GB826961A - Liquid fuel combustion apparatus - Google Patents

Liquid fuel combustion apparatus

Info

Publication number
GB826961A
GB826961A GB740956A GB740956A GB826961A GB 826961 A GB826961 A GB 826961A GB 740956 A GB740956 A GB 740956A GB 740956 A GB740956 A GB 740956A GB 826961 A GB826961 A GB 826961A
Authority
GB
United Kingdom
Prior art keywords
air
combustion chamber
plate
chest
combustion
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
GB740956A
Inventor
George Roland Wade
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries Ltd
Joseph Lucas Industries Ltd
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 Lucas Industries Ltd, Joseph Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to GB740956A priority Critical patent/GB826961A/en
Publication of GB826961A publication Critical patent/GB826961A/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
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Abstract

826,961. Generating combustion products under pressure; combustion apparatus of furnaces. LUCAS (INDUSTRIES) Ltd., J. March 8, 1957 [March 9, 1956], No. 7409/56. Class 51 (1). In liquid fuel combustion apparatus in which air is supplied from an air chest disposed at the inlet end of the combustion chamber, an annular air guide is provided which divides the air flowing from the air chest through an air swirling device into the combustion chamber into three coaxial streams, the inner stream flowing around the fuel nozzle, the outer stream flowing towards the wall of the combustion chamber and the third stream flowing into the combustion chamber between the other two streams. The inlet end a of a combustion chamber has an air chest b secured thereto, the air chest being supplied by an air blower. A fuel nozzle d is mounted on the wall of the air chest and a transverse plate e is slidably mounted on the fuel nozzle, axial movement of the plate being caused by means of a screwed member f. Two circular members g are secured in axially-spaced relation on the plate e, the members g having radially-spaced extensions h which provide three coaxial air passages j, i, k into the combustion chamber. Swirl vanes c are provided at the entrance to the air guide, the plate e being notched at its periphery to accommodate the swirl vanes c. The amount of air entering the combustion chamber may be regulated by axial movement of the plate e. The combustion apparatus is suitable for use with jet propulsion engines, gas turbines, air or water heaters or industrial furnaces.
GB740956A 1956-03-09 1956-03-09 Liquid fuel combustion apparatus Expired GB826961A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB740956A GB826961A (en) 1956-03-09 1956-03-09 Liquid fuel combustion apparatus

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB740956A GB826961A (en) 1956-03-09 1956-03-09 Liquid fuel combustion apparatus

Publications (1)

Publication Number Publication Date
GB826961A true GB826961A (en) 1960-01-27

Family

ID=9832572

Family Applications (1)

Application Number Title Priority Date Filing Date
GB740956A Expired GB826961A (en) 1956-03-09 1956-03-09 Liquid fuel combustion apparatus

Country Status (1)

Country Link
GB (1) GB826961A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2479952A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp FUEL INJECTOR GUIDING AND SEALING STRUCTURE FOR A GAS TURBINE
GB2270974A (en) * 1992-08-29 1994-03-30 Mtu Muenchen Gmbh Burner for gas turbine engines
GB2270973A (en) * 1992-08-29 1994-03-30 Mtu Muenchen Gmbh Burner for gas turbine engines
FR2704305A1 (en) * 1993-04-21 1994-10-28 Snecma Combustion chamber comprising a variable-geometry injection system
FR2772890A1 (en) * 1997-12-19 1999-06-25 Alstom Gas Turbines Ltd AIR MIXTURE AND FUEL ASSEMBLY AND GAS TURBINE ENGINE COMPRISING SAME
US20120186259A1 (en) * 2011-01-26 2012-07-26 United Technologies Corporation Fuel injector assembly

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2479952A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp FUEL INJECTOR GUIDING AND SEALING STRUCTURE FOR A GAS TURBINE
GB2270974A (en) * 1992-08-29 1994-03-30 Mtu Muenchen Gmbh Burner for gas turbine engines
GB2270973A (en) * 1992-08-29 1994-03-30 Mtu Muenchen Gmbh Burner for gas turbine engines
GB2270973B (en) * 1992-08-29 1995-11-01 Mtu Muenchen Gmbh Burner for gas turbine engines
GB2270974B (en) * 1992-08-29 1995-11-22 Mtu Muenchen Gmbh Burner for gas turbine engines
FR2704305A1 (en) * 1993-04-21 1994-10-28 Snecma Combustion chamber comprising a variable-geometry injection system
FR2772890A1 (en) * 1997-12-19 1999-06-25 Alstom Gas Turbines Ltd AIR MIXTURE AND FUEL ASSEMBLY AND GAS TURBINE ENGINE COMPRISING SAME
US6311496B1 (en) 1997-12-19 2001-11-06 Alstom Gas Turbines Limited Gas turbine fuel/air mixing arrangement with outer and inner radial inflow swirlers
US20120186259A1 (en) * 2011-01-26 2012-07-26 United Technologies Corporation Fuel injector assembly
US10317081B2 (en) * 2011-01-26 2019-06-11 United Technologies Corporation Fuel injector assembly

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