GB750200A - Improvements relating to ducted-fan, turbo-jet engines - Google Patents

Improvements relating to ducted-fan, turbo-jet engines

Info

Publication number
GB750200A
GB750200A GB36140/53A GB3614053A GB750200A GB 750200 A GB750200 A GB 750200A GB 36140/53 A GB36140/53 A GB 36140/53A GB 3614053 A GB3614053 A GB 3614053A GB 750200 A GB750200 A GB 750200A
Authority
GB
United Kingdom
Prior art keywords
header
fan
unit
turbo
oil
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
GB36140/53A
Inventor
Horace Sinclair Rainbow
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.)
Armstrong Siddeley Motors Ltd
Original Assignee
Armstrong Siddeley Motors Ltd
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 Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
Priority to GB36140/53A priority Critical patent/GB750200A/en
Publication of GB750200A publication Critical patent/GB750200A/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
    • 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)
  • Jet Pumps And Other Pumps (AREA)

Abstract

750,200. Lubricating. ARMSTRONG SIDDELEY MOTORS, Ltd. Nov. 16, 1954 [Dec. 30, 1953], No. 36140/53. Class 12 (3). [Also in Group XXVI] Relates to a turbo-jet engine having a multistage ducted fan 17 driven through reduction gearing and delivering air directly to the compressor 22 and to the jet. According to the invention an intermediate stage of the fan communicates with a surrounding annular passage 35 enlarged at one part to form a collecting chamber 34 having an open side connected to a heat exchanger unit 32 for cooling the oil used in the reduction gearing, means being provided for controlling the air flow through the unit. The oil is drawn from a tank 27 and delivered by a pump 28 to bearing 29. It returns to a collecting chamber 30 and from thence is delivered by a scavenge pump 31 to a header of unit 32. From the header the oil flows over the tubes 40, through which the air passes, to a second header connected to tank 27. The air flow is controllable by a valve 45. The casing 41 of the heat exchanger is stiffened by channel sections members 47.
GB36140/53A 1953-12-30 1953-12-30 Improvements relating to ducted-fan, turbo-jet engines Expired GB750200A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB36140/53A GB750200A (en) 1953-12-30 1953-12-30 Improvements relating to ducted-fan, turbo-jet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB36140/53A GB750200A (en) 1953-12-30 1953-12-30 Improvements relating to ducted-fan, turbo-jet engines

Publications (1)

Publication Number Publication Date
GB750200A true GB750200A (en) 1956-06-13

Family

ID=10385358

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36140/53A Expired GB750200A (en) 1953-12-30 1953-12-30 Improvements relating to ducted-fan, turbo-jet engines

Country Status (1)

Country Link
GB (1) GB750200A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0298011A1 (en) * 1987-06-29 1989-01-04 United Technologies Corporation Nose cowl mounted oil lubricating and cooling system
FR2635824A1 (en) * 1988-08-25 1990-03-02 Mtu Muenchen Gmbh GAS TURBOMOTEUR TURBOMOTOR DRIVEN BY A ROTORS REDUCER WITH PROPELLERS OR BLOWER ROTORS
EP1876328A2 (en) 2006-07-06 2008-01-09 United Technologies Corporation Heat exchange system in a turbofan engine
EP1944475A2 (en) 2007-01-08 2008-07-16 Pratt & Whitney Rocketdyne Inc. Heat exchange system
FR2946089A1 (en) * 2009-05-27 2010-12-03 Airbus France FLUID COOLING DEVICE FOR TURBOMACHINE PROPELLER
CN102135035A (en) * 2010-01-26 2011-07-27 空中客车营运有限公司 Aircraft propulsion unit with a cooler installed at engine nacelle
CN111895259A (en) * 2020-07-10 2020-11-06 中国航发湖南动力机械研究所 Integrated oil storage tank

