DE602007001911D1 - Abgasendstück zur Führung eines Gasstroms stromab einer Turbine - Google Patents

Abgasendstück zur Führung eines Gasstroms stromab einer Turbine

Info

Publication number
DE602007001911D1
DE602007001911D1 DE602007001911T DE602007001911T DE602007001911D1 DE 602007001911 D1 DE602007001911 D1 DE 602007001911D1 DE 602007001911 T DE602007001911 T DE 602007001911T DE 602007001911 T DE602007001911 T DE 602007001911T DE 602007001911 D1 DE602007001911 D1 DE 602007001911D1
Authority
DE
Germany
Prior art keywords
turbine
guide
gas flow
flow downstream
exhaust tail
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.)
Active
Application number
DE602007001911T
Other languages
English (en)
Inventor
Stephane Blanchard
Laurent Cameriano
Mathieu Dakowski
Alain Page
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of DE602007001911D1 publication Critical patent/DE602007001911D1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Exhaust Silencers (AREA)
DE602007001911T 2006-06-26 2007-06-25 Abgasendstück zur Führung eines Gasstroms stromab einer Turbine Active DE602007001911D1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0652641A FR2902838B1 (fr) 2006-06-26 2006-06-26 Cone d'echappement pour la canalisation d'une veine de gaz a l'aval d'une turbine

Publications (1)

Publication Number Publication Date
DE602007001911D1 true DE602007001911D1 (de) 2009-09-24

Family

ID=37734388

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602007001911T Active DE602007001911D1 (de) 2006-06-26 2007-06-25 Abgasendstück zur Führung eines Gasstroms stromab einer Turbine

Country Status (5)

Country Link
US (1) US7866162B2 (de)
EP (1) EP1873385B1 (de)
CA (1) CA2592483C (de)
DE (1) DE602007001911D1 (de)
FR (1) FR2902838B1 (de)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2935753B1 (fr) 2008-09-08 2011-07-01 Snecma Propulsion Solide Liaisons souples a butee pour fixation de piece en cmc
US8875520B2 (en) * 2008-12-31 2014-11-04 Rolls-Royce North American Technologies, Inc. Gas turbine engine device
US8800298B2 (en) * 2009-07-17 2014-08-12 United Technologies Corporation Washer with cooling passage for a turbine engine combustor
EP2410139A1 (de) * 2010-07-19 2012-01-25 Siemens Aktiengesellschaft Abgasdiffusor für eine Gasturbine
US9938900B2 (en) * 2011-05-26 2018-04-10 United Technologies Corporation Ceramic matrix composite turbine exhaust case for a gas turbine engine
PL220635B1 (pl) * 2011-10-03 2015-11-30 Gen Electric Dyfuzor gazu wydechowego i turbina zawierająca dyfuzor gazu wydechowego
FR2988777B1 (fr) * 2012-03-29 2014-04-25 Snecma Propulsion Solide Integration de pieces d'arriere-corps de moteur aeronautique
FR2994460B1 (fr) * 2012-08-09 2018-04-27 Safran Aircraft Engines Cone d'ejection pour turbomachine comportant des moyens d'aspiration de couche limite d'un flux d'air
US9644497B2 (en) * 2013-11-22 2017-05-09 Siemens Energy, Inc. Industrial gas turbine exhaust system with splined profile tail cone
US9551239B2 (en) * 2015-04-22 2017-01-24 Rohr, Inc. Exhaust assembly center body
US11118481B2 (en) 2017-02-06 2021-09-14 Raytheon Technologies Corporation Ceramic matrix composite turbine exhaust assembly for a gas turbine engine
FR3084916B1 (fr) * 2018-08-10 2020-07-17 Safran Ceramics Cone d'ejection a fixation flexible
CN109372653A (zh) * 2018-12-13 2019-02-22 中国航发沈阳发动机研究所 一种涡扇发动机降噪排气组件
FR3106376B1 (fr) * 2020-01-17 2022-08-12 Safran Aircraft Engines Sous ensemble de turbomachine comportant un insert conducteur thermique
FR3115827B1 (fr) * 2020-11-05 2023-09-22 Safran Nacelles Fixation d’un cône d’éjection dans une tuyère de turbomachine
FR3122695A1 (fr) * 2021-05-04 2022-11-11 Safran Aircraft Engines Cône de diffusion à double paroi définissant un plenum de refroidissement pour partie arrière de turboréacteur
FR3137721A1 (fr) * 2022-07-11 2024-01-12 Safran Ceramics Ensemble de turbine de turbomachine

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2570591A (en) * 1947-04-26 1951-10-09 Lockheed Aircraft Corp Fuel control system for turbo power plants
US2828603A (en) * 1948-04-09 1958-04-01 Westinghouse Electric Corp Afterburner for turbo jet engines and the like
GB739300A (en) * 1953-07-03 1955-10-26 Armstrong Siddeley Motors Ltd Improvements relating to the exhaust cone assemblies of gas turbine engines
US2799472A (en) * 1953-07-03 1957-07-16 Armstrong Siddeley Motors Ltd Exhaust cone assemblies of gas turbine engines
US4064961A (en) * 1976-04-05 1977-12-27 Rohr Industries, Incorporated Slanted cavity resonator
US4196856A (en) * 1977-11-25 1980-04-08 The Boeing Company Variable geometry convergent divergent exhaust nozzle
US4189939A (en) * 1977-12-12 1980-02-26 General Electric Company Compact multimission aircraft propulsion simulator
US4244441A (en) * 1979-07-31 1981-01-13 The Garrett Corporation Broad band acoustic attenuator
FR2516609A1 (fr) * 1981-11-19 1983-05-20 Snecma Dispositif de fixation de deux pieces de revolution en materiaux ayant des coefficients de dilatation differents
US4802629A (en) * 1982-10-22 1989-02-07 The Boeing Company Plug-type exhaust nozzle having a variable centerbody and translating shroud
FR2623249A1 (fr) * 1987-11-12 1989-05-19 Snecma Ensemble constitue de deux pieces en materiaux ayant des coefficients de dilatation differents, reliees entre elles et methode d'assemblage
US4909346A (en) * 1989-06-27 1990-03-20 Nordam Jet engine noise suppression system
US5230214A (en) * 1992-09-09 1993-07-27 United Technologies Corporation Recirculating zone inducing means for an augmentor burning section
FR2865502B1 (fr) * 2004-01-23 2006-03-03 Snecma Moteurs Bras monobloc accroche-flammes pour un dispositif de post combustion d'un turboreacteur a double flux
US9845727B2 (en) * 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US7784283B2 (en) * 2006-05-03 2010-08-31 Rohr, Inc. Sound-absorbing exhaust nozzle center plug
US7827780B2 (en) * 2006-11-15 2010-11-09 Pratt & Whitney Canada Corp. Assembly procedure for the adjustable pin-valve, fuel shut-off

Also Published As

Publication number Publication date
US20080104941A1 (en) 2008-05-08
CA2592483C (fr) 2014-08-12
EP1873385B1 (de) 2009-08-12
EP1873385A2 (de) 2008-01-02
CA2592483A1 (fr) 2007-12-26
US7866162B2 (en) 2011-01-11
FR2902838B1 (fr) 2013-03-15
FR2902838A1 (fr) 2007-12-28
EP1873385A3 (de) 2008-01-09

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition