GB1018538A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB1018538A
GB1018538A GB27839/64A GB2783964A GB1018538A GB 1018538 A GB1018538 A GB 1018538A GB 27839/64 A GB27839/64 A GB 27839/64A GB 2783964 A GB2783964 A GB 2783964A GB 1018538 A GB1018538 A GB 1018538A
Authority
GB
United Kingdom
Prior art keywords
turbine
shaft
lubricant
bearings
duct
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
GB27839/64A
Inventor
James Alexander Petrie
Kenneth Edward Bracey
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB27839/64A priority Critical patent/GB1018538A/en
Priority to FR20071A priority patent/FR1438694A/en
Priority to DER40917A priority patent/DE1300349B/en
Publication of GB1018538A publication Critical patent/GB1018538A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
    • B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
    • 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
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • 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
    • 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
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/062—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with aft fan
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Rolling Contact Bearings (AREA)

Abstract

1,018,538. Lubricating. ROLLS-ROYCE Ltd. July 6, 1964, No. 27839/64. Heading F2A. [Also in Division F1] In a lubrication and cooling system for a gas turbine engine, lubricant is pumped through bearings, is returned to a reservoir via a cooler, and is sprayed on to an air-intake member so as to prevent the formation of ice thereon. In an embodiment, a gas turbine 10 has a casing 12 having an airintake 13 and has a shaft 14 mounted in bearings 24, 27 and 32, the shaft 14 having a compressor 15 and a turbine 16 mounted thereon. The compressed air passes into a combustion chamber 22 which is supplied with fuel from a pipe 35, via a duct 33 which is mounted within the shaft 14 and via an annual member 37 which is connected by radial passes therein to the duct 33 and the chamber 22. The combustion gases pass to the turbine 16 which is driven in an opposite direction to that of a turbine 44 which is carried by a shaft 41 mounted in bearings 32A and 42 and is driven by gases passing through the engine. The turbine 44 has fan extensions 45 which extend into a by-pass duct 46, the latter by-passing the compressor 15, the combustion chamber 22 and the turbine 16. Air drawn by the fan extensions 45 is passed through vanes 49 to mix with the turbine exhaust gases in an exhaust duct 50. Lubricant is pumped from a reservoir 51 by a pump 55 which is driven by gearing &c. from the shaft 14, and passes, via a passage 52, an annular chamber 53 and supply ducts 62, 63 and 64, to the plain bearings 32, 32A and 42 from where it returns to the reservoir via ducts 66, 67 and 68, a cooler 70, a passage 71, and the passage 52. The pump 55 also pumps lubricant from the reservoir 51 into a pipe 72 leading to an annular manifold 73 having two sets of angularly-spaced apart apertures 74, 75 through which lubricant is directed against the air intake 13.
GB27839/64A 1964-07-06 1964-07-06 Gas turbine engine Expired GB1018538A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB27839/64A GB1018538A (en) 1964-07-06 1964-07-06 Gas turbine engine
FR20071A FR1438694A (en) 1964-07-06 1965-06-09 Gas turbine engine, intended in particular to be mounted on helicopter rotor blades
DER40917A DE1300349B (en) 1964-07-06 1965-06-21 Deicing device for a gas turbine jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB27839/64A GB1018538A (en) 1964-07-06 1964-07-06 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB1018538A true GB1018538A (en) 1966-01-26

Family

ID=10266145

Family Applications (1)

Application Number Title Priority Date Filing Date
GB27839/64A Expired GB1018538A (en) 1964-07-06 1964-07-06 Gas turbine engine

Country Status (3)

