DE60125279D1 - Strahlmischer für Strahltriebwerke - Google Patents

Strahlmischer für Strahltriebwerke

Info

Publication number
DE60125279D1
DE60125279D1 DE60125279T DE60125279T DE60125279D1 DE 60125279 D1 DE60125279 D1 DE 60125279D1 DE 60125279 T DE60125279 T DE 60125279T DE 60125279 T DE60125279 T DE 60125279T DE 60125279 D1 DE60125279 D1 DE 60125279D1
Authority
DE
Germany
Prior art keywords
jet
mixer
engines
jet engines
jet mixer
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
Application number
DE60125279T
Other languages
English (en)
Other versions
DE60125279T2 (de
Inventor
Ronald L Balzer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=26898428&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=DE60125279(D1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Boeing Co filed Critical Boeing Co
Publication of DE60125279D1 publication Critical patent/DE60125279D1/de
Application granted granted Critical
Publication of DE60125279T2 publication Critical patent/DE60125279T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • B64D33/06—Silencing exhaust or propulsion jets
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/11—Two-dimensional triangular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Exhaust Silencers (AREA)
  • Jet Pumps And Other Pumps (AREA)
DE60125279T 2000-05-05 2001-05-07 Strahlmischer für ein Strahltriebwerk Expired - Lifetime DE60125279T2 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US20322200P 2000-05-05 2000-05-05
US203222P 2000-05-05
US09/822,962 US6612106B2 (en) 2000-05-05 2001-03-30 Segmented mixing device having chevrons for exhaust noise reduction in jet engines
US822962 2001-03-30

Publications (2)

Publication Number Publication Date
DE60125279D1 true DE60125279D1 (de) 2007-02-01
DE60125279T2 DE60125279T2 (de) 2007-05-03

Family

ID=26898428

Family Applications (1)

Application Number Title Priority Date Filing Date
DE60125279T Expired - Lifetime DE60125279T2 (de) 2000-05-05 2001-05-07 Strahlmischer für ein Strahltriebwerk

Country Status (3)

Country Link
US (2) US6612106B2 (de)
EP (1) EP1160439B1 (de)
DE (1) DE60125279T2 (de)

Families Citing this family (53)