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0298011A1 (en) * 1987-06-29 1989-01-04 United Technologies Corporation Nose cowl mounted oil lubricating and cooling system
FR2635824A1 (en) * 1988-08-25 1990-03-02 Mtu Muenchen Gmbh GAS TURBOMOTEUR TURBOMOTOR DRIVEN BY A ROTORS REDUCER WITH PROPELLERS OR BLOWER ROTORS
US4999994A (en) * 1988-08-25 1991-03-19 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Turbo engine
EP1876328A2 (en) 2006-07-06 2008-01-09 United Technologies Corporation Heat exchange system in a turbofan engine
EP1876328A3 (en) * 2006-07-06 2010-11-03 United Technologies Corporation Heat exchange system in a turbofan engine
US8161726B2 (en) 2006-07-06 2012-04-24 United Technologies Corporation Cooling exchanger duct
EP1944475A2 (en) 2007-01-08 2008-07-16 Pratt & Whitney Rocketdyne Inc. Heat exchange system
EP1944475A3 (en) * 2007-01-08 2010-11-03 United Technologies Corporation Heat exchange system
WO2010136710A3 (en) * 2009-05-27 2011-04-14 Airbus Operations (S.A.S) Fluid-cooling device for a turbine engine propulsive unit
FR2946089A1 (en) * 2009-05-27 2010-12-03 Airbus France FLUID COOLING DEVICE FOR TURBOMACHINE PROPELLER
CN102695862A (en) * 2009-05-27 2012-09-26 空中客车营运有限公司 Fluid-cooling device for a turbine engine propulsive unit
CN102695862B (en) * 2009-05-27 2014-12-03 空中客车营运有限公司 Fluid-cooling device for a turbine engine propulsive unit
US9175695B2 (en) 2009-05-27 2015-11-03 Airbus Operations S.A.S. Fluid-cooling device for a turbine engine propulsive unit
CN102135035A (en) * 2010-01-26 2011-07-27 空中客车营运有限公司 Aircraft propulsion unit with a cooler installed at engine nacelle
CN111895259A (en) * 2020-07-10 2020-11-06 中国航发湖南动力机械研究所 Integrated oil storage tank
CN111895259B (en) * 2020-07-10 2021-11-12 中国航发湖南动力机械研究所 Integrated oil storage tank

Similar Documents

Publication Publication Date Title
US2435990A (en) Gas turbine lubricating oil cooling and air inlet deicing system
GB1244340A (en) Front fan gas turbine engine
GB790836A (en) Improvements in or relating to gas-turbine engine cooling arrangements
GB754856A (en) Improvements relating to the air cooling of gas turbines
US3080728A (en) Aircraft air conditioning systems
GB750200A (en) Improvements relating to ducted-fan, turbo-jet engines
GB709210A (en) Improvements in gas turbine engines
US2485590A (en) Cooling system for compartments using expansion engine means
GB713783A (en) Gas turbine propulsion units
US2328489A (en) Devices for controlling the pressure and temperature in altitude cabins, particularly for airplanes
US3083532A (en) Gas turbine engine with air-cooling means and means to control the temperature of cooling air by liquid injection
US2642155A (en) Lubrication apparatus
GB839344A (en) Improvements in or relating to gas-turbine engines
GB578306A (en) Improvements in an exhaust turbosupercharger
GB538022A (en) Improvements in the propulsion of aircraft
GB1018538A (en) Gas turbine engine
GB881967A (en) Improved propulsion unit for use in vertical take-off aircraft
GB685942A (en) Improvements relating to the jet propulsion of vehicles
GB629044A (en) Improvements in or relating to compressors, particularly for use with aircraft powerplants
GB736503A (en) Improvements relating to gas-turbine engines
GB763449A (en) Improvements relating to gas turbine engine fuel systems
GB630792A (en) Improvements in or relating to the cooling of the bearings of turbo-machinery as used in aircraft
DE701457C (en) Device for generating energy from the exhaust gases of internal combustion engines
GB831770A (en) Compressor-turbine unit
GB416463A (en) Improvements in constant pressure gas turbine plant