GB756264A - Improvements in thrust augmenting devices for aircraft gas turbine engines - Google Patents

Improvements in thrust augmenting devices for aircraft gas turbine engines

Info

Publication number
GB756264A
GB756264A GB21121/54A GB2112154A GB756264A GB 756264 A GB756264 A GB 756264A GB 21121/54 A GB21121/54 A GB 21121/54A GB 2112154 A GB2112154 A GB 2112154A GB 756264 A GB756264 A GB 756264A
Authority
GB
United Kingdom
Prior art keywords
manifold
gas turbine
aircraft gas
flame tube
outer 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
GB21121/54A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation Co
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 Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB756264A publication Critical patent/GB756264A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-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
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F02C3/305—Increasing 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

756,264. Generating combustion products under pressure. GENERAL MOTORS CORPORATION. July 20, 1954 [July 31, 1953], No. 21121/54. Class 51(1). In an aircraft gas turbine engine having a combustion chamber comprising an outer casing 22 and an inner flame tube 24, a ring, manifold 40 is disposed in the space between the outer casing and the flame tube and has apertures 42 in register with apertures 30 in the flame tube wall whereby evaporative coolant fluid such as water or water-alcohol may be injected into the flame tube so as to augment the thrust of the engine. Fluid is supplied from a manifold 36 through ducts 38 to each of a plurality of combustion chambers disposed in circular formation, the ducts 38 each connecting by a fitting 52 to a ring manifold 40. The manifold 40 is supported by means of two pins 44 projecting radially inwardly from the outer casing 22 which engage slidingly in 'sleeves 48 secured to the manifold so as to allow for expansion. The invention is applicable to aircraft gas turbine jet propulsion engines and to aircraft gas turbine propeller engines.
GB21121/54A 1953-07-31 1954-07-20 Improvements in thrust augmenting devices for aircraft gas turbine engines Expired GB756264A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US756264XA 1953-07-31 1953-07-31

Publications (1)

Publication Number Publication Date
GB756264A true GB756264A (en) 1956-09-05

Family

ID=22126997

Family Applications (1)

Application Number Title Priority Date Filing Date
GB21121/54A Expired GB756264A (en) 1953-07-31 1954-07-20 Improvements in thrust augmenting devices for aircraft gas turbine engines

Country Status (1)

Country Link
GB (1) GB756264A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3785146A (en) * 1972-05-01 1974-01-15 Gen Electric Self compensating flow divider for a gas turbine steam injection system
GB2119080A (en) * 1982-04-23 1983-11-09 Giavelli Mec Spa Burner having combustion air preheating

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3785146A (en) * 1972-05-01 1974-01-15 Gen Electric Self compensating flow divider for a gas turbine steam injection system
GB2119080A (en) * 1982-04-23 1983-11-09 Giavelli Mec Spa Burner having combustion air preheating

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