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GB850691A - Improvements in or relating to aircraft engine nacelle structures - Google Patents

Improvements in or relating to aircraft engine nacelle structures

Info

Publication number
GB850691A
GB850691A GB15234/57A GB1523457A GB850691A GB 850691 A GB850691 A GB 850691A GB 15234/57 A GB15234/57 A GB 15234/57A GB 1523457 A GB1523457 A GB 1523457A GB 850691 A GB850691 A GB 850691A
Authority
GB
United Kingdom
Prior art keywords
tank
engine
lubricant
nacelle
jacks
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
GB15234/57A
Inventor
Edward John Pedlingham
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB15234/57A priority Critical patent/GB850691A/en
Publication of GB850691A publication Critical patent/GB850691A/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
    • 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
    • F02C7/047—Heating to prevent icing
    • 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)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

850,691. Cooling aircraft tanks. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. April 22, 1958 [May 14, 1957], No. 15234/57. Class 4. [Also in Group XXVI] An aircraft has an engine nacelle formed in two relatively movable parts, one of which forms or houses a tank for lubricant or other liquid, so that the cooling effect of the ambient air can be varied by relative displacement of the parts. The Figure shows a half axial section of the forward portion of a nacelle forming the air intake of a gas turbine engine. A fixed part 2b is hollow, forming an annular engine lubricant tank, and a part 2a is axially movable by three double acting circumferentially spaced hydraulic jacks 6 (one shown). With the jacks in the extended position shown, an annular duct 5 is formed between parts 2a and 2b, to permit ambient air flow into the engine compressor intake as shown by arrows C, raising the surface area of the tank over which heat exchange with the air may take place. The jacks may be retracted during normal flight, when the airflow outside the nacelle is sufficient to cool the lubricant, and extended during low speed flight. Hot de-icing gases are led to the part 2a through telescopic tubes (see Group XXVI), these tubes being thermally insulated to prevent heating of the tank or the cooling air.
GB15234/57A 1957-05-14 1957-05-14 Improvements in or relating to aircraft engine nacelle structures Expired GB850691A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB15234/57A GB850691A (en) 1957-05-14 1957-05-14 Improvements in or relating to aircraft engine nacelle structures

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB15234/57A GB850691A (en) 1957-05-14 1957-05-14 Improvements in or relating to aircraft engine nacelle structures

Publications (1)

Publication Number Publication Date
GB850691A true GB850691A (en) 1960-10-05

Family

ID=10055427

Family Applications (1)

Application Number Title Priority Date Filing Date
GB15234/57A Expired GB850691A (en) 1957-05-14 1957-05-14 Improvements in or relating to aircraft engine nacelle structures

Country Status (1)

Country Link
GB (1) GB850691A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2242234A (en) * 1990-02-23 1991-09-25 Gen Electric Variable contour inlet for an aircraft engine nacelle.
GB2274490A (en) * 1993-01-26 1994-07-27 Short Brothers Plc Nacelle for an aircraft propulsive power unit
FR2859500A1 (en) * 2003-09-05 2005-03-11 Gen Electric METHOD FOR ASSEMBLING A TURBINE ENGINE PREVENTING ICE ACCUMULATION IN THE ENGINE AND SYSTEM FOR PROTECTING AGAINST FREEZING
FR2887294A1 (en) * 2005-06-21 2006-12-22 Airbus France Sas Nose cowl`s leading edge de-icing system for aircraft, has hot air supply conduit with rear part connected to shroud`s rear part that is directly mounted to slide in cylindrical surface of bearing
DE102009055879A1 (en) * 2009-11-26 2011-06-01 Rolls-Royce Deutschland Ltd & Co Kg Aircraft deicing device and engine nacelle of an aircraft gas turbine with deicing device
US10221764B2 (en) 2014-08-19 2019-03-05 Pratt & Whitney Canada Corp. Variable geometry inlet system
US10443497B2 (en) 2016-08-10 2019-10-15 Rolls-Royce Corporation Ice protection system for gas turbine engines
FR3099796A1 (en) * 2019-08-06 2021-02-12 Safran Nacelles Air inlet of a turbomachine nacelle comprising a duct for circulating a flow of hot air between a moving upstream part and a fixed downstream part
CN113785114A (en) * 2019-04-03 2021-12-10 赛峰短舱公司 System for cooling an aircraft turbojet engine
FR3114844A1 (en) 2020-10-07 2022-04-08 Safran Nacelles Air inlet of a turbomachine nacelle comprising a pipe for the circulation of a flow of hot air between a mobile upstream part and a fixed downstream part

