2069629B1 (en) * | 2006-10-12 | 2014-09-24 | United Technologies Corporation | Gas turbine engine fan variable area nozzle with swivalable insert system |
WO2008045093A1 (en) * | 2006-10-12 | 2008-04-17 | United Technologies Corporation | Gas turbine engine bifurcation located in a fan variable area nozzle |
US8650854B2 (en) * | 2006-10-12 | 2014-02-18 | United Technologies Corporation | Bifurcation and aft vent used to vary fan nozzle exit area |
EP2074311B1 (en) * | 2006-10-12 | 2013-09-11 | United Technologies Corporation | Nacelle assembly for a high-bypass gas turbine engine, corresponding high-bypass gas turbine engine and method of varying a fan nozzle exit area |
WO2008045053A2 (en) * | 2006-10-12 | 2008-04-17 | United Technologies Corporation | Actuation of a turbofan engine bifurcation to change an effective nozzle exit area |
US7673458B2 (en) * | 2006-11-14 | 2010-03-09 | General Electric Company | Turbofan engine nozzle assembly and method for operating the same |
US7726116B2 (en) * | 2006-11-14 | 2010-06-01 | General Electric Company | Turbofan engine nozzle assembly and method of operating same |
GB0700238D0 (en) | 2007-01-06 | 2007-02-14 | Rolls Royce Plc | Nozzle arrangement |
US20080273961A1 (en) | 2007-03-05 | 2008-11-06 | Rosenkrans William E | Flutter sensing and control system for a gas turbine engine |
US7966827B2 (en) * | 2007-05-31 | 2011-06-28 | United Technologies Corporation | Gas turbine engine with fan variable area nozzle having a rotational valve system |
FR2920197B1 (fr) * | 2007-08-20 | 2013-08-09 | Aircelle Sa | Ressort pour volet d'inverseur de poussee a grilles pour turboreacteur d'aeronef |
US8052085B2 (en) | 2007-11-16 | 2011-11-08 | The Nordam Group, Inc. | Thrust reverser for a turbofan gas turbine engine |
US7735778B2 (en) * | 2007-11-16 | 2010-06-15 | Pratt & Whitney Canada Corp. | Pivoting fairings for a thrust reverser |
US8091827B2 (en) | 2007-11-16 | 2012-01-10 | The Nordam Group, Inc. | Thrust reverser door |
US8172175B2 (en) | 2007-11-16 | 2012-05-08 | The Nordam Group, Inc. | Pivoting door thrust reverser for a turbofan gas turbine engine |
US8052086B2 (en) | 2007-11-16 | 2011-11-08 | The Nordam Group, Inc. | Thrust reverser door |
US8051639B2 (en) | 2007-11-16 | 2011-11-08 | The Nordam Group, Inc. | Thrust reverser |
US8127530B2 (en) | 2008-06-19 | 2012-03-06 | The Nordam Group, Inc. | Thrust reverser for a turbofan gas turbine engine |
US9181899B2 (en) * | 2008-08-27 | 2015-11-10 | General Electric Company | Variable slope exhaust nozzle |
US9885313B2 (en) | 2009-03-17 | 2018-02-06 | United Technologes Corporation | Gas turbine engine bifurcation located fan variable area nozzle |
US8844262B2 (en) * | 2009-12-29 | 2014-09-30 | Rolls-Royce North American Technologies, Inc. | Exhaust for a gas turbine engine |
GB201007215D0 (en) | 2010-04-30 | 2010-06-16 | Rolls Royce Plc | Gas turbine engine |
US8876043B2 (en) * | 2010-08-20 | 2014-11-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Aircraft engine exhaust nozzle system for jet noise reduction |
US8651429B2 (en) | 2010-08-20 | 2014-02-18 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Blended cutout flap for reduction of jet-flap interaction noise |
US9022311B2 (en) | 2010-08-20 | 2015-05-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Active aircraft pylon noise control system |
US8549834B2 (en) | 2010-10-21 | 2013-10-08 | United Technologies Corporation | Gas turbine engine with variable area fan nozzle |
FR2975971B1 (fr) * | 2011-06-01 | 2013-05-17 | Aircelle Sa | Nacelle pour un turboreacteur double flux d'un aeronef |
