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GB627396A - Improvements in or relating to aircraft gas-turbine power-plant installations - Google Patents

Improvements in or relating to aircraft gas-turbine power-plant installations

Info

Publication number
GB627396A
GB627396A GB25107/47A GB2510747A GB627396A GB 627396 A GB627396 A GB 627396A GB 25107/47 A GB25107/47 A GB 25107/47A GB 2510747 A GB2510747 A GB 2510747A GB 627396 A GB627396 A GB 627396A
Authority
GB
United Kingdom
Prior art keywords
air
duct
exchanger
channel
annular
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
GB25107/47A
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.)
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 GB25107/47A priority Critical patent/GB627396A/en
Publication of GB627396A publication Critical patent/GB627396A/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
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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

627,396. Propelling aircraft. HAWORTH, L. Sept. 12, 1947, No. 25107. [Class 4] [Also in Group XXVI] A heat-exchanger 17, for cooling lubricating oil or liquid coolant, is located within the normal cowling 10. It receives cooling air from the main air-intake through an annular channel 23 and discharges it through a duct 26. The channel 23 leads to an annular chamber 28a surrounding the main-air duct, which may be of elliptical or volute shape and from that chamber the air passes to the heat-exchanger 17 through a circular duct 19 having a hosepipe connection 18 with the exchanger. The exchanger may be annular and surround the main air duct 16. The air-intake shown commences with the parts 12, 15 of an air screw spinner and the channel 23 is at the forward end of the stationary duct 16.
GB25107/47A 1947-09-12 1947-09-12 Improvements in or relating to aircraft gas-turbine power-plant installations Expired GB627396A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB25107/47A GB627396A (en) 1947-09-12 1947-09-12 Improvements in or relating to aircraft gas-turbine power-plant installations

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB25107/47A GB627396A (en) 1947-09-12 1947-09-12 Improvements in or relating to aircraft gas-turbine power-plant installations

Publications (1)

Publication Number Publication Date
GB627396A true GB627396A (en) 1949-08-08

Family

ID=10222330

Family Applications (1)

Application Number Title Priority Date Filing Date
GB25107/47A Expired GB627396A (en) 1947-09-12 1947-09-12 Improvements in or relating to aircraft gas-turbine power-plant installations

Country Status (1)

Country Link
GB (1) GB627396A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2503255A1 (en) * 1981-04-01 1982-10-08 United Technologies Corp COOLING DEVICE FOR AN ELECTRIC GENERATOR OF A GAS TURBINE ENGINE
US4782658A (en) * 1987-05-07 1988-11-08 Rolls-Royce Plc Deicing of a geared gas turbine engine
US4844689A (en) * 1986-07-04 1989-07-04 Rolls-Royce Plc Compressor and air bleed system
GB2251031A (en) * 1990-12-19 1992-06-24 Rolls Royce Plc Cooling air pick up for gas turbine engine
FR2958974A1 (en) * 2010-04-16 2011-10-21 Snecma Gas turbine engine e.g. turboshaft engine, for use in nacelle of aircraft, has exchanger fixed on intermediate wall connecting annular aerodynamic walls and longitudinal reinforcement connecting leading edge of lip with intermediate wall

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2503255A1 (en) * 1981-04-01 1982-10-08 United Technologies Corp COOLING DEVICE FOR AN ELECTRIC GENERATOR OF A GAS TURBINE ENGINE
US4474001A (en) * 1981-04-01 1984-10-02 United Technologies Corporation Cooling system for the electrical generator of a turbofan gas turbine engine
US4844689A (en) * 1986-07-04 1989-07-04 Rolls-Royce Plc Compressor and air bleed system
US4782658A (en) * 1987-05-07 1988-11-08 Rolls-Royce Plc Deicing of a geared gas turbine engine
GB2204361A (en) * 1987-05-07 1988-11-09 Rolls Royce Plc Deicing of a geared gas turbine engine
GB2204361B (en) * 1987-05-07 1991-10-16 Rolls Royce Plc Deicing of a geared gas turbine.
GB2251031A (en) * 1990-12-19 1992-06-24 Rolls Royce Plc Cooling air pick up for gas turbine engine
GB2251031B (en) * 1990-12-19 1995-01-18 Rolls Royce Plc Cooling air pick up
FR2958974A1 (en) * 2010-04-16 2011-10-21 Snecma Gas turbine engine e.g. turboshaft engine, for use in nacelle of aircraft, has exchanger fixed on intermediate wall connecting annular aerodynamic walls and longitudinal reinforcement connecting leading edge of lip with intermediate wall

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