GB1180929A - Combustion Apparatus, for example for Gas Turbines. - Google Patents

Combustion Apparatus, for example for Gas Turbines.

Info

Publication number
GB1180929A
GB1180929A GB08655/66A GB1865566A GB1180929A GB 1180929 A GB1180929 A GB 1180929A GB 08655/66 A GB08655/66 A GB 08655/66A GB 1865566 A GB1865566 A GB 1865566A GB 1180929 A GB1180929 A GB 1180929A
Authority
GB
United Kingdom
Prior art keywords
swirl vanes
tube
end wall
upstream
fuel
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
GB08655/66A
Inventor
Gordon Thomas Harding
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.)
English Electric Co Ltd
Original Assignee
English Electric 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 English Electric Co Ltd filed Critical English Electric Co Ltd
Priority to GB08655/66A priority Critical patent/GB1180929A/en
Priority to FR101912A priority patent/FR1518225A/en
Priority to CH502467A priority patent/CH457040A/en
Priority to DE19671601541 priority patent/DE1601541A1/en
Priority to NL6706048A priority patent/NL6706048A/xx
Priority to US634762A priority patent/US3451216A/en
Publication of GB1180929A publication Critical patent/GB1180929A/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
    • 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
    • F23C7/02—Disposition of air supply not passing through burner
    • 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
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)

Abstract

1,180,929. Gas turbine &c. combustion chambers. ENGLISH ELECTRIC CO. Ltd. April 26, 1967 [April 28, 1966], No.18655/66. Heading F1L. Combustion apparatus, e. g. for gas turbine engines, comprises a flame tube having an open downstream end and an end wall enclosing the upstream end, fuel injection means for injecting fuel into the tube near the upstream end, air inlet openings situated intermediate the ends of the tube, and means for directing the air flow from the openings initially in an upstream direction towards the closed end wall, the fuel injection means comprising fuel nozzles circumferentially spaced around the tube, each with an axial location intermediate the air inlet openings and the closed end wall, for delivering substantially the whole combustion fuel supply in the form of fuel sprays substantially radially into the tube, and the closed end wall being shaped to deflect the initial upstream air flow radially inwards whereby to return it centrally within the tube in a downstream direction. In Fig. 1, primary air enters the flame tube 12 through a row of swirl vanes 17 and is deflected as shown by a ring 21 carried by a partition 20, whereby it flows in an upstream direction over the faces of burners 23 before being reversed in direction by an end wall 13 so as to flow in the downstream direction in the region substantially in the centre of the flame tube. Combustion is facilitated by a recirculation of the burning gases as shown. Further air enters by way of rows of swirl vanes 18, 24 and is deflected in the downstream direction as shown. The rows of swirl vanes 17, 18 may be formed by continuous corrugated parts. In Fig. 4, the primary air passes axially through swirl vanes 27 connecting the upstream end 14 of the flame tube to a conical portion 42. Further air enters radially through swirl vanes 38, 24 and is deflected axially as shown by a ring 34 carried by a partition 33. The conical portion 42 may be replaced by a cylindrical portion (32, Fig. 3, not shown), the axial swirl vanes 27 then being replaced by radial swirl vanes (17). In Fig. 2 (not shown), in which the conical portion 42 is again replaced by a cylindrical portion (31), the further air enters in the downstream direction through axial swirl vanes (28, 34). In all constructions, the flame tube 12 and the outer casing 11 may be either cylindrical or annular.
GB08655/66A 1966-04-28 1966-04-28 Combustion Apparatus, for example for Gas Turbines. Expired GB1180929A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
GB08655/66A GB1180929A (en) 1966-04-28 1966-04-28 Combustion Apparatus, for example for Gas Turbines.
FR101912A FR1518225A (en) 1966-04-28 1967-04-07 combustion equipment, in particular for gas turbo-engines
CH502467A CH457040A (en) 1966-04-28 1967-04-10 Combustion chamber, especially for gas turbines
DE19671601541 DE1601541A1 (en) 1966-04-28 1967-04-20 Combustion device for gas turbine engines
NL6706048A NL6706048A (en) 1966-04-28 1967-04-28
US634762A US3451216A (en) 1966-04-28 1967-04-28 Combustion equipment

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB08655/66A GB1180929A (en) 1966-04-28 1966-04-28 Combustion Apparatus, for example for Gas Turbines.

Publications (1)

Publication Number Publication Date
GB1180929A true GB1180929A (en) 1970-02-11

Family

ID=10116187

Family Applications (1)

Application Number Title Priority Date Filing Date
GB08655/66A Expired GB1180929A (en) 1966-04-28 1966-04-28 Combustion Apparatus, for example for Gas Turbines.

Country Status (5)

Country Link
US (1) US3451216A (en)
CH (1) CH457040A (en)
DE (1) DE1601541A1 (en)
GB (1) GB1180929A (en)
NL (1) NL6706048A (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3648457A (en) * 1970-04-30 1972-03-14 Gen Electric Combustion apparatus
JPS5037445Y1 (en) * 1973-06-13 1975-10-31
DE2341904B2 (en) * 1973-08-18 1978-07-27 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Combustion chamber for gas turbine engines
JPS50111421A (en) * 1974-02-16 1975-09-02
US3974647A (en) * 1974-08-26 1976-08-17 United Technologies Corporation Combustion instability reduction device having swirling flow
FR2381911A1 (en) * 1977-02-25 1978-09-22 Guidas IMPROVED COMBUSTION CHAMBER ESPECIALLY FOR A GAS TURBINE
US4385490A (en) * 1978-08-14 1983-05-31 Phillips Petroleum Company Combustors and methods of operating same
US4498287A (en) * 1980-12-23 1985-02-12 Phillips Petroleum Company Combustors and methods of operating same
AU551776B2 (en) * 1981-03-17 1986-05-08 Trw Inc. Fuel combustor
US4702073A (en) * 1986-03-10 1987-10-27 Melconian Jerry O Variable residence time vortex combustor
DE19720786A1 (en) * 1997-05-17 1998-11-19 Abb Research Ltd Combustion chamber
US7168949B2 (en) * 2004-06-10 2007-01-30 Georgia Tech Research Center Stagnation point reverse flow combustor for a combustion system
EP2700879B1 (en) * 2012-08-24 2019-03-27 Ansaldo Energia Switzerland AG Method for mixing a dilution air in a sequential combustion system of a gas turbine, and sequential combustion system for a gas turbine comprising dilution air injector
US11835236B1 (en) * 2022-07-05 2023-12-05 General Electric Company Combustor with reverse dilution air introduction

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2930192A (en) * 1953-12-07 1960-03-29 Gen Electric Reverse vortex combustion chamber
US2907171A (en) * 1954-02-15 1959-10-06 Lysholm Alf Combustion chamber inlet for thermal power plants
US3064424A (en) * 1959-09-30 1962-11-20 Gen Motors Corp Flame tube
US3306333A (en) * 1964-03-31 1967-02-28 Bendix Corp Air spray combustor

Also Published As

Publication number Publication date
US3451216A (en) 1969-06-24
NL6706048A (en) 1967-10-30
CH457040A (en) 1968-05-31
DE1601541A1 (en) 1970-12-17

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