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US7065957B2 (en) * 2000-05-05 2006-06-27 The Boeing Company Segmented mixing device for jet engines and aircraft
US6658839B2 (en) * 2002-02-28 2003-12-09 The Boeing Company Convergent/divergent segmented exhaust nozzle
US8997454B2 (en) * 2002-03-20 2015-04-07 The Regents Of The University Of California Turbofan engine noise suppression using fan flow deflector
US7644888B2 (en) * 2002-05-15 2010-01-12 The Boeing Company High-speed aircraft and methods for their manufacture
US6969028B2 (en) * 2003-01-22 2005-11-29 The Boeing Company Scarf nozzle for a jet engine and method of using the same
US20040244357A1 (en) * 2003-06-05 2004-12-09 Sloan Mark L. Divergent chevron nozzle and method
FR2857416B1 (fr) * 2003-07-09 2007-05-25 Snecma Moteurs Dispositif de reduction du bruit de jet d'une turbomachine
US7305817B2 (en) * 2004-02-09 2007-12-11 General Electric Company Sinuous chevron exhaust nozzle
US7114323B2 (en) * 2004-03-05 2006-10-03 United Technologies Corporation Jet exhaust noise reduction system and method
FR2868131B1 (fr) * 2004-03-25 2006-06-09 Airbus France Sas Tuyere primaire a chevrons pour turboreacteur a double flux d'aeronef et aeronef comportant une telle tuyere
US7246481B2 (en) * 2004-03-26 2007-07-24 General Electric Company Methods and apparatus for operating gas turbine engines
US7377109B2 (en) * 2004-04-09 2008-05-27 The Boeing Company Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flows
US7377108B2 (en) * 2004-04-09 2008-05-27 The Boeing Company Apparatus and method for reduction jet noise from single jets
FR2873166B1 (fr) * 2004-07-13 2008-10-31 Snecma Moteurs Sa Tuyere de turbomachine a motifs a reduction de bruit de jet
US20060059891A1 (en) * 2004-09-23 2006-03-23 Honeywell International, Inc. Quiet chevron/tab exhaust eductor system
US7434384B2 (en) * 2004-10-25 2008-10-14 United Technologies Corporation Fluid mixer with an integral fluid capture ducts forming auxiliary secondary chutes at the discharge end of said ducts
US7506501B2 (en) * 2004-12-01 2009-03-24 Honeywell International Inc. Compact mixer with trimmable open centerbody
US20060157613A1 (en) * 2005-01-19 2006-07-20 Adamson Eric E Supersonic aircraft with active lift distribution control for reducing sonic boom
EP1731747B1 (de) * 2005-06-10 2010-08-04 United Technologies Corporation Vorrichtung und Methode zur Reduktion des Luftstrahlaustrittslärms
US7966824B2 (en) 2006-08-09 2011-06-28 The Boeing Company Jet engine nozzle exit configurations and associated systems and methods
US8157207B2 (en) * 2006-08-09 2012-04-17 The Boeing Company Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods
KR20080024623A (ko) * 2006-09-14 2008-03-19 삼성전자주식회사 디스플레이장치 및 그 데이터 표시방법
US8015819B2 (en) * 2006-09-29 2011-09-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Wet active chevron nozzle for controllable jet noise reduction
US7870722B2 (en) * 2006-12-06 2011-01-18 The Boeing Company Systems and methods for passively directing aircraft engine nozzle flows
US7966826B2 (en) * 2007-02-14 2011-06-28 The Boeing Company Systems and methods for reducing noise from jet engine exhaust
US7963099B2 (en) * 2007-05-21 2011-06-21 General Electric Company Fluted chevron exhaust nozzle
US20110215204A1 (en) * 2007-06-20 2011-09-08 General Electric Company System and method for generating thrust
US20100019079A1 (en) * 2007-06-20 2010-01-28 General Electric Company Thrust generator for a rotary wing aircraft
US20080315042A1 (en) * 2007-06-20 2008-12-25 General Electric Company Thrust generator for a propulsion system
US7882696B2 (en) * 2007-06-28 2011-02-08 Honeywell International Inc. Integrated support and mixer for turbo machinery
US7926285B2 (en) * 2007-07-18 2011-04-19 General Electric Company Modular chevron exhaust nozzle
DE102007063018A1 (de) * 2007-12-21 2009-06-25 Rolls-Royce Deutschland Ltd & Co Kg Düse mit Leitelementen
FR2930972B1 (fr) * 2008-05-07 2012-11-30 Airbus France Turbomachine a double flux pour aeronef a emission de bruit reduite
US8087250B2 (en) 2008-06-26 2012-01-03 General Electric Company Duplex tab exhaust nozzle
US8746613B2 (en) * 2008-08-20 2014-06-10 Williams International Co., L.L.C. Jet engine exhaust nozzle and associated system and method of use
US8807458B2 (en) * 2009-04-29 2014-08-19 King Saud University Vortex-generating nozzle-end ring
US20110006165A1 (en) * 2009-07-10 2011-01-13 Peter Ireland Application of conformal sub boundary layer vortex generators to a foil or aero/ hydrodynamic surface
US8635875B2 (en) 2010-04-29 2014-01-28 Pratt & Whitney Canada Corp. Gas turbine engine exhaust mixer including circumferentially spaced-apart radial rows of tabs extending downstream on the radial walls, crests and troughs
FR2960028B1 (fr) * 2010-05-12 2016-07-15 Snecma Dispositif pour attenuer le bruit emis par le jet d'un moteur de propulsion d'un aeronef.
JP5842211B2 (ja) * 2011-01-21 2016-01-13 国立研究開発法人宇宙航空研究開発機構 空力騒音低減装置
US9416752B2 (en) 2012-02-28 2016-08-16 Pratt & Whitney Canada Corp. Gas turbine exhaust having reduced jet noise
US10190536B2 (en) 2012-09-17 2019-01-29 Pratt & Whitney Canada Corp. Turbine exhaust case mixer of gas turbine with variable thickness
DE102012220358A1 (de) 2012-11-08 2014-06-12 Rolls-Royce Deutschland Ltd & Co Kg Düse mit Leitvorrichtungen
DE102012220360A1 (de) 2012-11-08 2014-05-08 Rolls-Royce Deutschland Ltd & Co Kg Düse mit Leitvorrichtungen
FR3010454B1 (fr) * 2013-09-10 2024-02-16 Snecma Arriere corps de turboreacteur a flux melanges comportant un melangeur a lobes et des chevrons a surface interne non axisymetrique
US10953186B2 (en) 2014-07-31 2021-03-23 Koninklijke Philips N.V. Fluid coupling conduit for a patient interface device
US9915225B2 (en) 2015-02-06 2018-03-13 United Technologies Corporation Propulsion system arrangement for turbofan gas turbine engine
CN106567789B (zh) * 2016-07-27 2019-01-11 北京航空航天大学 一种防激波入喷口过膨胀大推力尾喷管
US12116913B2 (en) 2018-09-13 2024-10-15 The University Of Adelaide Exhaust gas assembly
US11028778B2 (en) 2018-09-27 2021-06-08 Pratt & Whitney Canada Corp. Engine with start assist
JP7297574B2 (ja) 2019-07-12 2023-06-26 三菱重工業株式会社 ガスタービンシステムおよびそれを備えた移動体
US11781506B2 (en) 2020-06-03 2023-10-10 Rtx Corporation Splitter and guide vane arrangement for gas turbine engines
US11772809B2 (en) 2021-11-27 2023-10-03 Airbus Defence and Space GmbH Fuselage for an aircraft with fuselage-integrated tailplane

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FR1422203A (fr) 1964-11-03 1965-12-24 Snecma Perfectionnement à la régulation de section des tuyères à effet de silencieux
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US5924632A (en) 1996-05-02 1999-07-20 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Jet nozzle having centerbody for enhanced exit area mixing
US6082635A (en) * 1996-06-12 2000-07-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Undulated nozzle for enhanced exit area mixing
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US5906097A (en) 1997-03-28 1999-05-25 The Boeing Company Engine flow control device
US6360528B1 (en) * 1997-10-31 2002-03-26 General Electric Company Chevron exhaust nozzle for a gas turbine engine
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Also Published As

Publication number Publication date
US20030115852A1 (en) 2003-06-26
US6612106B2 (en) 2003-09-02
EP1160439A1 (de) 2001-12-05
EP1160439B1 (de) 2006-12-20
US6786037B2 (en) 2004-09-07
US20010035004A1 (en) 2001-11-01
DE60125279T2 (de) 2007-05-03

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Legal Events

Date Code Title Description
8363 Opposition against the patent
8365 Fully valid after opposition proceedings