BR0306780A - Tubo de descarga de suspiro com área variável - Google Patents

Tubo de descarga de suspiro com área variável

Info

Publication number
BR0306780A
BR0306780A BR0306780-7A BR0306780A BR0306780A BR 0306780 A BR0306780 A BR 0306780A BR 0306780 A BR0306780 A BR 0306780A BR 0306780 A BR0306780 A BR 0306780A
Authority
BR
Brazil
Prior art keywords
vent
flap
exhaust flow
preset
variable
Prior art date
Application number
BR0306780-7A
Other languages
English (en)
Inventor
Jean-Pierre Lair
Original Assignee
Nordam Group Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Nordam Group Inc filed Critical Nordam Group Inc
Publication of BR0306780A publication Critical patent/BR0306780A/pt

Links

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
    • F02K1/78—Other construction of jet pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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
    • F02K1/40—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
    • 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
    • F02K1/80—Couplings or connections
    • F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Supercharger (AREA)
  • Exhaust Silencers (AREA)

Abstract

"TUBO DE DESCARGA DE SUSPIRO COM áREA VARIáVEL". Trata-se de um suspiro central (36) que é configurado para uso variável em um tubo de descarga de exaustão (34) . Uma parte à frente do suspiro (36) inclui uma admissão (56) possuindo uma aba de fechamento (58) na mesma e uma parte atrás do suspiro inclui uma saída (60). A aba (58) é seletivamente aberta durante a operação de decolagem da aeronave e até uma altitude de subida preestabelecida para desviar uma parte do fluxo de exaustão principal através do suspiro, com a aba sendo fechada a partir da altitude preestabelecida e da operação de cruzeiro. A abertura da aba (58) de forma correspondente aumenta a área de fluxo disponível para descarga do fluxo de exaustão para reduzir a velocidade do mesmo e atenuar o ruído.
BR0306780-7A 2002-01-09 2003-01-08 Tubo de descarga de suspiro com área variável BR0306780A (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US34694902P 2002-01-09 2002-01-09
PCT/US2003/000462 WO2003060311A1 (en) 2002-01-09 2003-01-08 Variable area plug nozzle

Publications (1)

Publication Number Publication Date
BR0306780A true BR0306780A (pt) 2004-12-28

Family

ID=23361698

Family Applications (1)

Application Number Title Priority Date Filing Date
BR0306780-7A BR0306780A (pt) 2002-01-09 2003-01-08 Tubo de descarga de suspiro com área variável

Country Status (5)

Country Link
US (1) US6845607B2 (pt)
EP (1) EP1470327A4 (pt)
BR (1) BR0306780A (pt)
CA (1) CA2472604A1 (pt)
WO (1) WO2003060311A1 (pt)

