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GB1351069A - Cooling of combustion chamber walls - Google Patents

Cooling of combustion chamber walls

Info

Publication number
GB1351069A
GB1351069A GB4601072A GB4601072A GB1351069A GB 1351069 A GB1351069 A GB 1351069A GB 4601072 A GB4601072 A GB 4601072A GB 4601072 A GB4601072 A GB 4601072A GB 1351069 A GB1351069 A GB 1351069A
Authority
GB
United Kingdom
Prior art keywords
bore
annular
oct
connecting member
gas turbine
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
Application number
GB4601072A
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 GB1351069A publication Critical patent/GB1351069A/en
Expired 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
    • 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)
  • Spray-Type Burners (AREA)
  • Sampling And Sample Adjustment (AREA)

Abstract

1351069 Gas turbine flame tubes SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 5 Oct 1972 [8 Oct 1971] 46010/72 Heading F1L An annular connecting member 13, Fig.6, joining upstream and downstream wall sections 10a, 10b of a gas turbine flame tube includes a tongue 19 defining with flange 16 an annular duct 20 into which emerge axially extending circumferentially spaced cooling air passages, each consisting of a bore 22 opening abruptly at 23 into a bore 24 of larger cross-section which opens into duct 20. The entrance to bore 22 may be chamfered at 27, Fig.7 (not shown). Each bore 24 is fully circular or, in a modification Fig. 9, part of the connecting member is cut away so that the corresponding bores 24b are semicircular and surrounded by an annular channel 29. Relative demensions of the bores are specified.
GB4601072A 1971-10-08 1972-10-05 Cooling of combustion chamber walls Expired GB1351069A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7136330A FR2155835B1 (en) 1971-10-08 1971-10-08

Publications (1)

Publication Number Publication Date
GB1351069A true GB1351069A (en) 1974-04-24

Family

ID=9084127

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4601072A Expired GB1351069A (en) 1971-10-08 1972-10-05 Cooling of combustion chamber walls

Country Status (3)

Country Link
US (1) US3811276A (en)
FR (1) FR2155835B1 (en)
GB (1) GB1351069A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4232442A1 (en) * 1992-09-28 1994-03-31 Asea Brown Boveri Gas turbine combustion chamber
CN113154453A (en) * 2021-05-06 2021-07-23 中国航发湖南动力机械研究所 Tangential inclined annular membrane diverging and cooling structure

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1429677A (en) * 1973-03-20 1976-03-24 Rolls Royce Gas turbine engine combustion equipment
US4232527A (en) * 1979-04-13 1980-11-11 General Motors Corporation Combustor liner joints
US4529358A (en) * 1984-02-15 1985-07-16 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Vortex generating flow passage design for increased film cooling effectiveness
FR2604509B1 (en) * 1986-09-25 1988-11-18 Snecma PROCESS FOR PRODUCING A COOLING FILM FOR A TURBOMACHINE COMBUSTION CHAMBER, FILM THUS PRODUCED AND COMBUSTION CHAMBER COMPRISING SAME
US5329773A (en) * 1989-08-31 1994-07-19 Alliedsignal Inc. Turbine combustor cooling system
EP0761928A3 (en) * 1995-08-31 1999-03-31 United Technologies Corporation Edge geometry to facilitate eddy-current inspection
US7571611B2 (en) * 2006-04-24 2009-08-11 General Electric Company Methods and system for reducing pressure losses in gas turbine engines
GB2441342B (en) * 2006-09-01 2009-03-18 Rolls Royce Plc Wall elements with apertures for gas turbine engine components
CH699997A1 (en) * 2008-11-25 2010-05-31 Alstom Technology Ltd Combustor assembly for operating a gas turbine.
US20100263384A1 (en) * 2009-04-17 2010-10-21 Ronald James Chila Combustor cap with shaped effusion cooling holes
US9851096B2 (en) * 2012-04-16 2017-12-26 Gas Technology Institute Steam generator film cooling using produced water
JP6082287B2 (en) * 2013-03-15 2017-02-15 三菱日立パワーシステムズ株式会社 Combustor, gas turbine, and first cylinder of combustor
US10101030B2 (en) * 2014-09-02 2018-10-16 Honeywell International Inc. Gas turbine engines with plug resistant effusion cooling holes
JP6485942B2 (en) * 2014-09-25 2019-03-20 三菱日立パワーシステムズ株式会社 Combustor, gas turbine
US11988145B2 (en) * 2018-01-12 2024-05-21 Rtx Corporation Apparatus and method for mitigating airflow separation around engine combustor
US11306659B2 (en) * 2019-05-28 2022-04-19 Honeywell International Inc. Plug resistant effusion holes for gas turbine engine
US11867402B2 (en) * 2021-03-19 2024-01-09 Rtx Corporation CMC stepped combustor liner
CN117091161A (en) 2022-05-13 2023-11-21 通用电气公司 Combustor liner hollow plate design and construction
CN117091159A (en) 2022-05-13 2023-11-21 通用电气公司 Combustor liner
CN117091158A (en) 2022-05-13 2023-11-21 通用电气公司 Combustor chamber mesh structure
CN117091157A (en) 2022-05-13 2023-11-21 通用电气公司 Plate hanger structure for durable combustor liner
CN117091162A (en) 2022-05-13 2023-11-21 通用电气公司 Burner with dilution hole structure
JP2025117172A (en) * 2024-01-30 2025-08-12 本田技研工業株式会社 Gas turbine combustor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3038309A (en) * 1959-07-21 1962-06-12 Gen Electric Cooling liner for jet engine afterburner
NL127178C (en) * 1959-11-20
GB1060097A (en) * 1964-05-13 1967-02-22 Rolls Royce Improvements relating to the flow of a cooling fluid
GB1130371A (en) * 1964-10-20 1968-10-16 Rolls Royce Improvements in boundary wall structures for hot fluid streams
US3359724A (en) * 1965-08-03 1967-12-26 Bristol Siddeley Engines Ltd Cooling means in combustors for gas turbine engines
US3369363A (en) * 1966-01-19 1968-02-20 Gen Electric Integral spacing rings for annular combustion chambers
US3589128A (en) * 1970-02-02 1971-06-29 Avco Corp Cooling arrangement for a reverse flow gas turbine combustor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4232442A1 (en) * 1992-09-28 1994-03-31 Asea Brown Boveri Gas turbine combustion chamber
CN113154453A (en) * 2021-05-06 2021-07-23 中国航发湖南动力机械研究所 Tangential inclined annular membrane diverging and cooling structure
CN113154453B (en) * 2021-05-06 2022-07-08 中国航发湖南动力机械研究所 Tangential tilting type annular membrane diverging and cooling structure

Also Published As

Publication number Publication date
US3811276A (en) 1974-05-21
FR2155835A1 (en) 1973-05-25
FR2155835B1 (en) 1974-05-31

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PE20 Patent expired after termination of 20 years