US9249731B2 (en) | 2012-06-05 | 2016-02-02 | United Technologies Corporation | Nacelle bifurcation for gas turbine engine |
GB201220378D0 (en) * | 2012-11-13 | 2012-12-26 | Rolls Royce Plc | A gas turbine engine exhaust nozzle |
JP6317946B2 (ja) * | 2014-02-18 | 2018-04-25 | 三菱航空機株式会社 | 航空機 |
US10030608B2 (en) | 2015-05-15 | 2018-07-24 | Rohr Inc. | Variable area fan nozzle actuation system |
US9810178B2 (en) | 2015-08-05 | 2017-11-07 | General Electric Company | Exhaust nozzle with non-coplanar and/or non-axisymmetric shape |
US10040560B2 (en) * | 2015-09-30 | 2018-08-07 | The Boeing Company | Trailing edge core compartment vent for an aircraft engine |
US9863368B1 (en) * | 2016-09-09 | 2018-01-09 | Florida Turbine Technologies, Inc. | Aircraft with gas turbine engine having outer bypass elements removed |
PL419827A1 (pl) * | 2016-12-16 | 2018-06-18 | General Electric Company | Rozpórki do ram wylotowych systemów turbin |
ES2758083T3 (es) * | 2017-07-14 | 2020-05-04 | Airbus Operations Sl | Aeronave que incorpora un sistema de recuperación de empuje utilizando aire de la cabina |
FR3074227B1 (fr) * | 2017-11-28 | 2020-02-28 | Airbus Operations | Structure interne d'un conduit d'ejection primaire |
CN111219265A (zh) * | 2020-02-14 | 2020-06-02 | 中国航发沈阳发动机研究所 | 变循环发动机模式控制机构及具有其的中介机匣结构 |
CN111207005A (zh) * | 2020-02-14 | 2020-05-29 | 中国航发沈阳发动机研究所 | 一种变循环发动机模式控制机构及具有其的中介机匣结构 |
CN112412655A (zh) * | 2020-11-05 | 2021-02-26 | 中国航发四川燃气涡轮研究院 | 一种多流道小偏心短距s弯喷管结构 |
CN114878175B (zh) * | 2022-04-15 | 2024-02-23 | 中国航发沈阳发动机研究所 | 一种内外涵分流排气***的外涵面积同步调节机构 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3137131A (en) * | 1961-09-18 | 1964-06-16 | United Aircraft Corp | Noise suppression of fan engines |
US3892358A (en) | 1971-03-17 | 1975-07-01 | Gen Electric | Nozzle seal |
US4278220A (en) | 1979-03-30 | 1981-07-14 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Thrust reverser for a long duct fan engine |
US4420932A (en) * | 1982-03-02 | 1983-12-20 | The United States Of America As Represented By The Secretary Of The Air Force | Pressure control system for convergent-divergent exhaust nozzle |
US5251435A (en) * | 1991-10-30 | 1993-10-12 | General Electric Company | Reverser inner cowl with integral bifurcation walls and core cowl |
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 |
US6751944B2 (en) * | 2001-10-23 | 2004-06-22 | The Nordam Group, Inc. | Confluent variable exhaust nozzle |
US6705547B2 (en) * | 2002-02-01 | 2004-03-16 | Luis Manuel Braga Da Costa Campos | Active noise reducing nozzle |
-
2003
- 2003-05-19 US US10/440,933 patent/US6820410B2/en not_active Expired - Lifetime
- 2003-05-19 WO PCT/US2003/015644 patent/WO2003099654A2/en not_active Application Discontinuation
- 2003-05-19 CA CA002486175A patent/CA2486175A1/en not_active Abandoned
- 2003-05-19 BR BR0311164-4A patent/BR0311164A/pt not_active IP Right Cessation
- 2003-05-19 EP EP03755373A patent/EP1509447A4/en not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
US20040187476A1 (en) | 2004-09-30 |
WO2003099654A3 (en) | 2004-08-05 |
WO2003099654A2 (en) | 2003-12-04 |
US6820410B2 (en) | 2004-11-23 |
EP1509447A2 (en) | 2005-03-02 |
EP1509447A4 (en) | 2010-07-21 |
CA2486175A1 (en) | 2003-12-04 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B08F | Application fees: application dismissed [chapter 8.6 patent gazette] |
Free format text: REFERENTE 6A. E 8A, ANUIDADE(S). |
|
B08K | Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette] |
Free format text: NAO APRESENTADA A GUIA DE CUMPRIMENTO DE EXIGENCIA. REFERENTE AS 8A E 9A ANUIDADES. |