Country Link
DE (1) DE1300349B (en)
FR (1) FR1438694A (en)
GB (1) GB1018538A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2136880A (en) * 1983-03-18 1984-09-26 Rolls Royce Anti-icing of gas turbine engine air intakes
EP1479889A2 (en) * 2003-05-21 2004-11-24 ROLLS-ROYCE plc Gas turbine engine and intake for a gas turbine engine with a device to prevent ice forming
GB2414520A (en) * 2004-05-28 2005-11-30 Rolls Royce Plc Increasing gas turbine bypass pressure
US7500352B2 (en) 2004-05-28 2009-03-10 Rolls-Royce Plc Gas turbine engine
FR3001253A1 (en) * 2013-01-22 2014-07-25 Snecma CONTROLLED OIL COOLING SYSTEM OF A TURBOJET ENGINE WITH DEFROSTING THE NACELLE
EP2961962A4 (en) * 2013-02-28 2016-03-16 United Technologies Corp Integrated thermal management with nacelle laminar flow control for geared architecture gas turbine engine
WO2019076519A1 (en) 2017-10-16 2019-04-25 Safran Aero Boosters Sa Outer turbocharger housing having an integrated oil tank

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2046843B (en) * 1979-04-17 1983-01-26 Rolls Royce Gas turbine engines-de-icing-icing
IT1166979B (en) * 1983-10-03 1987-05-06 Nuovo Pignone Spa ANTI-ICE SYSTEM FOR GAS TURBINE

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2400392A (en) * 1943-04-10 1946-05-14 Westinghouse Electric Corp Turbine apparatus
US2435990A (en) * 1945-08-17 1948-02-17 Westinghouse Electric Corp Gas turbine lubricating oil cooling and air inlet deicing system
US2474068A (en) * 1947-04-21 1949-06-21 Napier & Son Ltd Air intake system of internal-combustion engines
GB658931A (en) * 1948-08-19 1951-10-17 Westinghouse Electric Int Co Improvements in or relating to power plants for the propulsion of aircraft
GB697093A (en) * 1950-05-17 1953-09-16 Rolls Royce Improvements in or relating to gas-turbine power plants
GB753224A (en) * 1953-04-13 1956-07-18 Rolls Royce Improvements in or relating to blading for turbines or compressors

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2136880A (en) * 1983-03-18 1984-09-26 Rolls Royce Anti-icing of gas turbine engine air intakes
EP1479889A2 (en) * 2003-05-21 2004-11-24 ROLLS-ROYCE plc Gas turbine engine and intake for a gas turbine engine with a device to prevent ice forming
EP1479889A3 (en) * 2003-05-21 2005-02-09 ROLLS-ROYCE plc Gas turbine engine and intake for a gas turbine engine with a device to prevent ice forming
GB2414520A (en) * 2004-05-28 2005-11-30 Rolls Royce Plc Increasing gas turbine bypass pressure
GB2414520B (en) * 2004-05-28 2006-07-05 Rolls Royce Plc Gas turbine engine
US7500352B2 (en) 2004-05-28 2009-03-10 Rolls-Royce Plc Gas turbine engine
FR3001253A1 (en) * 2013-01-22 2014-07-25 Snecma CONTROLLED OIL COOLING SYSTEM OF A TURBOJET ENGINE WITH DEFROSTING THE NACELLE
EP2961962A4 (en) * 2013-02-28 2016-03-16 United Technologies Corp Integrated thermal management with nacelle laminar flow control for geared architecture gas turbine engine
US10371052B2 (en) 2013-02-28 2019-08-06 United Technologies Corporation Integrated thermal management with nacelle laminar flow control for geared architecture gas turbine engine
WO2019076519A1 (en) 2017-10-16 2019-04-25 Safran Aero Boosters Sa Outer turbocharger housing having an integrated oil tank
BE1025642B1 (en) * 2017-10-16 2019-05-15 Safran Aero Boosters S.A. COMPRESSOR HOUSING WITH OIL TANK FOR TURBOMACHINE
US11506068B2 (en) 2017-10-16 2022-11-22 Safran Aero Boosters Sa Compressor casing with oil tank for a turbine engine

Also Published As

Publication number Publication date
FR1438694A (en) 1966-05-13
DE1300349B (en) 1969-07-31

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