ATE193353T1 - Satz für bläsertriebwerkslärmdampfung - Google Patents

Satz für bläsertriebwerkslärmdampfung

Info

Publication number
ATE193353T1
ATE193353T1 AT96650036T AT96650036T ATE193353T1 AT E193353 T1 ATE193353 T1 AT E193353T1 AT 96650036 T AT96650036 T AT 96650036T AT 96650036 T AT96650036 T AT 96650036T AT E193353 T1 ATE193353 T1 AT E193353T1
Authority
AT
Austria
Prior art keywords
fan
core engine
exhaust gas
flow
common nozzle
Prior art date
Application number
AT96650036T
Other languages
English (en)
Inventor
Kenneth R Mcguire
Edward J Phillips
Robert W Lillibridge
Eugene James Matthews
Original Assignee
Burbank Aeronautical Corp Ii
Kenneth R Mcguire
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
Priority claimed from US08/521,139 external-priority patent/US5706651A/en
Priority claimed from US08/584,342 external-priority patent/US5791138A/en
Application filed by Burbank Aeronautical Corp Ii, Kenneth R Mcguire filed Critical Burbank Aeronautical Corp Ii
Application granted granted Critical
Publication of ATE193353T1 publication Critical patent/ATE193353T1/de

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
    • F02K3/06—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
    • 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
    • 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
    • F02C7/24—Heat or noise insulation
    • 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
    • F02K1/46—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
    • F02K1/48—Corrugated nozzles
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
    • 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
    • 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)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Supercharger (AREA)
AT96650036T 1995-08-29 1996-08-27 Satz für bläsertriebwerkslärmdampfung ATE193353T1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/521,139 US5706651A (en) 1995-08-29 1995-08-29 Turbofan engine with reduced noise
US08/584,342 US5791138A (en) 1996-01-11 1996-01-11 Turbofan engine with reduced noise

Publications (1)

Publication Number Publication Date
ATE193353T1 true ATE193353T1 (de) 2000-06-15

Family

ID=27060383

Family Applications (1)

Application Number Title Priority Date Filing Date
AT96650036T ATE193353T1 (de) 1995-08-29 1996-08-27 Satz für bläsertriebwerkslärmdampfung

Country Status (5)

Country Link
EP (1) EP0761947B1 (de)
AT (1) ATE193353T1 (de)
CA (1) CA2181963A1 (de)
DE (1) DE69608513D1 (de)
IL (1) IL119150A0 (de)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2764644B1 (fr) * 1997-06-12 1999-07-16 Hispano Suiza Sa Turboreacteur a double flux associe a un inverseur de poussee avec un carenage rapporte dans la veine fluide
FR2788564B1 (fr) * 1999-01-14 2001-02-16 Snecma Tuyere d'ejection de turboreacteur a reverse integree
US20070130913A1 (en) * 2003-11-18 2007-06-14 Howard Harrison Coaxial propulsion systems with flow modification element
FR2961857B1 (fr) * 2010-06-28 2012-07-27 Snecma Tube d'alimentation en air de refroidissement d'une turbine d'un turbomoteur, et turbomoteur equipe d'un tel tube
US9617009B2 (en) 2013-02-22 2017-04-11 United Technologies Corporation ATR full ring sliding nacelle
US9670876B2 (en) 2013-02-22 2017-06-06 United Technologies Corporation Tandem thrust reverser with sliding rails
US10197010B2 (en) 2013-08-12 2019-02-05 The Boeing Company Long-duct, mixed-flow nozzle system for a turbofan engine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3696617A (en) * 1969-11-10 1972-10-10 Rohr Corp Turbo-fan propulsion apparatus and operating method
US4292803A (en) * 1979-01-19 1981-10-06 Rohr Industries, Inc. Turbo fan engine mixer
US4817756A (en) * 1985-08-26 1989-04-04 Aeronautic Development Corp. Ltd. Quiet nacelle system and hush kit
EP0412127B1 (de) * 1989-02-27 1994-06-15 United Technologies Methode und system zur regelung eines kompressors mit variabler geometrie
US5127602B1 (en) * 1989-11-21 1995-05-02 Federal Express Corp Noise reduction kit for jet turbine engines.
GB9014381D0 (en) * 1990-06-28 1990-08-22 Short Brothers Plc A composite structural component
US5169288A (en) * 1991-09-06 1992-12-08 General Electric Company Low noise fan assembly
US5372006A (en) * 1993-02-08 1994-12-13 Aeronautical Concept Of Exhaust, Ltd. Turbine engine equipped with thrust reverser

Also Published As

Publication number Publication date
EP0761947B1 (de) 2000-05-24
EP0761947A1 (de) 1997-03-12
DE69608513D1 (de) 2000-06-29
IL119150A0 (en) 1996-11-14
CA2181963A1 (en) 1997-03-01

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Legal Events

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