ATE358232T1 - Turbofandüse und geräuschminderungsverfahren in einer solchen düse - Google Patents

Turbofandüse und geräuschminderungsverfahren in einer solchen düse

Info

Publication number
ATE358232T1
ATE358232T1 AT03702035T AT03702035T ATE358232T1 AT E358232 T1 ATE358232 T1 AT E358232T1 AT 03702035 T AT03702035 T AT 03702035T AT 03702035 T AT03702035 T AT 03702035T AT E358232 T1 ATE358232 T1 AT E358232T1
Authority
AT
Austria
Prior art keywords
nozzle
duct
fan
noise reduction
reduction method
Prior art date
Application number
AT03702035T
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
Application granted granted Critical
Publication of ATE358232T1 publication Critical patent/ATE358232T1/de

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
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F02K1/50—Deflecting outwardly a portion of the jet by retractable scoop-like baffles
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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
    • F02K1/827—Sound absorbing structures or liners
    • 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Exhaust Gas After Treatment (AREA)
  • Nozzles (AREA)
  • Supercharger (AREA)
AT03702035T 2002-01-09 2003-01-08 Turbofandüse und geräuschminderungsverfahren in einer solchen düse ATE358232T1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US34687902P 2002-01-09 2002-01-09

Publications (1)

Publication Number Publication Date
ATE358232T1 true ATE358232T1 (de) 2007-04-15

Family

ID=23361407

Family Applications (1)

Application Number Title Priority Date Filing Date
AT03702035T ATE358232T1 (de) 2002-01-09 2003-01-08 Turbofandüse und geräuschminderungsverfahren in einer solchen düse

Country Status (7)

Country Link
US (1) US6983588B2 (de)
EP (1) EP1470328B1 (de)
AT (1) ATE358232T1 (de)
BR (1) BR0306781B1 (de)
CA (1) CA2472605C (de)
DE (1) DE60312817T2 (de)
WO (1) WO2003060312A1 (de)

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US7293401B2 (en) * 2002-03-20 2007-11-13 The Regents Of The University Of California Jet engine noise suppressor
US8997454B2 (en) * 2002-03-20 2015-04-07 The Regents Of The University Of California Turbofan engine noise suppression using fan flow deflector
GB0314123D0 (en) * 2003-06-18 2003-07-23 Rolls Royce Plc A gas turbine engine
DE102004004945A1 (de) * 2004-01-31 2005-08-18 Mtu Aero Engines Gmbh Gasturbine, insbesondere Flugtriebwerk
FR2879563B1 (fr) * 2004-12-20 2008-07-11 Airbus France Sas Agencement d'entree d'air de ventilation
US20070245708A1 (en) * 2006-04-20 2007-10-25 United Technologies Corporation High cycle fatigue management for gas turbine engines
FR2902758B1 (fr) * 2006-06-21 2009-04-10 Airbus France Sas Ensemble propulsif d'aeronef comportant un conduit d'ejection avec un bord de fuite echancre
US7721551B2 (en) * 2006-06-29 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle
GB0618072D0 (en) 2006-09-14 2006-10-25 Rolls Royce Plc Aeroengine nozzle
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
US8418471B2 (en) * 2006-10-12 2013-04-16 United Technologies Corporation Gas turbine engine having variable flow through a bifurcation having an intake with multiple louvers
US8313285B2 (en) * 2006-10-12 2012-11-20 United Technologies Corporation Variable area nozzle assisted noise control of a gas turbine engine
US8137060B2 (en) * 2006-10-12 2012-03-20 United Technologies Corporation Actuation of a turbofan engine bifurcation to change an effective nozzle exit area
WO2008045094A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Bifurcation and aft vent used to vary fan nozzle exit area
WO2008063153A2 (en) 2006-10-12 2008-05-29 United Technologies Corporation Managing low pressure turbine maximum speed in a turbofan engine
US7886518B2 (en) 2006-11-14 2011-02-15 General Electric Company Turbofan engine cowl assembly and method of 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
US8459035B2 (en) 2007-07-27 2013-06-11 United Technologies Corporation Gas turbine engine with low fan pressure ratio
US8347633B2 (en) * 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US8240120B2 (en) * 2007-10-25 2012-08-14 United Technologies Corporation Vibration management for gas turbine engines
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
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
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US7716932B2 (en) * 2008-07-24 2010-05-18 Spirit Aerosystems, Inc. Dilating fan duct nozzle
US9885313B2 (en) 2009-03-17 2018-02-06 United Technologes Corporation Gas turbine engine bifurcation located fan variable area nozzle
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.
US8549834B2 (en) * 2010-10-21 2013-10-08 United Technologies Corporation Gas turbine engine with variable area fan nozzle
US20120301273A1 (en) * 2011-05-24 2012-11-29 Justak John F Adjustable exhaust apparatus for a ram air turbine generating system
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
US9021813B2 (en) 2011-07-18 2015-05-05 The Boeing Company Cable-actuated variable area fan nozzle with elastomeric seals
FR2988439B1 (fr) * 2012-03-20 2014-11-28 Aircelle Sa Tuyere a section variable et nacelle pour turboreacteur d'aeronef equipee d'une telle tuyere
US9989009B2 (en) * 2012-10-31 2018-06-05 The Boeing Company Methods and apparatus for sealing variable area fan nozzles of jet engines
US9581145B2 (en) * 2013-05-14 2017-02-28 The Boeing Company Shape memory alloy actuation system for variable area fan nozzle
US9650991B2 (en) 2013-06-27 2017-05-16 The Boeing Company Pivoting ring petal actuation for variable area fan nozzle
US9670877B2 (en) 2013-07-15 2017-06-06 United Technologies Corporation Link arm drag reducing device
US9488130B2 (en) 2013-10-17 2016-11-08 Honeywell International Inc. Variable area fan nozzle systems with improved drive couplings
US10030608B2 (en) 2015-05-15 2018-07-24 Rohr Inc. Variable area fan nozzle actuation system
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
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FR2550821B1 (fr) * 1983-08-18 1985-11-08 Snecma Dispositif variateur du flux secondaire d'un turboreacteur multiflux
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Also Published As

Publication number Publication date
BR0306781A (pt) 2005-04-26
CA2472605A1 (en) 2003-07-24
BR0306781B1 (pt) 2013-01-22
US20050039437A1 (en) 2005-02-24
DE60312817T2 (de) 2008-01-24
EP1470328B1 (de) 2007-03-28
EP1470328A4 (de) 2005-02-09
DE60312817D1 (de) 2007-05-10
EP1470328A1 (de) 2004-10-27
US6983588B2 (en) 2006-01-10
WO2003060312A1 (en) 2003-07-24
CA2472605C (en) 2010-10-19

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Legal Events

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