DE69602804D1 - Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind - Google Patents

Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind

Info

Publication number
DE69602804D1
DE69602804D1 DE69602804T DE69602804T DE69602804D1 DE 69602804 D1 DE69602804 D1 DE 69602804D1 DE 69602804 T DE69602804 T DE 69602804T DE 69602804 T DE69602804 T DE 69602804T DE 69602804 D1 DE69602804 D1 DE 69602804D1
Authority
DE
Germany
Prior art keywords
combustion chamber
large number
cooling holes
film cooling
different axial
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
DE69602804T
Other languages
English (en)
Other versions
DE69602804T2 (de
Inventor
Denis Roger Henri Ansart
Patrick Samuel Andre Ciccia
Michel Andre Albert Desaulty
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
Publication of DE69602804D1 publication Critical patent/DE69602804D1/de
Application granted granted Critical
Publication of DE69602804T2 publication Critical patent/DE69602804T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/30—Arrangement of components
    • F05B2250/32—Arrangement of components according to their shape
    • F05B2250/322—Arrangement of components according to their shape tangential
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling

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)
DE69602804T 1995-04-26 1996-04-24 Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind Expired - Lifetime DE69602804T2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR9504968A FR2733582B1 (fr) 1995-04-26 1995-04-26 Chambre de combustion comportant une multiperforation d'inclinaison axiale et tangentielle variable

Publications (2)

Publication Number Publication Date
DE69602804D1 true DE69602804D1 (de) 1999-07-15
DE69602804T2 DE69602804T2 (de) 2000-01-27

Family

ID=9478445

Family Applications (1)

Application Number Title Priority Date Filing Date
DE69602804T Expired - Lifetime DE69602804T2 (de) 1995-04-26 1996-04-24 Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind

Country Status (5)

Country Link
US (1) US5775108A (de)
EP (1) EP0743490B1 (de)
JP (1) JP3302559B2 (de)
DE (1) DE69602804T2 (de)
FR (1) FR2733582B1 (de)

