GB859713A - Improvements in or relating to combustion systems for gas turbine engines - Google Patents

Improvements in or relating to combustion systems for gas turbine engines

Info

Publication number
GB859713A
GB859713A GB1417958A GB1417958A GB859713A GB 859713 A GB859713 A GB 859713A GB 1417958 A GB1417958 A GB 1417958A GB 1417958 A GB1417958 A GB 1417958A GB 859713 A GB859713 A GB 859713A
Authority
GB
United Kingdom
Prior art keywords
valve
fuel
bleed
vapour
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
GB1417958A
Inventor
Martin Land
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB1417958A priority Critical patent/GB859713A/en
Publication of GB859713A publication Critical patent/GB859713A/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
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • 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
    • F02C7/232—Fuel valves; Draining valves or systems
    • 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

Abstract

859,713. Vapour burners. ROLLS-ROYCE Ltd. Feb. 27,1959 [May 3, 1958], No. 14179/58. Class 75(1). A combustion system for a gas turbine engine comprises a fuel injection nozzle and fuel conduit means for supplying the fuel injection nozzle with fuel, the fuel conduit means, incorporating a bleed valve which is open when fuel vapour is passing through the bleed valve so as to permit the escape of fuel vapour from the system and valve closure means which, when the fuel in its liquid state flows through the bleed valve, effects delayed closure thereof. A reheat system has a fuel tank 17, a pump 18, an adjustable valve 19 and manifold switch supplies fuel to three concentric pipes 25 to 27 each of which is connected to the casing 32 of the bleed valve supported'by a bracket 16 within a jet pipe 13. Any fuel which vaporizes in the pipes flows into the valve casing through an aperture 34 at one end of a sleeve 33 therein and out through the other end of the valve, the mushroom valve 35 being unseated from its seating 38 at all temperatures of fuel at and above vaporization temperature. When the valve closes the fuel discharges manually from the aperture in the concentric pipes. The valve stem 36 has a greater coefficient of expansion than that of the valve casing and sleeve. A small.bleed hole 39 is provided in the valve which remain open when the mushroom valve closes. The engine comprises combustion chambers 10, low and high pressure turbines 11, 12, a jet cone 14 and a jet pipe 13 with a nozzle 15. The bracket 16 supports three girders 25a to 27a.
GB1417958A 1958-05-03 1958-05-03 Improvements in or relating to combustion systems for gas turbine engines Expired GB859713A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1417958A GB859713A (en) 1958-05-03 1958-05-03 Improvements in or relating to combustion systems for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1417958A GB859713A (en) 1958-05-03 1958-05-03 Improvements in or relating to combustion systems for gas turbine engines

Publications (1)

Publication Number Publication Date
GB859713A true GB859713A (en) 1961-01-25

Family

ID=10036439

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1417958A Expired GB859713A (en) 1958-05-03 1958-05-03 Improvements in or relating to combustion systems for gas turbine engines

Country Status (1)

Country Link
GB (1) GB859713A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2402077A1 (en) * 1975-06-30 1979-03-30 Gen Electric MANEUVERABLE IN-FLIGHT EJECTION DEVICE FOR A GAS TURBINE ENGINE
US20160010564A1 (en) * 2013-03-14 2016-01-14 United Technologies Corporation Bleed valve assembly

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2402077A1 (en) * 1975-06-30 1979-03-30 Gen Electric MANEUVERABLE IN-FLIGHT EJECTION DEVICE FOR A GAS TURBINE ENGINE
US20160010564A1 (en) * 2013-03-14 2016-01-14 United Technologies Corporation Bleed valve assembly
US10132246B2 (en) * 2013-03-14 2018-11-20 United Technologies Corporation Bleed valve assembly

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