DE69606133T2 - Strömungskörper für den Trägermast eines Turbostrahltriebwerks mit onduliertem Mischer - Google Patents

Strömungskörper für den Trägermast eines Turbostrahltriebwerks mit onduliertem Mischer

Info

Publication number
DE69606133T2
DE69606133T2 DE69606133T DE69606133T DE69606133T2 DE 69606133 T2 DE69606133 T2 DE 69606133T2 DE 69606133 T DE69606133 T DE 69606133T DE 69606133 T DE69606133 T DE 69606133T DE 69606133 T2 DE69606133 T2 DE 69606133T2
Authority
DE
Germany
Prior art keywords
undulated
turbojet
mast
mixer
flow body
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
DE69606133T
Other languages
English (en)
Other versions
DE69606133D1 (de
Inventor
Bruno Filbert Dessale
Jean-Luc Gerard Duparcq
Hugues Denis Joubert
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Application granted granted Critical
Publication of DE69606133D1 publication Critical patent/DE69606133D1/de
Publication of DE69606133T2 publication Critical patent/DE69606133T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F02K1/48—Corrugated nozzles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • F02K1/38—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
    • F02K1/52—Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
DE69606133T 1995-10-18 1996-10-16 Strömungskörper für den Trägermast eines Turbostrahltriebwerks mit onduliertem Mischer Expired - Lifetime DE69606133T2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR9512205A FR2740175B1 (fr) 1995-10-18 1995-10-18 Dispositif de pylone associe au melangeur d'une tuyere d'ejection de turboreacteur a flux melangeur

Publications (2)

Publication Number Publication Date
DE69606133D1 DE69606133D1 (de) 2000-02-17
DE69606133T2 true DE69606133T2 (de) 2000-06-15

Family

ID=9483634

Family Applications (1)

Application Number Title Priority Date Filing Date
DE69606133T Expired - Lifetime DE69606133T2 (de) 1995-10-18 1996-10-16 Strömungskörper für den Trägermast eines Turbostrahltriebwerks mit onduliertem Mischer

Country Status (4)

Country Link
US (1) US5755092A (de)
EP (1) EP0769617B1 (de)
DE (1) DE69606133T2 (de)
FR (1) FR2740175B1 (de)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5884472A (en) * 1995-10-11 1999-03-23 Stage Iii Technologies, L.C. Alternating lobed mixer/ejector concept suppressor
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
US6314721B1 (en) 1998-09-04 2001-11-13 United Technologies Corporation Tabbed nozzle for jet noise suppression
US6487848B2 (en) 1998-11-06 2002-12-03 United Technologies Corporation Gas turbine engine jet noise suppressor
WO2000040851A1 (en) 1999-01-04 2000-07-13 Allison Advanced Development Company Exhaust mixer and apparatus using same
US6178740B1 (en) 1999-02-25 2001-01-30 The Boeing Company Turbo fan engine nacelle exhaust system with concave primary nozzle plug
DE19909793A1 (de) * 1999-03-05 2000-09-07 Rolls Royce Deutschland Blütenmischer für ein Zweikreis-Strahltriebwerk
DE19909792A1 (de) * 1999-03-05 2000-09-07 Rolls Royce Deutschland Blütenmischer für ein Zweikreis-Strahltriebwerk
US7316109B2 (en) * 2006-01-17 2008-01-08 Fleetguard, Inc Lobed exhaust diffuser apparatus, system, and method
US7293401B2 (en) * 2002-03-20 2007-11-13 The Regents Of The University Of California Jet engine noise suppressor
US6983912B2 (en) * 2002-04-30 2006-01-10 The Boeing Company Hybrid exhaust heat shield for pylon mounted gas turbine engines
FR2855558B1 (fr) * 2003-05-28 2005-07-15 Snecma Moteurs Tuyere de turbomachine a reduction de bruit
FR2875854B1 (fr) * 2004-09-29 2009-04-24 Snecma Propulsion Solide Sa Melangeur pour tuyere a flux separes
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
US7757481B2 (en) * 2006-01-17 2010-07-20 Cummins Filtration Ip, Inc Enclosed volume exhaust diffuser apparatus, system, and method
US8549850B2 (en) * 2008-10-31 2013-10-08 Cummins Filtration Ip, Inc. Exhaust gas aspirator
DE102010014037A1 (de) * 2009-04-02 2010-11-04 Cummins Filtration IP, Inc., Minneapolis Reduktionsmittelzersetzungssystem
GB201011056D0 (en) * 2010-07-01 2010-08-18 Rolls Royce Plc Pylon for attaching a gas turbine engine
WO2014151673A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Aerodynamic track fairing for a gas turbine engine fan nacelle
CN105392700B (zh) 2013-07-26 2018-12-18 Mra系统有限责任公司 飞行器发动机吊架
CN115234938B (zh) * 2022-09-21 2022-11-25 中国空气动力研究与发展中心空天技术研究所 用于旁路引气高马赫数涡轮发动机气流掺混器及设计方法

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4238092A (en) * 1978-08-17 1980-12-09 Rohr Industries, Inc. Accessory for a turbine engine
GB2082259B (en) * 1980-08-15 1984-03-07 Rolls Royce Exhaust flow mixers and nozzles
US4466587A (en) * 1981-12-21 1984-08-21 General Electric Company Nacelle installation
GB2146702B (en) * 1983-09-14 1987-12-23 Rolls Royce Exhaust mixer for turbofan aeroengine
US4712750A (en) * 1986-05-02 1987-12-15 The Boeing Company Temperature control device for jet engine nacelle associated structure
GB2209054B (en) * 1987-08-26 1992-04-15 Rolls Royce Plc Gas turbine nozzles
US5216879A (en) * 1991-08-30 1993-06-08 United Technologies Corporation Propulsion system assembly
US5265807A (en) * 1992-06-01 1993-11-30 Rohr, Inc. Aerodynamic stiffening ring for an aircraft turbine engine mixer
US5524847A (en) * 1993-09-07 1996-06-11 United Technologies Corporation Nacelle and mounting arrangement for an aircraft engine
US5444912A (en) * 1993-10-29 1995-08-29 Folmer; Carroll W. Method for forming aircraft engine nacelle exhaust mixers and similar products

Also Published As

Publication number Publication date
US5755092A (en) 1998-05-26
FR2740175B1 (fr) 1997-11-21
EP0769617B1 (de) 2000-01-12
FR2740175A1 (fr) 1997-04-25
DE69606133D1 (de) 2000-02-17
EP0769617A1 (de) 1997-04-23

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: SNECMA MOTEURS, PARIS, FR

8327 Change in the person/name/address of the patent owner

Owner name: SNECMA, PARIS, FR