GB644719A - Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamber - Google Patents

Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamber

Info

Publication number
GB644719A
GB644719A GB1328448A GB1328448A GB644719A GB 644719 A GB644719 A GB 644719A GB 1328448 A GB1328448 A GB 1328448A GB 1328448 A GB1328448 A GB 1328448A GB 644719 A GB644719 A GB 644719A
Authority
GB
United Kingdom
Prior art keywords
valve
flame tube
air
sleeve
casing
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
GB1328448A
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.)
Bataafsche Petroleum Maatschappij NV
Original Assignee
Bataafsche Petroleum Maatschappij NV
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 to NL644719X priority Critical
Application filed by Bataafsche Petroleum Maatschappij NV filed Critical Bataafsche Petroleum Maatschappij NV
Publication of GB644719A publication Critical patent/GB644719A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F02C3/305Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26Controlling the air flow

Abstract

644,719. Gas turbine plant. NAAMLOOZE VENNOOTSCHAP DE BATAAFSCHE PETROLEUM MAATSCHAPPIJ. May 14, 1948, No. 13284. Convention date, May 14, 1947. [Class 110(iii)] [Also in Group XII] To increase the output of a combustion chamber for a gas turbine plant of the kind in which an air stream is divided during normal operation into primary air which enters the combustion zone and secondary air which mixes with the combustion products leaving the combustion zone, means are provided to pass substantially the whole of said air stream into the combustion zone, to increase the fuel supply to the combustion zone and to add water or other volatile cooling,liquid in such quantity that the temperature of the mixture does not exceed that during normal operation. A combustion chamber for a jet propulsion gas turbine plant, Fig. 1, comprises an outer casing 4, a flame tube 5 and a fuel supply 12. A slide or sleeve valve 6 is arranged around the flame tube 5. In the normal position shown, Fig. 1, the air from the compressor 3 is divided, part flows into the combustion zone through passages near the burner and the remainder flows outside the flame tube to cool it and then passes through orifices 18 to mix with the combustion products. To increase the output of the combustion chamber the slide valve 6 is turned and the interconnecting pipes 24 which pass through helical slots 24<SP>1</SP> cause the valve to move rearwardly. This rearward movement of the valve shuts of the annular space between the flame tube 5 and casing 4 and all the air is forced to flow into the flame tube in the neighbourhood of the burner nozzle. Part of this air passes through orifices 14 which are shut off during normal operation by the ring 15 attached to the valve 6. The rotation of the valve 6 opens the orifices 6<SP>1</SP> and allows part of the combustion gases to pass to one or more jet pipes 9. A balancing piston 11 aids the rearward movement of the valve 6. Operation of the valve 6 is accompanied by an increase of the quantity of fuel supplied and the injection of water into the flame tube from pipes 19 and 20. A modification in which the air flows around the flame tube in the opposite direction to the flow of gases in the flame tube is described. In this arrangement the ports 18 are shut off by the rearward movement of the valve 6. In another modification, Fig. 9, a sleeve 25 is interposed between the flame tube 5 and casing 4. In normal operation, the annular space between this sleeve and the casing 4 is shut off by an annular valve 26 and the dilution air flows between the sleeve and flame tube 5 to the orifices 18. Rearward movement of the valve 6 opens the annular space between the sleeve 25 and casing 4, shuts off the annular space between the sleeve 25 and the flame tube 5 and closes the ports 18 causing part of the air to pass along the outside of the sleeve 25 and back along the outside of the flame tube to the inlet of the flame tube. The valve 6 may be actuated by a rod attached to the valve which engages a helical slot in the casing 4. The gases passing through the orifices 6<SP>1</SP> may actuate a turbine which is formed by the extension of the rotor and stator blades of the main turbine or a separate turbine surrounding the main turbine to the shaft of which it is attached by a one-way clutch. The main turbine may be in two parts, one of which drives an air compressor and the other an airscrew.
GB1328448A 1947-05-14 1948-05-14 Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamber Expired GB644719A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
NL644719X 1947-05-14

Publications (1)

Publication Number Publication Date
GB644719A true GB644719A (en) 1950-10-18

Family

ID=19791887

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1328448A Expired GB644719A (en) 1947-05-14 1948-05-14 Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamber

Country Status (1)

Country Link
GB (1) GB644719A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2847825A (en) * 1953-07-31 1958-08-19 Gen Motors Corp Gas turbine thrust augmenter comprising water injection ring
US2973624A (en) * 1955-10-26 1961-03-07 Gen Electric Cowled dome liners
US3038308A (en) * 1956-07-16 1962-06-12 Nancy W N Fuller Gas turbine combustion chamber and method
DE1153570B (en) * 1959-04-17 1963-08-29 Rolls Royce Combustor for gas turbine installations
DE1197280B (en) * 1960-02-25 1965-07-22 Rolls Royce convey smoke precipitation gas turbine engine
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
WO2000011323A1 (en) * 1998-08-21 2000-03-02 Alliedsignal Inc. Apparatus for water injection in a gas turbine combustor
EP1207344A2 (en) * 2000-11-17 2002-05-22 Mitsubishi Heavy Industries, Ltd. Combustor
JP2016145669A (en) * 2015-02-06 2016-08-12 三菱日立パワーシステムズ株式会社 Gas turbine combustor, and steam injection gas turbine

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2847825A (en) * 1953-07-31 1958-08-19 Gen Motors Corp Gas turbine thrust augmenter comprising water injection ring
US2973624A (en) * 1955-10-26 1961-03-07 Gen Electric Cowled dome liners
US3038308A (en) * 1956-07-16 1962-06-12 Nancy W N Fuller Gas turbine combustion chamber and method
DE1153570B (en) * 1959-04-17 1963-08-29 Rolls Royce Combustor for gas turbine installations
DE1197280B (en) * 1960-02-25 1965-07-22 Rolls Royce convey smoke precipitation gas turbine engine
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
US6112511A (en) * 1997-08-29 2000-09-05 Alliedsignal, Inc. Method and apparatus for water injection via primary jets
WO2000011323A1 (en) * 1998-08-21 2000-03-02 Alliedsignal Inc. Apparatus for water injection in a gas turbine combustor
EP1207344A2 (en) * 2000-11-17 2002-05-22 Mitsubishi Heavy Industries, Ltd. Combustor
EP1207344A3 (en) * 2000-11-17 2003-04-02 Mitsubishi Heavy Industries, Ltd. Combustor
US6662547B2 (en) 2000-11-17 2003-12-16 Mitsubishi Heavy Industries, Ltd. Combustor
JP2016145669A (en) * 2015-02-06 2016-08-12 三菱日立パワーシステムズ株式会社 Gas turbine combustor, and steam injection gas turbine

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