GB1239559A - - Google Patents

Info

Publication number
GB1239559A
GB1239559A GB529868A GB1239559DA GB1239559A GB 1239559 A GB1239559 A GB 1239559A GB 529868 A GB529868 A GB 529868A GB 1239559D A GB1239559D A GB 1239559DA GB 1239559 A GB1239559 A GB 1239559A
Authority
GB
United Kingdom
Prior art keywords
air
vanes
passages
apertures
combustion chamber
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
GB529868A
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 filed Critical
Publication of GB1239559A publication Critical patent/GB1239559A/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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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

Abstract

1,239,559. Gas turbine engine combustion equipment. GENERAL MOTORS CORP. Feb. 1, 1968, No. 5298/68. Headings F1G, F1L. A combustion system for a gas turbine engine comprises an annular casing 14 within which is mounted an annular combustion chamber 18 radially spaced from the casing to provide inner and outer annular air passages 22, 20, circumferentially spaced stator vanes 28 mounted across the downstream end of the combustion chamber 18, circumferentially spaced apertures 34 in the combustion chamber 18 adjacent the leading edges 36 of the vanes 28, and short truncated tubes 38 mounted in each aperture 34 so as to direct air from the annular air passages 20, 22 on to the leading edges 36. Compressed air enters the casing 14 through an inlet 17 and is proportional by a deflector 23 between primary air admission passages 19 and the annular air passages 20, 22. A fuel ring 24 mounted inside the deflector 23 includes a number of circumferentially spaced fuel spray nozzles 26. The stator vanes 28 are hollow and have open outer and inner ends 30 and 32 in fluid communication with the annular air passages 20 and 22, respectively. The walls 33 of the vanes have a number of apertures 35 through which air from the passages 20, 22 flows to provide convection cooling of the vanes 28 and a film of cool air adjacent their outer surface. The leading edges 36 of the vanes 28 are impingement cooled by air flowing through the apertures 34. Apertures (not shown) in the combustion chamber radially inner wall admit dilution air to the spaces between the vanes. The particular combustion chamber illustrated is of the progressive burning type so that primary air is admitted through larger apertures 44 and smaller apertures 45 in addition to the primary air admitted through passages 19. Adequate film cooling is provided by air flowing through the slots 42. The combustion system has an axial length of such reduced dimensions as to be applicable to lift type gas turbine engines.
GB529868A 1966-06-27 1968-02-01 Expired GB1239559A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US56065866A 1966-06-27 1966-06-27

Publications (1)

Publication Number Publication Date
GB1239559A true GB1239559A (en) 1971-07-21

Family

ID=24238758

Family Applications (1)

Application Number Title Priority Date Filing Date
GB529868A Expired GB1239559A (en) 1966-06-27 1968-02-01

Country Status (2)

Country Link
US (1) US3608310A (en)
GB (1) GB1239559A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2939563A1 (en) * 1978-10-02 1980-04-17 Gen Electric GAS TURBINE ENGINE
EP0178242A1 (en) * 1984-10-11 1986-04-16 United Technologies Corporation Cooling scheme for combustor vane interface
GB2263733A (en) * 1992-01-28 1993-08-04 Snecma Turbomachine with removable combustion chamber.
US5235805A (en) * 1991-03-20 1993-08-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine engine combustion chamber with oxidizer intake flow control