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2242234A (en) * 1990-02-23 1991-09-25 Gen Electric Variable contour inlet for an aircraft engine nacelle.
GB2274490A (en) * 1993-01-26 1994-07-27 Short Brothers Plc Nacelle for an aircraft propulsive power unit
GB2274490B (en) * 1993-01-26 1996-09-18 Short Brothers Plc An aircraft propulsive power unit
US5609313A (en) * 1993-01-26 1997-03-11 Short Brothers Plc Aircraft propulsive power unit
FR2859500A1 (en) * 2003-09-05 2005-03-11 Gen Electric METHOD FOR ASSEMBLING A TURBINE ENGINE PREVENTING ICE ACCUMULATION IN THE ENGINE AND SYSTEM FOR PROTECTING AGAINST FREEZING
US8308110B2 (en) 2005-06-21 2012-11-13 Airbus Operations Sas System for defrosting the leading edge sheath of an air inlet hood for a turboengine
FR2887294A1 (en) * 2005-06-21 2006-12-22 Airbus France Sas Nose cowl`s leading edge de-icing system for aircraft, has hot air supply conduit with rear part connected to shroud`s rear part that is directly mounted to slide in cylindrical surface of bearing
WO2006136680A1 (en) * 2005-06-21 2006-12-28 Airbus France System for defrosting the leading edge sheath of an air inlet hood for a tirboengine
CN100538047C (en) * 2005-06-21 2009-09-09 法国空中巴士公司 Be used to remove the system of frost of leading edge of the air intlet cover of turbogenerator
US8480032B2 (en) 2009-11-26 2013-07-09 Rolls-Royce Deutschland Ltd & Co Kg Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
DE102009055879A1 (en) * 2009-11-26 2011-06-01 Rolls-Royce Deutschland Ltd & Co Kg Aircraft deicing device and engine nacelle of an aircraft gas turbine with deicing device
US10221764B2 (en) 2014-08-19 2019-03-05 Pratt & Whitney Canada Corp. Variable geometry inlet system
US11066993B2 (en) 2014-08-19 2021-07-20 Pratt & Whitney Canada Corp. Variable geometry inlet system
US11661887B2 (en) 2014-08-19 2023-05-30 Pratt & Whitney Canada Corp. Variable geometry inlet system
US10443497B2 (en) 2016-08-10 2019-10-15 Rolls-Royce Corporation Ice protection system for gas turbine engines
CN113785114A (en) * 2019-04-03 2021-12-10 赛峰短舱公司 System for cooling an aircraft turbojet engine
FR3099796A1 (en) * 2019-08-06 2021-02-12 Safran Nacelles Air inlet of a turbomachine nacelle comprising a duct for circulating a flow of hot air between a moving upstream part and a fixed downstream part
FR3114844A1 (en) 2020-10-07 2022-04-08 Safran Nacelles Air inlet of a turbomachine nacelle comprising a pipe for the circulation of a flow of hot air between a mobile upstream part and a fixed downstream part
WO2022073891A1 (en) 2020-10-07 2022-04-14 Safran Nacelles Air intake of a turbine engine nacelle comprising a channel for circulating a flow of hot air between a movable upstream portion and a stationary downstream portion
US12044168B2 (en) 2020-10-07 2024-07-23 Safran Nacelles Air inlet of a turbomachine nacelle including a circulation conduit of a hot air flow between a movable upstream part and a fixed downstream part

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