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DE10145489B4 (de) * 2001-09-14 2008-11-06 Mtu Aero Engines Gmbh Anordnung zum Vermischen von zwei ursprünglich getrennt geführten Fluidströmen in einem Zweikreis-Strahltriebwerk
US7849695B1 (en) * 2001-09-17 2010-12-14 Alliant Techsystems Inc. Rocket thruster comprising load-balanced pintle valve
GB0205701D0 (en) * 2002-03-12 2002-04-24 Rolls Royce Plc Variable area nozzle
US7264203B2 (en) * 2003-10-02 2007-09-04 The Nordam Group, Inc. Spider actuated thrust reverser
US20060288688A1 (en) * 2005-06-22 2006-12-28 Jean-Pierre Lair Turbofan core thrust spoiler
US7823376B2 (en) * 2005-09-13 2010-11-02 Aerojet-General Corporation Thrust augmentation in plug nozzles and expansion-deflection nozzles
FR2892152B1 (fr) * 2005-10-19 2007-11-23 Airbus France Sas Turbomoteur a bruit de jet attenue
US20070163227A1 (en) * 2006-01-17 2007-07-19 Aerojet-General Corporation Nozzles with rotatable sections for variable thrust
FR2898940B1 (fr) * 2006-03-24 2008-05-30 Snecma Sa Corps central de tuyere de turboreacteur
US7784283B2 (en) * 2006-05-03 2010-08-31 Rohr, Inc. Sound-absorbing exhaust nozzle center plug
FR2901578B1 (fr) * 2006-05-23 2008-07-25 Snecma Sa Corps central pour canal d'echappement d'un turboreacteur, turboreacteur
US7805925B2 (en) * 2006-08-18 2010-10-05 Pratt & Whitney Canada Corp. Gas turbine engine exhaust duct ventilation
US7509796B2 (en) * 2006-09-13 2009-03-31 Aerojet-General Corporation Pintle-controlled propulsion system with external dynamic seal
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
US8286415B2 (en) * 2006-10-12 2012-10-16 United Technologies Corporation Turbofan engine having inner fixed structure including ducted passages
DE102006051308A1 (de) * 2006-10-31 2008-05-08 Bayer Materialscience Ag Verfahren zur Behandlung von Metalloberflächen
US8371806B2 (en) * 2007-10-03 2013-02-12 United Technologies Corporation Gas turbine engine having core auxiliary duct passage
FR2921977B1 (fr) * 2007-10-08 2012-09-21 Airbus France Turbomoteur a double flux pour aeronef
US7735778B2 (en) * 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8051639B2 (en) * 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
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
FR2929998B1 (fr) * 2008-04-14 2011-08-12 Aircelle Sa Nacelle de turboreacteur a double flux
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8025122B2 (en) * 2008-11-06 2011-09-27 The Boeing Company Acoustically treated exhaust centerbody for jet engines and associated methods
US20110004388A1 (en) * 2009-07-01 2011-01-06 United Technologies Corporation Turbofan temperature control with variable area nozzle
FR2949820B1 (fr) * 2009-09-04 2011-10-14 Aircelle Sa Ensemble structurant pour une tuyere d'ejection.
DE102010026834A1 (de) * 2010-07-12 2012-01-12 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenabgaskonus
US8857761B2 (en) 2010-10-27 2014-10-14 Ata Engineering, Inc. Variable geometry aircraft pylon structure and related operation techniques
US8443931B2 (en) 2011-04-06 2013-05-21 Lockheed Martin Corporation Noise reduction of supersonic jet engines
US9567867B2 (en) 2011-09-14 2017-02-14 Ata Engineering, Inc. Methods and apparatus for deployable swirl vanes
GB201412379D0 (en) 2014-07-11 2014-08-27 Rolls Royce Plc Ventilation inlet
CN106704028A (zh) * 2017-01-19 2017-05-24 中国航发沈阳发动机研究所 一种轴对称塞式矢量喷管
GB201704841D0 (en) * 2017-03-27 2017-05-10 Rolls Royce Plc Gas Turbine Engine
US10570852B2 (en) * 2017-09-21 2020-02-25 United Technologies Corporation Moveable exhaust plug liner
GB201806614D0 (en) * 2018-04-24 2018-06-06 Rolls Royce Plc Gas turbine engine
GB201808852D0 (en) * 2018-05-31 2018-07-18 Rolls Royce Plc Gas turbine engine
GB201819748D0 (en) * 2018-10-12 2019-01-16 Rolls Royce Plc Afterburner system
FR3107318B1 (fr) * 2020-02-17 2022-01-14 Safran Aircraft Engines Turbomachine d’aéronef à double flux équipée d’un dispositif d’arrêt en survitesse du rotor
US11560847B2 (en) 2020-04-07 2023-01-24 Rohr, Inc. Transpirationally cooled exhaust center body for an aircraft propulsion system
CN114673605B (zh) * 2022-04-14 2023-10-10 中国航发沈阳发动机研究所 一种轻质高隐身能力单边膨胀喷管
US12163472B2 (en) 2022-09-02 2024-12-10 Rohr, Inc. Engine exhaust nozzle with acoustic attenuation
US12110839B1 (en) * 2023-12-22 2024-10-08 Rtx Corporation Variable area nozzle assembly for an aircraft propulsion system

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US2952124A (en) * 1957-07-29 1960-09-13 Boeing Co Plug type noise suppressor and thrust reverser
US3084507A (en) 1958-06-17 1963-04-09 Douglas Aircraft Co Inc Jet engine sound suppressor and reverser
US3390837A (en) 1965-12-08 1968-07-02 Gen Electric Convergent-divergent plug nozzle having a plurality of freely-floating tandem flaps
US3780827A (en) * 1972-12-19 1973-12-25 Nasa Gas turbine exhaust nozzle
US3829020A (en) 1973-06-13 1974-08-13 Boeing Co Translating sleeve variable area nozzle and thrust reverser
FR2241695B1 (pt) * 1973-08-21 1978-03-17 Bertin & Cie
US3889882A (en) * 1974-03-25 1975-06-17 Gen Electric Retractable sound suppressor 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
US3990530A (en) * 1975-05-19 1976-11-09 United Technologies Corporation Noise suppressor for turbine type power plant
US4258822A (en) * 1979-07-27 1981-03-31 United Technologies Corporation Muffler plug for gas turbine power plant
US4271666A (en) * 1979-08-20 1981-06-09 Avco Corporation Integral infrared radiation suppressor for a turbofan engine
WO1983003281A1 (en) * 1982-03-17 1983-09-29 Klees, Garry, William Internally ventilated noise suppressor with large plug nozzle
US4537026A (en) * 1982-04-07 1985-08-27 Rolls-Royce Inc. Variable area nozzles for turbomachines
US5184459A (en) * 1990-05-29 1993-02-09 The United States Of America As Represented By The Secretary Of The Air Force Variable vane valve in a gas turbine
GB2308866B (en) * 1996-01-04 1999-09-08 Rolls Royce Plc Ducted fan gas turbine engine with secondary duct

Also Published As

Publication number Publication date
US6845607B2 (en) 2005-01-25
EP1470327A1 (en) 2004-10-27
WO2003060311A1 (en) 2003-07-24
EP1470327A4 (en) 2010-07-21
US20030150214A1 (en) 2003-08-14
CA2472604A1 (en) 2003-07-24

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Legal Events

Date Code Title Description
B06A Notification to applicant to reply to the report for non-patentability or inadequacy of the application [chapter 6.1 patent gazette]
B08F Application fees: application dismissed [chapter 8.6 patent gazette]

Free format text: REFERENTE A 8A ANUIDADE(S).

B11B Dismissal acc. art. 36, par 1 of ipl - no reply within 90 days to fullfil the necessary requirements