FR2444231A1 - Chemise de chambre de combustion - Google Patents

Chemise de chambre de combustion

Info

Publication number
FR2444231A1
FR2444231A1 FR7930319A FR7930319A FR2444231A1 FR 2444231 A1 FR2444231 A1 FR 2444231A1 FR 7930319 A FR7930319 A FR 7930319A FR 7930319 A FR7930319 A FR 7930319A FR 2444231 A1 FR2444231 A1 FR 2444231A1
Authority
FR
France
Prior art keywords
downstream
segment
annular
jacket
liner
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.)
Granted
Application number
FR7930319A
Other languages
English (en)
Other versions
FR2444231B1 (fr
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.)
General Electric Co
Original Assignee
General Electric 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
Application filed by General Electric Co filed Critical General Electric Co
Publication of FR2444231A1 publication Critical patent/FR2444231A1/fr
Application granted granted Critical
Publication of FR2444231B1 publication Critical patent/FR2444231B1/fr
Granted 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
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections

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)
  • Centrifugal Separators (AREA)
  • Spray-Type Burners (AREA)

Abstract

Chemise pourvue de fentes de refroidissement éliminant les surchauffes localisées. Elle comprend un élargissement annulaire 23 reliant les côtés externes des segments de chemise et délimitant avec le segment aval une chambre qui communique avec la fente annulaire 33 au moyen d'une surface curviligne 28 contiguë au segment amont de chemise; une ouverture 34 dans le côté aval de l'élargissement annulaire, faisant entrer le flux d'air de refroidissement dans la chambre, où il est ensuite centrifugé radialement vers l'intérieur par la surface curviligne et suit le côté radialement interne 37 de la fente annulaire avant de s'attacher au segment aval de chemise; une série d'appuis 38, répartis circulairement, disposés dans la fente annulaire et fixés sur le segment aval de chemise 24, limitant le déplacement vers l'extérieur que fait la partie de chemise amont sous l'effet de la dilatation thermique. Application aux moteurs d'avion.
FR7930319A 1978-12-11 1979-12-11 Chemise de chambre de combustion Granted FR2444231A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/967,928 US4259842A (en) 1978-12-11 1978-12-11 Combustor liner slot with cooled props

Publications (2)

Publication Number Publication Date
FR2444231A1 true FR2444231A1 (fr) 1980-07-11
FR2444231B1 FR2444231B1 (fr) 1984-12-21

Family

ID=25513502

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7930319A Granted FR2444231A1 (fr) 1978-12-11 1979-12-11 Chemise de chambre de combustion

Country Status (6)

Country Link
US (1) US4259842A (fr)
JP (1) JPS5599526A (fr)
DE (1) DE2949473A1 (fr)
FR (1) FR2444231A1 (fr)
GB (1) GB2036945B (fr)
IT (1) IT1126444B (fr)