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FR2770283B1 (fr) * 1997-10-29 1999-11-19 Snecma Chambre de combustion pour turbomachine
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US6408629B1 (en) 2000-10-03 2002-06-25 General Electric Company Combustor liner having preferentially angled cooling holes
US6620457B2 (en) * 2001-07-13 2003-09-16 General Electric Company Method for thermal barrier coating and a liner made using said method
FR2856468B1 (fr) * 2003-06-17 2007-11-23 Snecma Moteurs Chambre de combustion annulaire de turbomachine
FR2856467B1 (fr) * 2003-06-18 2005-09-02 Snecma Moteurs Chambre de combustion annulaire de turbomachine
US7146816B2 (en) * 2004-08-16 2006-12-12 Honeywell International, Inc. Effusion momentum control
US20060037323A1 (en) * 2004-08-20 2006-02-23 Honeywell International Inc., Film effectiveness enhancement using tangential effusion
US7464554B2 (en) * 2004-09-09 2008-12-16 United Technologies Corporation Gas turbine combustor heat shield panel or exhaust panel including a cooling device
US7614235B2 (en) * 2005-03-01 2009-11-10 United Technologies Corporation Combustor cooling hole pattern
FR2892180B1 (fr) * 2005-10-18 2008-02-01 Snecma Sa Amelioration des perfomances d'une chambre de combustion par multiperforation des parois
US7631502B2 (en) * 2005-12-14 2009-12-15 United Technologies Corporation Local cooling hole pattern
US7546737B2 (en) * 2006-01-24 2009-06-16 Honeywell International Inc. Segmented effusion cooled gas turbine engine combustor
FR2899315B1 (fr) * 2006-03-30 2012-09-28 Snecma Configuration d'ouvertures de dilution dans une paroi de chambre de combustion de turbomachine
US7887322B2 (en) * 2006-09-12 2011-02-15 General Electric Company Mixing hole arrangement and method for improving homogeneity of an air and fuel mixture in a combustor
US7942006B2 (en) * 2007-03-26 2011-05-17 Honeywell International Inc. Combustors and combustion systems for gas turbine engines
US8091367B2 (en) * 2008-09-26 2012-01-10 Pratt & Whitney Canada Corp. Combustor with improved cooling holes arrangement
FR2941287B1 (fr) * 2009-01-19 2011-03-25 Snecma Paroi de chambre de combustion de turbomachine a une seule rangee annulaire d'orifices d'entree d'air primaire et de dilution
US8640464B2 (en) * 2009-02-23 2014-02-04 Williams International Co., L.L.C. Combustion system
FR2955374B1 (fr) * 2010-01-15 2012-05-18 Turbomeca Chambre de combustion multi-percee a ecoulements tangentiels contre giratoires
FR2974162B1 (fr) * 2011-04-14 2018-04-13 Safran Aircraft Engines Virole de tube a flamme dans une chambre de combustion de turbomachine
FR2979416B1 (fr) * 2011-08-26 2013-09-20 Turbomeca Paroi de chambre de combustion
EP3039340B1 (de) * 2013-08-30 2018-11-28 United Technologies Corporation Vena-contracta-verwirbelungs-verdünnungspassagen für eine gasturbinenmotor-brennkammer
US9453424B2 (en) * 2013-10-21 2016-09-27 Siemens Energy, Inc. Reverse bulk flow effusion cooling
FR3013996B1 (fr) 2013-12-02 2017-04-28 Office National Detudes Et De Rech Aerospatiales Onera Procede de reparation locale de barrieres thermiques
FR3014115B1 (fr) 2013-12-02 2017-04-28 Office National Detudes Et De Rech Aerospatiales Onera Procede et systeme de depot d'oxyde sur un composant poreux
WO2015103357A1 (en) 2013-12-31 2015-07-09 United Technologies Corporation Gas turbine engine wall assembly with enhanced flow architecture
EP3099976B1 (de) 2014-01-30 2019-03-13 United Technologies Corporation Kühlfluss für führungspaneel in einer gasturbinenbrennkammer
US20160258623A1 (en) * 2015-03-05 2016-09-08 United Technologies Corporation Combustor and heat shield configurations for a gas turbine engine
DE102016201452A1 (de) 2016-02-01 2017-08-03 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit Wandkonturierung
JP6026028B1 (ja) * 2016-03-10 2016-11-16 三菱日立パワーシステムズ株式会社 燃焼器用パネル、燃焼器、燃焼装置、ガスタービン、及び燃焼器用パネルの冷却方法
US10823410B2 (en) 2016-10-26 2020-11-03 Raytheon Technologies Corporation Cast combustor liner panel radius for gas turbine engine combustor
US10830448B2 (en) 2016-10-26 2020-11-10 Raytheon Technologies Corporation Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor
US10670269B2 (en) * 2016-10-26 2020-06-02 Raytheon Technologies Corporation Cast combustor liner panel gating feature for a gas turbine engine combustor
US10669939B2 (en) 2016-10-26 2020-06-02 Raytheon Technologies Corporation Combustor seal for a gas turbine engine combustor
US10935243B2 (en) 2016-11-30 2021-03-02 Raytheon Technologies Corporation Regulated combustor liner panel for a gas turbine engine combustor
US11015529B2 (en) 2016-12-23 2021-05-25 General Electric Company Feature based cooling using in wall contoured cooling passage
US10480327B2 (en) 2017-01-03 2019-11-19 General Electric Company Components having channels for impingement cooling
US10753283B2 (en) 2017-03-20 2020-08-25 Pratt & Whitney Canada Corp. Combustor heat shield cooling hole arrangement
US11029027B2 (en) 2018-10-03 2021-06-08 Raytheon Technologies Corporation Dilution/effusion hole pattern for thick combustor panels
CN113251441B (zh) * 2021-06-28 2022-03-25 南京航空航天大学 一种新型航天发动机用多斜孔板椭球摆冷却结构

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FR512723A (fr) * 1920-01-05 1921-01-29 Rene Lucien Joseph Pierrel Générateur de gaz sous pression par combustion continue en vase clos
GB1271084A (en) * 1968-05-13 1972-04-19 T C Borrie Ltd Improvements in or relating to cartridge-operated hand tools
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US3916619A (en) * 1972-10-30 1975-11-04 Hitachi Ltd Burning method for gas turbine combustor and a construction thereof
DE2607214A1 (de) * 1976-02-23 1977-09-01 Volkswagenwerk Ag Brennkammer fuer gasturbinen
FR2410138A2 (fr) * 1977-11-29 1979-06-22 Snecma Perfectionnements aux chambres de combustion pour moteur a turbine a gaz
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US4790140A (en) * 1985-01-18 1988-12-13 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Liner cooling construction for gas turbine combustor or the like
DE3711751A1 (de) * 1987-04-07 1988-10-20 Bergwerksverband Gmbh Gleichstromdatenuebertragungseinrichtung
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US5329773A (en) * 1989-08-31 1994-07-19 Alliedsignal Inc. Turbine combustor cooling system
US5181379A (en) * 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
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FR2714152B1 (fr) * 1993-12-22 1996-01-19 Snecma Dispositif de fixation d'une tuile de protection thermique dans une chambre de combustion.

Also Published As

Publication number Publication date
JPH08312960A (ja) 1996-11-26
EP0743490B1 (de) 1999-06-09
FR2733582B1 (fr) 1997-06-06
DE69602804T2 (de) 2000-01-27
EP0743490A1 (de) 1996-11-20
US5775108A (en) 1998-07-07
FR2733582A1 (fr) 1996-10-31
JP3302559B2 (ja) 2002-07-15

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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