GB672530A - Improvements in gas turbine combustion chambers - Google Patents

Improvements in gas turbine combustion chambers

Info

Publication number
GB672530A
GB672530A GB2030950A GB2030950A GB672530A GB 672530 A GB672530 A GB 672530A GB 2030950 A GB2030950 A GB 2030950A GB 2030950 A GB2030950 A GB 2030950A GB 672530 A GB672530 A GB 672530A
Authority
GB
United Kingdom
Prior art keywords
swirler
shroud
hub
vanes
ports
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
GB2030950A
Inventor
Leslie George Blyther
Harold Rowling
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.)
Shell Refining and Marketing Co Ltd
Original Assignee
Shell Refining and Marketing Co 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 Shell Refining and Marketing Co Ltd filed Critical Shell Refining and Marketing Co Ltd
Priority to GB2030950A priority Critical patent/GB672530A/en
Publication of GB672530A publication Critical patent/GB672530A/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
    • 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
    • F23C7/008—Flow control devices

Abstract

672,530. Generating combustion products under pressure. SHELL REFINING & MARKETING CO., Ltd. Aug. 16, 1950, No. 20309/50. Class 51 (i). [Also in Group XI] A gas turbine combustion chamber comprises a multi-vaned air swirler 1, 2 and a shutter device having the form of a set of sectoral vanes 4 equal in number to the vanes 1 of the swirler, the air swirler and shutter device being capable of rotation relatively to each other so as to vary the areas of the outlet orifices of the swirler, and means are provided for causing the relative rotation. Each swirler vane 1 has a baffle plate fixed thereto of the same form as the corresponding shutter vane and lies against it. A shroud 8 having ports 19 is disposed around the burner 7 and carries pegs 11 which engage in helical slots 10 in the hub 2 of the air swirler so that axial movement of the shroud 8 by means of the sleeve 9 causes the hub 2 and swirler vanes 1 to rotate relatively to the fixed shutter device 4. Axial movement of the shroud 8 also varies the quantity of air admitted by the shroud by varying the space between the shroud and the burner tip and by varying the area of the ports 19 in the shroud uncovered by the ports 21 in the swirler hub 2. The control means may be actuated manually or automatically in dependence on the rate at which fuel is supplied to the burner.
GB2030950A 1950-08-16 1950-08-16 Improvements in gas turbine combustion chambers Expired GB672530A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2030950A GB672530A (en) 1950-08-16 1950-08-16 Improvements in gas turbine combustion chambers

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2030950A GB672530A (en) 1950-08-16 1950-08-16 Improvements in gas turbine combustion chambers

Publications (1)

Publication Number Publication Date
GB672530A true GB672530A (en) 1952-05-21

Family

ID=10143840

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2030950A Expired GB672530A (en) 1950-08-16 1950-08-16 Improvements in gas turbine combustion chambers

Country Status (1)

Country Link
GB (1) GB672530A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1265497B (en) * 1962-07-24 1968-04-04 Prvni Brnenska Strojirna Control device for the combustion chamber of gas turbines
US4497170A (en) * 1982-07-22 1985-02-05 The Garrett Corporation Actuation system for a variable geometry combustor
FR2572463A1 (en) * 1984-10-30 1986-05-02 Snecma INJECTION SYSTEM WITH VARIABLE GEOMETRY.
US4754600A (en) * 1986-03-20 1988-07-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Axial-centripetal swirler injection apparatus

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1265497B (en) * 1962-07-24 1968-04-04 Prvni Brnenska Strojirna Control device for the combustion chamber of gas turbines
US4497170A (en) * 1982-07-22 1985-02-05 The Garrett Corporation Actuation system for a variable geometry combustor
FR2572463A1 (en) * 1984-10-30 1986-05-02 Snecma INJECTION SYSTEM WITH VARIABLE GEOMETRY.
EP0182687A1 (en) * 1984-10-30 1986-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Injection system with a variable geometry
US4726182A (en) * 1984-10-30 1988-02-23 501 Societe Nationale d'Etude et de Construction de Meteur d'Aviation-S.N.E.C.M.A. Variable flow air-fuel mixing device for a turbojet engine
US4754600A (en) * 1986-03-20 1988-07-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Axial-centripetal swirler injection apparatus

Similar Documents

Publication Publication Date Title
GB958842A (en) Ducted fan lift engine
GB721126A (en) Improvements in or relating to gas burners
GB639617A (en) Improvements in and relating to combustion chambers
GB686908A (en) Improvements in or relating to combustion apparatus for a gas turbine unit
GB650462A (en) Improvements in or relating to combustion apparatus
GB947873A (en) An annular combustion chamber for gas turbines
GB616695A (en) Improvements in and relating to gas turbine power plants
GB672530A (en) Improvements in gas turbine combustion chambers
GB891278A (en) A gas turbine power unit
JPS5546309A (en) Burner for gas turbine
GB578764A (en) Improvements relating to combustion chambers for internal combustion turbines
GB694448A (en) Improvements in or relating to gas-turbine engines
GB870988A (en) Improvements in or relating to a liquid fuel atomiser
GB931105A (en) Improvements in combustion apparatus
GB699267A (en) Improvements in or relating to combustion turbine units
GB619353A (en) Liquid-fuel combustion chamber
GB820337A (en) Improvements in and relating to gas turbines
GB737081A (en) Improvements relating to jet propulsion engines
GB637223A (en) Improvements in and relating to combustion units particularly for use in gas turbinesystems
GB252424A (en) An improved water turbine
GB706841A (en) Improvements relating to turbine jet propulsion power units
GB791917A (en) Improvements in and relating to gas turbine plants
GB723413A (en) Improvements in combustion chambers for gas turbines, jet propulsion plants and the like
GB901199A (en) Gas turbine
GB595644A (en) Improvements in liquid fuel burners suitable for gas-turbines