GB1392783A - Reaction propulsion engine and method of operation - Google Patents

Reaction propulsion engine and method of operation

Info

Publication number
GB1392783A
GB1392783A GB582673A GB582673A GB1392783A GB 1392783 A GB1392783 A GB 1392783A GB 582673 A GB582673 A GB 582673A GB 582673 A GB582673 A GB 582673A GB 1392783 A GB1392783 A GB 1392783A
Authority
GB
United Kingdom
Prior art keywords
fuel
heat exchanger
stage
turbine
passed
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
GB582673A
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.)
Texaco Development Corp
Original Assignee
Texaco Development Corp
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 Texaco Development Corp filed Critical Texaco Development Corp
Priority to GB582673A priority Critical patent/GB1392783A/en
Publication of GB1392783A publication Critical patent/GB1392783A/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
    • 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
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • 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
    • F02C7/224—Heating fuel before feeding to the burner
    • 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)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

1392783 Jet propulsion engines TEXACO DEVELOPMENT CORP 6 Feb 1973 5826/73 Heading F1J The invention relates to a reaction propulsion engine suitable for operation from standstill to hypersonic speeds. The engine shown diagrammatically comprises a ram air intake 14 in which are disposed first and second heat exchanger stages 20, 26. Fuel from a tank 16 is passed by a pump to the first heat exchanger stage 20, the heated fuel then passing to a first stage turbine by-pass valve 3 and may then pass to a turbine temperature modulating valve 4, a mixer and then to a first turbine stage 24 which is connected to drive the fuel pump also an air compressor 22. The fuel discharging from the turbine is then passed to the second heat exchanger stage 26 where the fuel is again heated and then passes to a second stage turbine by-pass valve 6 from which the fuel may pass to the second turbine stage 28 which is also connected to drive the fuel pump and the air compressor 22, the fuel discharging from the turbine to the combustion chamber 10 where it burns with air from the compressor, the resulting combustion products discharging through a propulsion nozzle 12. The air from the ram air intake 14 after being cooled in the second and first heat exchanger stages passes to the compressor 22 and thence to the combustion chamber 10. At starting, a portion of fuel from the first heat exchanger 20 may be passed through a regenerative heat exchanger 30 disposed in the combustion chamber 10 whereby the fuel is heated and then passed to the mixer and thence to the first turbine stage 24. Fuel discharging from the first heat exchanger stage may be passed through a heat exchanger 32 associated with the air compressor whereby the fuel is further heated and the air in the compressor cooled; the fuel is then returned to the circuit. Fuel discharging from the first turbine stage 24 may also be passed through the heat exchanger 32 before being returned to the circuit. A portion of fuel from the first and second stage by-pass valves may be passed to thrust nozzles 12 or directly to the combustion chamber 10. Suitable fuels are hydrogen and hydrogen-bearing compounds such as ammonia, methyl alcohol, ethylene glycol and cyclohexane.
GB582673A 1973-02-06 1973-02-06 Reaction propulsion engine and method of operation Expired GB1392783A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB582673A GB1392783A (en) 1973-02-06 1973-02-06 Reaction propulsion engine and method of operation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB582673A GB1392783A (en) 1973-02-06 1973-02-06 Reaction propulsion engine and method of operation

Publications (1)

Publication Number Publication Date
GB1392783A true GB1392783A (en) 1975-04-30

Family

ID=9803332

Family Applications (1)

Application Number Title Priority Date Filing Date
GB582673A Expired GB1392783A (en) 1973-02-06 1973-02-06 Reaction propulsion engine and method of operation

Country Status (1)

Country Link
GB (1) GB1392783A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007095047A2 (en) * 2006-02-09 2007-08-23 Argo-Tech Corporation Regenerative pumping element start stage for high-speed centrifugal pump
US10907598B2 (en) 2018-03-07 2021-02-02 Eaton Intelligent Power Limited Self-limiting regenerative pumping element start stage for high speed centrifugal engine fuel pump and associated method
WO2021240107A1 (en) * 2020-05-28 2021-12-02 Safran Cryogenic fuel supply system for a turbine engine combustion chamber
WO2023281265A1 (en) 2021-07-09 2023-01-12 Reaction Engines Ltd Thermally integrated ammonia fuelled engine
FR3134848A1 (en) * 2022-04-26 2023-10-27 Safran Fuel conditioning system for supplying an aircraft turbomachine, method of supplying a turbomachine

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007095047A2 (en) * 2006-02-09 2007-08-23 Argo-Tech Corporation Regenerative pumping element start stage for high-speed centrifugal pump
WO2007095047A3 (en) * 2006-02-09 2008-12-11 Argo Tech Corp Regenerative pumping element start stage for high-speed centrifugal pump
US10907598B2 (en) 2018-03-07 2021-02-02 Eaton Intelligent Power Limited Self-limiting regenerative pumping element start stage for high speed centrifugal engine fuel pump and associated method
WO2021240107A1 (en) * 2020-05-28 2021-12-02 Safran Cryogenic fuel supply system for a turbine engine combustion chamber
FR3110935A1 (en) * 2020-05-28 2021-12-03 Safran Installation for supplying cryogenic fuel to the combustion chamber of a turbomachine.
US11920518B2 (en) 2020-05-28 2024-03-05 Safran Cryogenic fuel supply system for a turbine engine combustion chamber
WO2023281265A1 (en) 2021-07-09 2023-01-12 Reaction Engines Ltd Thermally integrated ammonia fuelled engine
FR3134848A1 (en) * 2022-04-26 2023-10-27 Safran Fuel conditioning system for supplying an aircraft turbomachine, method of supplying a turbomachine
WO2023208884A1 (en) * 2022-04-26 2023-11-02 Safran Fuel conditioning system for supplying an aircraft turbine engine, and method of supplying a turbine engine

Similar Documents

Publication Publication Date Title
US2585626A (en) Turbine mechanism for driving the fuel pumps of rockets
US3747339A (en) Reaction propulsion engine and method of operation
US2586025A (en) Jet reaction engine of the turbine type
GB749176A (en) Improvements relating to jet propulsion apparatus
US2689454A (en) Rocket engine
US3740949A (en) Fuel cooled ram air reaction propulsion engine
GB1451207A (en) Gas turbine plant
GB793689A (en) Rocket motors
US3690100A (en) Method of operating a reaction propulsion engine and fuels therefor
US4092824A (en) Method of operating a turbine
AU721864B2 (en) Drive arrangement and method of reducing the amount of NOx in the exhaust gases from an internal combustion engine
GB1390919A (en) Lasers
GB196452A (en) Improvements in or relating to internal combustion turbine engines
GB1392783A (en) Reaction propulsion engine and method of operation
GB702779A (en) Means for supplying propellents to a rocket motor
GB1138165A (en) Improvements in or relating to a gas turbine plant
GB853495A (en) Improvements in or relating to liquid propellent rocket motors
US2775866A (en) Starters for prime movers such as gas turbines
US2641904A (en) Apparatus for cooling combustion chambers of movable power plants with an oxidizing agent
GB876186A (en) High output power plant, for example, rocket engines
GB1392781A (en) Reaction propulsion engine and method of operation
GB1329803A (en) Gas generator and method of operation
GB1392782A (en) Reaction propulsion engine and method of operation
GB744923A (en) Improvements relating to gas turbine engines
US3722220A (en) Reaction propulsion engine and method of operation

Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee