GB888080A - Improvements in or relating to gas turbine engines - Google Patents

Improvements in or relating to gas turbine engines

Info

Publication number
GB888080A
GB888080A GB6049/60A GB604960A GB888080A GB 888080 A GB888080 A GB 888080A GB 6049/60 A GB6049/60 A GB 6049/60A GB 604960 A GB604960 A GB 604960A GB 888080 A GB888080 A GB 888080A
Authority
GB
United Kingdom
Prior art keywords
engine
pass
pass duct
wall
pressure compressor
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
GB6049/60A
Inventor
Thomas Henry Kerry
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 GB6049/60A priority Critical patent/GB888080A/en
Publication of GB888080A publication Critical patent/GB888080A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • 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
    • F02K3/06—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 front 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
    • Y02T50/40—Weight reduction
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

888,080. Gas-turbine jet-propulsion engines. ROLLS-ROYCE Ltd. Jan. 16, 1961 [Feb. 20, 1960], No. 6049/60. Class 110 (3). A by-pass gas-turbine engine has the outer wall of the by-pass duct formed, in a transverse section, over a major part of its length by a pair of outwardly-convex arcs joined endto-end, each arc being greater than a semicircle in extent so that the transverse dimension of the engine is reduced in the axial plane where the two arcs join. The invention is described with reference to a by-pass compound gasturbine engine in which air compressed in a low pressure compressor is divided, part flows direct to the propulsion nozzle through a by-pass duct and the remainder is further compressed by a high-pressure compressor and supplied to a combustion chamber feeding two separate turbines, one of which drives the highpressure compressor and the other drives the low-pressure compressor. The turbines exhaust to the propulsion nozzle. The by-pass duct 13, Fig. 2, has an outer wall 26 formed along part of its length by a pair of outwardly-convex arcuate portions 26a which are joined together in the vertical plane. At the intersection of the two arcuate portions, radial walls 27 which are connected to the inner circular wall 28 of the by-pass duct, are provided. The walls 27 have a number of apertures 29 which equalize the gas pressures in the arcuate portions 26a, and the topmost wall is connected to the strut 24 by means of which the engine is supported from the aircraft wing. This arrangement of the by-pass duct allows a larger engine to be installed in an existing aircraft without affecting the ground clearance and the clearance between the engine and the aircraft wing. A modification in which the engines are mounted on the side of the fuselage is also described. Specifications 843,359 and 852,829 are referred to.
GB6049/60A 1960-02-20 1960-02-20 Improvements in or relating to gas turbine engines Expired GB888080A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB6049/60A GB888080A (en) 1960-02-20 1960-02-20 Improvements in or relating to gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB6049/60A GB888080A (en) 1960-02-20 1960-02-20 Improvements in or relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB888080A true GB888080A (en) 1962-01-24

Family

ID=9807475

Family Applications (1)

Application Number Title Priority Date Filing Date
GB6049/60A Expired GB888080A (en) 1960-02-20 1960-02-20 Improvements in or relating to gas turbine engines

Country Status (1)

Country Link
GB (1) GB888080A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5369954A (en) * 1991-04-22 1994-12-06 General Electric Company Turbofan engine bypass and exhaust system
FR3012417A1 (en) * 2013-10-31 2015-05-01 Snecma TURBOREACTOR NACELLE
RU2566091C2 (en) * 2010-02-08 2015-10-20 Снекма Cold flow nozzle of bypass turbojet with separate flows including grate thrust reverser
EP3020952A1 (en) * 2014-11-11 2016-05-18 Rolls-Royce plc Gas turbine engine duct with profiled region
EP3020951A1 (en) * 2014-11-11 2016-05-18 Rolls-Royce plc Gas turbine engine duct with profiled region

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5369954A (en) * 1991-04-22 1994-12-06 General Electric Company Turbofan engine bypass and exhaust system
RU2566091C2 (en) * 2010-02-08 2015-10-20 Снекма Cold flow nozzle of bypass turbojet with separate flows including grate thrust reverser
FR3012417A1 (en) * 2013-10-31 2015-05-01 Snecma TURBOREACTOR NACELLE
EP3020952A1 (en) * 2014-11-11 2016-05-18 Rolls-Royce plc Gas turbine engine duct with profiled region
EP3020951A1 (en) * 2014-11-11 2016-05-18 Rolls-Royce plc Gas turbine engine duct with profiled region
US10053997B2 (en) 2014-11-11 2018-08-21 Rolls-Royce Plc Gas turbine engine
US10215042B2 (en) 2014-11-11 2019-02-26 Rolls-Royce Plc Gas turbine engine

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