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4733538A (en) * 1978-10-02 1988-03-29 General Electric Company Combustion selective temperature dilution
US4825640A (en) * 1987-06-22 1989-05-02 Sundstrand Corporation Combustor with enhanced turbine nozzle cooling
US4926630A (en) * 1988-12-12 1990-05-22 Sundstrand Corporation Jet air cooled turbine shroud for improved swirl cooling and mixing
US5101620A (en) * 1988-12-28 1992-04-07 Sundstrand Corporation Annular combustor for a turbine engine without film cooling
US5303543A (en) * 1990-02-08 1994-04-19 Sundstrand Corporation Annular combustor for a turbine engine with tangential passages sized to provide only combustion air
US5239818A (en) * 1992-03-30 1993-08-31 General Electric Company Dilution pole combustor and method
DE19651881A1 (en) * 1996-12-13 1998-06-18 Asea Brown Boveri Combustion chamber with integrated guide vanes
US6101814A (en) * 1999-04-15 2000-08-15 United Technologies Corporation Low emissions can combustor with dilution hole arrangement for a turbine engine
DE10214574A1 (en) * 2002-04-02 2003-10-16 Rolls Royce Deutschland Combustion chamber for jet propulsion unit has openings in wall, ceramic, glass or glass-ceramic, secondary air element with profiling
GB2391297A (en) * 2002-07-24 2004-02-04 Rolls Royce Plc Gas supply assembly
US7234304B2 (en) * 2002-10-23 2007-06-26 Pratt & Whitney Canada Corp Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine
FR2871847B1 (en) * 2004-06-17 2006-09-29 Snecma Moteurs Sa MOUNTING A TURBINE DISPENSER ON A COMBUSTION CHAMBER WITH CMC WALLS IN A GAS TURBINE
WO2006053825A1 (en) * 2004-11-16 2006-05-26 Alstom Technology Ltd Gas turbine system and associated combustion chamber
GB0601418D0 (en) * 2006-01-25 2006-03-08 Rolls Royce Plc Wall elements for gas turbine engine combustors
FR2922629B1 (en) * 2007-10-22 2009-12-25 Snecma COMBUSTION CHAMBER WITH OPTIMIZED DILUTION AND TURBOMACHINE WHILE MUNIED
US8127554B2 (en) * 2007-11-29 2012-03-06 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
US8616004B2 (en) * 2007-11-29 2013-12-31 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
WO2009083456A2 (en) * 2007-12-29 2009-07-09 Alstom Technology Ltd Gas turbine
FR2930591B1 (en) * 2008-04-24 2011-09-09 Snecma OPTIMIZING THE ANGULAR POSITIONING OF A TURBINE DISPENSER OUTSIDE A TURBOMACHINE COMBUSTION CHAMBER
US8276389B2 (en) * 2008-09-29 2012-10-02 Siemens Energy, Inc. Assembly for directing combustion gas
US8230688B2 (en) * 2008-09-29 2012-07-31 Siemens Energy, Inc. Modular transvane assembly
US8087253B2 (en) * 2008-11-20 2012-01-03 General Electric Company Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath
DE102010023816A1 (en) * 2010-06-15 2011-12-15 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustor assembly
DE102011108887A1 (en) 2011-07-28 2013-01-31 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine centripetal ring combustion chamber and method for flow guidance
EP2613080A1 (en) * 2012-01-05 2013-07-10 Siemens Aktiengesellschaft Combustion chamber of an annular combustor for a gas turbine
US9482432B2 (en) * 2012-09-26 2016-11-01 United Technologies Corporation Gas turbine engine combustor with integrated combustor vane having swirler
EP2767675A1 (en) 2013-02-15 2014-08-20 Siemens Aktiengesellschaft Through flow ventilation system for a power generation turbine package
US9322335B2 (en) 2013-03-15 2016-04-26 Siemens Energy, Inc. Gas turbine combustor exit piece with hinged connections
GB201505502D0 (en) * 2015-03-31 2015-05-13 Rolls Royce Plc Combustion equipment
EP3848556A1 (en) * 2020-01-13 2021-07-14 Ansaldo Energia Switzerland AG Gas turbine engine having a transition piece with inclined cooling holes

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2939563A1 (en) * 1978-10-02 1980-04-17 Gen Electric GAS TURBINE ENGINE
FR2438166A1 (en) * 1978-10-02 1980-04-30 Gen Electric IMPROVED GAS TURBINE ENGINE
EP0178242A1 (en) * 1984-10-11 1986-04-16 United Technologies Corporation Cooling scheme for combustor vane interface
US5235805A (en) * 1991-03-20 1993-08-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine engine combustion chamber with oxidizer intake flow control
GB2263733A (en) * 1992-01-28 1993-08-04 Snecma Turbomachine with removable combustion chamber.
GB2263733B (en) * 1992-01-28 1995-01-18 Snecma Turbomachine with removable combustion chamber

Also Published As

Publication number Publication date
US3608310A (en) 1971-09-28

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees