GB620270A - Improvements in or relating to turbine apparatus - Google Patents

Improvements in or relating to turbine apparatus

Info

Publication number
GB620270A
GB620270A GB1255/47A GB125547A GB620270A GB 620270 A GB620270 A GB 620270A GB 1255/47 A GB1255/47 A GB 1255/47A GB 125547 A GB125547 A GB 125547A GB 620270 A GB620270 A GB 620270A
Authority
GB
United Kingdom
Prior art keywords
annular
stream
turbine
combustion
chambers
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
GB1255/47A
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.)
Westinghouse Electric International Co
Original Assignee
Westinghouse Electric International 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 Westinghouse Electric International Co filed Critical Westinghouse Electric International Co
Publication of GB620270A publication Critical patent/GB620270A/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

620,270. Generating combustion products under pressure. WESTINGHOUSE ELECTRIC INTERNATIONAL CO. Jan. 14, 1947, No. 1255. Convention date, Nov. 20, 1945. [Class 51 (i)] [Also in Group XXVI] In a gas turbine plant having a straight through flow through axial flow compressor, combustion chambers, turbine and propulsion jet nozzle, the combustion chambers are annular, one within the other.' The chambers are located within a main annular airduct leading from the compressor diffuser 30 to the turbine nozzle passage 32 and are defined by four conical walls 35, 36, 37, 38. Each wall has perforations 49 of a size increasing from the up-stream end. The annular air spaces 29 are bridged at the up-stream end by a gauze screen 65. The up-stream ends of the annular flame tubes 31 are closed by radial annular plates 39 in which fuel nozzles 51 are mounted. The nozzles are fed from ring mains 53, 54 enclosed by stream-lined fairings. The up-stream end of the structure is strengthened by ribs 59. A gap is left between the combustion chamber at 42a and the shell 12 to provide a flow of air outside the part 43 of the combustion chamber. The turbine shaft is surrounded by inner and outer shells 27 between which supply pipes are located.
GB1255/47A 1945-11-20 1947-01-14 Improvements in or relating to turbine apparatus Expired GB620270A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US620270XA 1945-11-20 1945-11-20

Publications (1)

Publication Number Publication Date
GB620270A true GB620270A (en) 1949-03-22

Family

ID=22039749

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1255/47A Expired GB620270A (en) 1945-11-20 1947-01-14 Improvements in or relating to turbine apparatus

Country Status (1)

Country Link
GB (1) GB620270A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2674090A (en) * 1950-03-21 1954-04-06 United Aircraft Corp Combustion chamber for gas turbines
US2720080A (en) * 1952-02-01 1955-10-11 Rolls Royce Combustion equipment for gas-turbine engines with support means for supporting the flame tube from an air casing
US2996884A (en) * 1959-03-11 1961-08-22 Rolls Royce Combustion chamber
US3132483A (en) * 1960-04-25 1964-05-12 Rolls Royce Gas turbine engine combustion chamber
DE2412120A1 (en) * 1973-03-13 1974-09-19 Snecma ENVIRONMENTALLY FRIENDLY COMBUSTION CHAMBER FOR GAS TURBINES
FR2356000A1 (en) * 1976-06-21 1978-01-20 Gen Electric TURBOMACHINE COMBUSTION CHAMBER SUPPORT DEVICE

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2674090A (en) * 1950-03-21 1954-04-06 United Aircraft Corp Combustion chamber for gas turbines
US2720080A (en) * 1952-02-01 1955-10-11 Rolls Royce Combustion equipment for gas-turbine engines with support means for supporting the flame tube from an air casing
US2996884A (en) * 1959-03-11 1961-08-22 Rolls Royce Combustion chamber
US3132483A (en) * 1960-04-25 1964-05-12 Rolls Royce Gas turbine engine combustion chamber
DE2412120A1 (en) * 1973-03-13 1974-09-19 Snecma ENVIRONMENTALLY FRIENDLY COMBUSTION CHAMBER FOR GAS TURBINES
FR2356000A1 (en) * 1976-06-21 1978-01-20 Gen Electric TURBOMACHINE COMBUSTION CHAMBER SUPPORT DEVICE

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