GB632506A - Improvements in or relating to fuel-injection nozzles and gas-turbine fuel-systems - Google Patents

Improvements in or relating to fuel-injection nozzles and gas-turbine fuel-systems

Info

Publication number
GB632506A
GB632506A GB3428946A GB3428946A GB632506A GB 632506 A GB632506 A GB 632506A GB 3428946 A GB3428946 A GB 3428946A GB 3428946 A GB3428946 A GB 3428946A GB 632506 A GB632506 A GB 632506A
Authority
GB
United Kingdom
Prior art keywords
fuel
air
orifice
chamber
nozzle
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
GB3428946A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB3428946A priority Critical patent/GB632506A/en
Publication of GB632506A publication Critical patent/GB632506A/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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/236—Fuel delivery systems comprising two or more pumps
    • F02C7/2365—Fuel delivery systems comprising two or more pumps comprising an air supply system for the atomisation of fuel
    • 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
    • F23D11/101—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 before the burner outlet
    • F23D11/102—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 before the burner outlet in an internal mixing chamber
    • F23D11/103—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 before the burner outlet in an internal mixing chamber with means creating a swirl inside the mixing chamber

Abstract

632,506. Liquid - f u e l burners. CARLISLE, D. R. Nov. 19, 1946, No. 34289. [Class 75(i)] A fuel-injection nozzle for use in a gas turbine fuel system comprises a mixing chamber into which fuel and compressed air can be delivered, an atomising orifice through which the air and fuel are ejected from the chamber into a combustion space, and a baffle so arranged in a fixed location with respect to the orifice on the side thereof remote from the chamber as to ensure more complete mixing of the air and fuel. Fuel and air are supplied through connections 11, 12, respectively, to ducts 13, 14 in the nozzle body 10. The fuel passes through ports 19 in a spacer plate 16 and through swirling slots 20 in a plate 17, whilst the air passes through a chamber 22 to be swirled in helical grooves on the surface of a spring-pressed frustoconical plug 23 and impinges upon the fuel leaving the slots 20. The fuel air mixture leaves the nozzle through a tapering orifice 26 in the end plate 18 and impinges upon a baffle 27 carried by a stem 28 projecting from the plug 23. The baffle 27 has a diameter slightly less than the minimum diameter of the orifice 26 so that the plate 18 may be passed over it. The nozzle may be employed in a fuel system as described in Specification 618,479. Specification 632,507 also is referred to.
GB3428946A 1946-11-19 1946-11-19 Improvements in or relating to fuel-injection nozzles and gas-turbine fuel-systems Expired GB632506A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3428946A GB632506A (en) 1946-11-19 1946-11-19 Improvements in or relating to fuel-injection nozzles and gas-turbine fuel-systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3428946A GB632506A (en) 1946-11-19 1946-11-19 Improvements in or relating to fuel-injection nozzles and gas-turbine fuel-systems

Publications (1)

Publication Number Publication Date
GB632506A true GB632506A (en) 1949-11-28

Family

ID=10363774

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3428946A Expired GB632506A (en) 1946-11-19 1946-11-19 Improvements in or relating to fuel-injection nozzles and gas-turbine fuel-systems

Country Status (1)

Country Link
GB (1) GB632506A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20100942A1 (en) * 2010-05-26 2011-11-27 Ansaldo Energia Spa BURNER UNIT FOR A COMBUSTION CHAMBER OF A GAS TURBINE SYSTEM, COMBUSTION CHAMBER INCLUDING THE BURNER GROUP AND METHOD TO OPERATE THE BURNER GROUP

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20100942A1 (en) * 2010-05-26 2011-11-27 Ansaldo Energia Spa BURNER UNIT FOR A COMBUSTION CHAMBER OF A GAS TURBINE SYSTEM, COMBUSTION CHAMBER INCLUDING THE BURNER GROUP AND METHOD TO OPERATE THE BURNER GROUP

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