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2490728A1 (fr) * 1980-09-25 1982-03-26 Snecma Dispositif de refroidissement par film d'air pour tube a flamme de moteur a turbine a gaz
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4655044A (en) * 1983-12-21 1987-04-07 United Technologies Corporation Coated high temperature combustor liner
DE3540942A1 (de) * 1985-11-19 1987-05-21 Mtu Muenchen Gmbh Umkehrbrennkammer, insbesondere umkehrringbrennkammer, fuer gasturbinentriebwerke, mit mindestens einer flammrohrwandfilmkuehleinrichtung
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US4896510A (en) * 1987-02-06 1990-01-30 General Electric Company Combustor liner cooling arrangement
JP2597800B2 (ja) * 1992-06-12 1997-04-09 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジン用燃焼器
JPH08278029A (ja) * 1995-02-06 1996-10-22 Toshiba Corp 燃焼器用ライナー及びその製造方法
US6250082B1 (en) * 1999-12-03 2001-06-26 General Electric Company Combustor rear facing step hot side contour method and apparatus
US6438958B1 (en) * 2000-02-28 2002-08-27 General Electric Company Apparatus for reducing heat load in combustor panels
US7104067B2 (en) * 2002-10-24 2006-09-12 General Electric Company Combustor liner with inverted turbulators
US6875476B2 (en) * 2003-01-15 2005-04-05 General Electric Company Methods and apparatus for manufacturing turbine engine components
US7546743B2 (en) * 2005-10-12 2009-06-16 General Electric Company Bolting configuration for joining ceramic combustor liner to metal mounting attachments
GB2434199B (en) * 2006-01-14 2011-01-05 Alstom Technology Ltd Combustor liner with heat shield
EP1813869A3 (fr) * 2006-01-25 2013-08-14 Rolls-Royce plc Éléments de paroi de chambre de combustion de turbine à gaz
JP4969384B2 (ja) * 2007-09-25 2012-07-04 三菱重工業株式会社 ガスタービン燃焼器の冷却構造
US20100107645A1 (en) * 2008-10-31 2010-05-06 General Electric Company Combustor liner cooling flow disseminator and related method
US9810081B2 (en) 2010-06-11 2017-11-07 Siemens Energy, Inc. Cooled conduit for conveying combustion gases
US9267687B2 (en) 2011-11-04 2016-02-23 General Electric Company Combustion system having a venturi for reducing wakes in an airflow
US8899975B2 (en) * 2011-11-04 2014-12-02 General Electric Company Combustor having wake air injection
US9739201B2 (en) 2013-05-08 2017-08-22 General Electric Company Wake reducing structure for a turbine system and method of reducing wake
US9322553B2 (en) 2013-05-08 2016-04-26 General Electric Company Wake manipulating structure for a turbine system
US9435221B2 (en) 2013-08-09 2016-09-06 General Electric Company Turbomachine airfoil positioning
WO2016032434A1 (fr) 2014-08-26 2016-03-03 Siemens Energy, Inc. Agencement de trous de refroidissement de film pour résonateurs acoustiques dans des moteurs à turbine à gaz
GB201603166D0 (en) * 2016-02-24 2016-04-06 Rolls Royce Plc A combustion chamber
JP6815735B2 (ja) * 2016-03-03 2021-01-20 三菱パワー株式会社 音響装置、ガスタービン
US11371703B2 (en) * 2018-01-12 2022-06-28 Raytheon Technologies Corporation Apparatus and method for mitigating particulate accumulation on a component of a gas turbine
JP2022150946A (ja) * 2021-03-26 2022-10-07 本田技研工業株式会社 ガスタービン用燃焼器

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1049280A (fr) * 1950-03-24 1953-12-29 Thomson Houston Comp Francaise Perfectionnements aux chambres de combustion
US3572031A (en) * 1969-07-11 1971-03-23 United Aircraft Corp Variable area cooling passages for gas turbine burners
US3826082A (en) * 1973-03-30 1974-07-30 Gen Electric Combustion liner cooling slot stabilizing dimple
US3978662A (en) * 1975-04-28 1976-09-07 General Electric Company Cooling ring construction for combustion chambers
FR2340453A1 (fr) * 1976-02-06 1977-09-02 Snecma Corps de chambre de combustion, notamment pour turboreacteurs
US4050241A (en) * 1975-12-22 1977-09-27 General Electric Company Stabilizing dimple for combustion liner cooling slot
US4064300A (en) * 1975-07-16 1977-12-20 Rolls-Royce Limited Laminated materials
US4077205A (en) * 1975-12-05 1978-03-07 United Technologies Corporation Louver construction for liner of gas turbine engine combustor

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1049280A (fr) * 1950-03-24 1953-12-29 Thomson Houston Comp Francaise Perfectionnements aux chambres de combustion
US3572031A (en) * 1969-07-11 1971-03-23 United Aircraft Corp Variable area cooling passages for gas turbine burners
US3826082A (en) * 1973-03-30 1974-07-30 Gen Electric Combustion liner cooling slot stabilizing dimple
US3978662A (en) * 1975-04-28 1976-09-07 General Electric Company Cooling ring construction for combustion chambers
US4064300A (en) * 1975-07-16 1977-12-20 Rolls-Royce Limited Laminated materials
US4077205A (en) * 1975-12-05 1978-03-07 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
US4050241A (en) * 1975-12-22 1977-09-27 General Electric Company Stabilizing dimple for combustion liner cooling slot
FR2340453A1 (fr) * 1976-02-06 1977-09-02 Snecma Corps de chambre de combustion, notamment pour turboreacteurs

Also Published As

Publication number Publication date
IT7927751A0 (it) 1979-11-30
FR2444231B1 (fr) 1984-12-21
GB2036945A (en) 1980-07-02
JPS5599526A (en) 1980-07-29
DE2949473A1 (de) 1980-06-19
JPS6335897B2 (fr) 1988-07-18
GB2036945B (en) 1983-02-09
US4259842A (en) 1981-04-07
IT1126444B (it) 1986-05-21

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Legal Events

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