GB774704A - Improvements relating to combustion equipment for gas-turbine engines - Google Patents

Improvements relating to combustion equipment for gas-turbine engines

Info

Publication number
GB774704A
GB774704A GB2238354A GB2238354A GB774704A GB 774704 A GB774704 A GB 774704A GB 2238354 A GB2238354 A GB 2238354A GB 2238354 A GB2238354 A GB 2238354A GB 774704 A GB774704 A GB 774704A
Authority
GB
United Kingdom
Prior art keywords
tube
fuel
rings
annular
downstream
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
GB2238354A
Inventor
Francis Murray Johnson
Denis Richard Carlisle
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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
Priority claimed from GB1159352A external-priority patent/GB731609A/en
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB2238354A priority Critical patent/GB774704A/en
Publication of GB774704A publication Critical patent/GB774704A/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11001—Impinging-jet injectors or jet impinging on a surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Abstract

774,704. Spray burners. ROLLS-ROYCE Ltd. July 7, 1955 [July 30, 1954], No. 22383/54. Addition to 731,609. Class 75(1) [Also in Group XII] The combustion equipment of the parent Specification is modified by the addition of second fuel supply means arranged to introduce fuel into the air passage 25 extending through the fuel injector assembly in such manner that the additional fuel is. introduced directly into theflame tube 12 without contact with the spill lip of the assembly. The fuel injector 19, Fig. 1, produces an inner cone 23 and an outer cone 24 of atomized fuel, and is supported in a tube 17 defining the air passage 25 of the assembly so that the inner cone 23 clears the downstream end of the tube 17 to pass directly into the flame tube 12 and the outer cone 24 impinges on the inner surface of the tube 17 and flows over the spill lip formed at the downstream end thereof. A baffle plate 18 is mounted at the downstream end of the tube 17 by four radial arms 18a. The flame tube 12 is enclosed in a tubular air casing supplied' with air from the compressor. In a modification a plurality of flame tubes are enclosed in an annular air casing. In the embodiment shown in Fig. 3 the flame tube is annular and comprises inner and outer coaxial walls 33, 32 disposed within an annular air casing. Two coaxial fuel manifolds 43. 44 are mounted in an annular air passage 50 leading to the flame tube and formed by two rings 41, 42. The inner manifold 44 has discharge orifices forming two conical sheets 46, 47 of atomized fuel, clearing the downstream edges of the rings: 41, 42, the outer sheet 46 diverging and the inner sheet 47 converging in the direction of flow. The outer manifold 43 has discharge orifices producing two sprays of fuel which impinge on the rings 41, 42 and flow to spill lips formed by the downstream edges of the rings. An annular baffle ring 45 is supported at the downstream ends of the rings 41; 42 by lugs 45a. Specification 645,696 is referred to.
GB2238354A 1952-05-07 1954-07-30 Improvements relating to combustion equipment for gas-turbine engines Expired GB774704A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2238354A GB774704A (en) 1952-05-07 1954-07-30 Improvements relating to combustion equipment for gas-turbine engines

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1159352A GB731609A (en) 1952-05-07 1952-05-07 Improvements in or relating to combustion equipment for gas turbine engines
GB2238354A GB774704A (en) 1952-05-07 1954-07-30 Improvements relating to combustion equipment for gas-turbine engines

Publications (1)

Publication Number Publication Date
GB774704A true GB774704A (en) 1957-05-15

Family

ID=32910486

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2238354A Expired GB774704A (en) 1952-05-07 1954-07-30 Improvements relating to combustion equipment for gas-turbine engines

Country Status (1)

Country Link
GB (1) GB774704A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959003A (en) * 1957-06-20 1960-11-08 Rolls Royce Fuel burner
DE1097213B (en) * 1958-05-22 1961-01-12 Rolls Royce Incinerator for gas turbine engines
EP1001221A2 (en) * 1998-11-12 2000-05-17 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor cooling structure
EP1909031A1 (en) * 2006-10-06 2008-04-09 Snecma Fuel injector for the combustion chamber of a gas turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959003A (en) * 1957-06-20 1960-11-08 Rolls Royce Fuel burner
DE1097213B (en) * 1958-05-22 1961-01-12 Rolls Royce Incinerator for gas turbine engines
EP1001221A2 (en) * 1998-11-12 2000-05-17 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor cooling structure
EP1001221A3 (en) * 1998-11-12 2002-07-10 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor cooling structure
EP1909031A1 (en) * 2006-10-06 2008-04-09 Snecma Fuel injector for the combustion chamber of a gas turbine engine
FR2906868A1 (en) * 2006-10-06 2008-04-11 Snecma Sa FUEL INJECTOR FOR GAS TURBINE ENGINE COMBUSTION CHAMBER
US7849693B2 (en) 2006-10-06 2010-12-14 Snecma Fuel injector for a gas turbine engine combustion chamber

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