GB626174A - Improvements relating to combustion turbines - Google Patents

Improvements relating to combustion turbines

Info

Publication number
GB626174A
GB626174A GB12640/47A GB1264047A GB626174A GB 626174 A GB626174 A GB 626174A GB 12640/47 A GB12640/47 A GB 12640/47A GB 1264047 A GB1264047 A GB 1264047A GB 626174 A GB626174 A GB 626174A
Authority
GB
United Kingdom
Prior art keywords
stage
fuel
compressor
meker
grates
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
GB12640/47A
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.)
Bataafsche Petroleum Maatschappij NV
Original Assignee
Bataafsche Petroleum Maatschappij NV
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 Bataafsche Petroleum Maatschappij NV filed Critical Bataafsche Petroleum Maatschappij NV
Publication of GB626174A publication Critical patent/GB626174A/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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • 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
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • 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
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • 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
    • F02C7/236—Fuel delivery systems comprising two or more pumps
    • F02C7/2365—Fuel delivery systems comprising two or more pumps comprising an air supply system for the atomisation of fuel
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

626,174. Generating combustion products under pressure. NAAMLOOZE VENNOOTSCHAP DE BATAAFSCHE PETROLEUM MAATSCHAPPIJ. May 9, 1947, No. 12640. Convention date, March 15, 1946. [Class 51(i)] [Also in Group XXVI] In a gas turbine plant for jet-propulsion the combustion air is mixed with the fuel before compression or before the last stage of compression. In Fig. 1, the fuel is sprayed at 2 before the inlet of the compressor 1 and the compressed mixture passes through meker grates 5 which prevent flash-back. Secondary air is passed through a compressor 8 which delivers to chambers 3 around the flame tubes 4. In Fig. 2, part of the delivery of a first axial flow compressor stage 8 is led by pipes 11 to a second axial flow stage 1 and fuel is injected at 2 before the second stage. The mixture passes through meker grates 5 to an annular combustion chamber. The other part of the delivery of stage 8 passes to a second stage 13 and enters the combustion chamber from a surrounding chamber 12 through radial slots.
GB12640/47A 1946-03-15 1947-05-09 Improvements relating to combustion turbines Expired GB626174A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
NL626174X 1946-03-15

Publications (1)

Publication Number Publication Date
GB626174A true GB626174A (en) 1949-07-11

Family

ID=19788578

Family Applications (1)

Application Number Title Priority Date Filing Date
GB12640/47A Expired GB626174A (en) 1946-03-15 1947-05-09 Improvements relating to combustion turbines

Country Status (1)

Country Link
GB (1) GB626174A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2671314A (en) * 1950-01-26 1954-03-09 Socony Vacuum Oil Co Inc Gas turbine and method of operation therefor
US2825205A (en) * 1953-07-15 1958-03-04 Snecma Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft
US3475907A (en) * 1967-04-27 1969-11-04 Cav Ltd Gas turbine with lubricant and fuel supply systems therefor
US3486338A (en) * 1959-04-16 1969-12-30 Hans K Haussmann Air breathing missile

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2671314A (en) * 1950-01-26 1954-03-09 Socony Vacuum Oil Co Inc Gas turbine and method of operation therefor
US2825205A (en) * 1953-07-15 1958-03-04 Snecma Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft
US3486338A (en) * 1959-04-16 1969-12-30 Hans K Haussmann Air breathing missile
US3475907A (en) * 1967-04-27 1969-11-04 Cav Ltd Gas turbine with lubricant and fuel supply systems therefor

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