GB700672A - Improvements in or relating to gas turbines - Google Patents

Improvements in or relating to gas turbines

Info

Publication number
GB700672A
GB700672A GB2843/49A GB284349A GB700672A GB 700672 A GB700672 A GB 700672A GB 2843/49 A GB2843/49 A GB 2843/49A GB 284349 A GB284349 A GB 284349A GB 700672 A GB700672 A GB 700672A
Authority
GB
United Kingdom
Prior art keywords
blades
air
compressor
rotor
turbine
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
GB2843/49A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB2843/49A priority Critical patent/GB700672A/en
Publication of GB700672A publication Critical patent/GB700672A/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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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

700,672. Gas turbine plant; jet propulsion plant. ROSENGART, H. C. Feb. 2, 1949, No. 2843/49. Class 110 (3) In a gas turbine plant for the jet propulsion of aircraft or for other driving purposes comprising a rotor having blades 9 constituting an air compressor, blades 11 constituting the turbine, and an annular toroidal-shaped combustion chamber 5 disposed around the compressor-turbine rotor, the compressor blades and the turbine blades are hollow and in register so that cooling air may flow through the blades from the air inlet end 7 to the gas discharge end 8. The combustion chamber is shaped so that air and combustion gases are given a whirling motion both around the circular axis of the chamber and around the axis of the rotor. The fuel is discharged into the combustion chamber along the wall thereof through the nozzles 14 which receive fuel through the radial bores 13 in the rotor. An axial-flow compressor 18 is mounted on the rotor shaft and supplies air to the compressor 9. The gases discharge from the turbine into a ring of blades which impart axial flow thereto, and the gases draw in air through the inlet surrounding the combustion chamber, the air and gases passing into the jet propulsion nozzle 17.
GB2843/49A 1949-02-02 1949-02-02 Improvements in or relating to gas turbines Expired GB700672A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2843/49A GB700672A (en) 1949-02-02 1949-02-02 Improvements in or relating to gas turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2843/49A GB700672A (en) 1949-02-02 1949-02-02 Improvements in or relating to gas turbines

Publications (1)

Publication Number Publication Date
GB700672A true GB700672A (en) 1953-12-09

Family

ID=9747002

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2843/49A Expired GB700672A (en) 1949-02-02 1949-02-02 Improvements in or relating to gas turbines

Country Status (1)

Country Link
GB (1) GB700672A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1056428B (en) * 1953-06-09 1959-04-30 Laval Steam Turbine Company De Method for regulating an internal combustion engine with an exhaust gas turbocharger
DE1131947B (en) * 1959-03-28 1962-06-20 Maschf Augsburg Nuernberg Ag Combustion process for gas turbine combustion chambers and equipment for carrying out the process
DE1190734B (en) * 1963-09-12 1965-04-08 Sergio Simioni Combustion turbine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1056428B (en) * 1953-06-09 1959-04-30 Laval Steam Turbine Company De Method for regulating an internal combustion engine with an exhaust gas turbocharger
DE1131947B (en) * 1959-03-28 1962-06-20 Maschf Augsburg Nuernberg Ag Combustion process for gas turbine combustion chambers and equipment for carrying out the process
DE1190734B (en) * 1963-09-12 1965-04-08 Sergio Simioni Combustion turbine

Similar Documents

Publication Publication Date Title
GB1317992A (en) Gas turbine power plant
US3300121A (en) Axial-flow compressor
GB1113542A (en) Gas turbine engine
US4989404A (en) Turbine engine with high efficiency fuel atomization
GB609926A (en) Improvements in or relating to internal-combustion turbines
US5027603A (en) Turbine engine with start injector
GB695948A (en) Improvements in or relating to centrifugal gas compressors
GB935903A (en) Gas turbine power plant having centripetal flow compressors and centrifugal flow turbines
GB867849A (en) Improvements in or relating to axial flow compressors, and their applications
GB700672A (en) Improvements in or relating to gas turbines
GB891278A (en) A gas turbine power unit
GB795651A (en) Improvements in or relating to aircraft power plant installations incorporating gas-turbine engines
GB970188A (en) Gas turbine vertical lift engine
GB753561A (en) Axial flow dynamic compressors, and gas turbine power plants utilising such compressors
US2752753A (en) Air swirler surrounding fuel nozzle discharge end
GB733362A (en) Improvements in or relating to gas turbine engines
GB800602A (en) Improvements in or relating to jet propulsion gas turbine engines
FR2389772A1 (en) Jet engine for subsonic aircraft - has hollow rotor with internal blades to produce secondary stream of air within annular primary stream
GB737081A (en) Improvements relating to jet propulsion engines
GB620270A (en) Improvements in or relating to turbine apparatus
GB118650A (en) Improvements in Air or Gas Turbines.
RU2764941C1 (en) Turbojet engine
GB719479A (en) Improvements relating to gas turbine jet propulsion power units
GB814745A (en) An axial flow compressor
GB881816A (en) Improved gas turbine engine