GB537286A - A continuous combustion gas turbine system - Google Patents

A continuous combustion gas turbine system

Info

Publication number
GB537286A
GB537286A GB126140A GB126140A GB537286A GB 537286 A GB537286 A GB 537286A GB 126140 A GB126140 A GB 126140A GB 126140 A GB126140 A GB 126140A GB 537286 A GB537286 A GB 537286A
Authority
GB
United Kingdom
Prior art keywords
turbine
pipes
exit
passes
sub
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
GB126140A
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.)
HENRY ANDREWS HEPBURN
Original Assignee
HENRY ANDREWS HEPBURN
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 HENRY ANDREWS HEPBURN filed Critical HENRY ANDREWS HEPBURN
Priority to GB126140A priority Critical patent/GB537286A/en
Publication of GB537286A publication Critical patent/GB537286A/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
    • F02C3/36—Open cycles

Abstract

537,286. Gas turbines. HEPBURN, H. A. Jan. 20, 1940, No. 1261, [Class 110 (iii)] A gas turbine arranged for aircraft propulsion operates at a sub-atmospheric pressure. Air is compressed and passes by pipes 3, the jackets of turbine exit pipes 6 and pipes 9 to inlet valves 11 of combustion chambers 10. Fuel supplied by valves 14 is burnt in the chambers and the products of combustion under pressure pass to turbine nozzles 15 in which they are expanded to a sub-atmospheric pressure. The exhaust from the turbine passes through pipes 7 to an ejector pump 21 and the exit velocity is converted into pressure in the exit nozzles 23. The pump 21 may be driven, at a higher speed than the turbine, through epicyclic gearing 26. Cooling air passes along the bore 44 of the shaftinto the hollow turbine rotor around a dividing plate 45 and is discharged from the shaft at ports 47. Each combustion chamber comprises a shell 61, Fig. 7 and a refractory lining 60 and is slidingly fitted into a nozzle part 58.
GB126140A 1940-01-20 1940-01-20 A continuous combustion gas turbine system Expired GB537286A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB126140A GB537286A (en) 1940-01-20 1940-01-20 A continuous combustion gas turbine system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB126140A GB537286A (en) 1940-01-20 1940-01-20 A continuous combustion gas turbine system

Publications (1)

Publication Number Publication Date
GB537286A true GB537286A (en) 1941-06-16

Family

ID=9718889

Family Applications (1)

Application Number Title Priority Date Filing Date
GB126140A Expired GB537286A (en) 1940-01-20 1940-01-20 A continuous combustion gas turbine system

Country Status (1)

Country Link
GB (1) GB537286A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2583872A (en) * 1947-08-02 1952-01-29 United Aircraft Corp Gas turbine power plant, including planetary gearing between a compressor, turbine, and power consumer
US2637166A (en) * 1948-10-07 1953-05-05 James M Carswell Pure reaction turbine with evacuated chamber and rotor element therefor
US3009319A (en) * 1955-06-29 1961-11-21 Gregory D Filipenco Turbojet engine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2583872A (en) * 1947-08-02 1952-01-29 United Aircraft Corp Gas turbine power plant, including planetary gearing between a compressor, turbine, and power consumer
US2637166A (en) * 1948-10-07 1953-05-05 James M Carswell Pure reaction turbine with evacuated chamber and rotor element therefor
US3009319A (en) * 1955-06-29 1961-11-21 Gregory D Filipenco Turbojet engine

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