CH418733A - Bypass gas turbine engine - Google Patents

Bypass gas turbine engine

Info

Publication number
CH418733A
CH418733A CH657363A CH657363A CH418733A CH 418733 A CH418733 A CH 418733A CH 657363 A CH657363 A CH 657363A CH 657363 A CH657363 A CH 657363A CH 418733 A CH418733 A CH 418733A
Authority
CH
Switzerland
Prior art keywords
gas turbine
turbine engine
bypass gas
bypass
engine
Prior art date
Application number
CH657363A
Other languages
German (de)
Inventor
Taylor Hewson Colin
Original Assignee
Rolls Royce
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 filed Critical Rolls Royce
Publication of CH418733A publication Critical patent/CH418733A/en

Links

Classifications

    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/03—Annular blade-carrying members having blades on the inner periphery of the annulus and extending inwardly radially, i.e. inverted rotors
    • 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
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • 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
    • F02K3/072—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 counter-rotating, e.g. fan rotors
    • 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
    • F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
CH657363A 1962-05-31 1963-05-27 Bypass gas turbine engine CH418733A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB21106/62A GB978658A (en) 1962-05-31 1962-05-31 Gas turbine by-pass engines
GB3665063 1963-05-10

Publications (1)

Publication Number Publication Date
CH418733A true CH418733A (en) 1966-08-15

Family

ID=26255145

Family Applications (1)

Application Number Title Priority Date Filing Date
CH657363A CH418733A (en) 1962-05-31 1963-05-27 Bypass gas turbine engine

Country Status (4)

Country Link
US (1) US3182898A (en)
CH (1) CH418733A (en)
DE (1) DE1428220C3 (en)
GB (1) GB978658A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2506500A1 (en) * 1974-02-25 1975-08-28 Gen Electric TURBO DRIVE WITH VARIABLE BYPASS RATIO
DE102005021446B3 (en) * 2005-05-04 2006-06-29 Technische Universität Dresden Gas turbine, has guide vane grid rotatably supported around rotational axis of gas turbine, and brake provided for reducing number of revolutions of guide vane grid lesser than ten revolution per minute and engaging at grid

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB978462A (en) * 1963-10-28 1964-12-23 Rolls Royce Gas turbine by-pass engine
GB992931A (en) * 1964-02-21 1965-05-26 Rolls Royce Gas turbine jet propulsion engine
US3330475A (en) * 1965-04-12 1967-07-11 United Aircraft Corp Vane construction in turbofan engine
US3283995A (en) * 1965-04-28 1966-11-08 United Aircraft Corp Splitter vane construction for turbofan engine
GB1436796A (en) * 1972-08-22 1976-05-26 Mtu Muenchen Gmbh Gas turbine ducted fan engines of multi-shaft and multi-flow construction
GB1535765A (en) * 1975-01-02 1978-12-13 Gen Electric Variable cycle turbofan engines
US4043121A (en) * 1975-01-02 1977-08-23 General Electric Company Two-spool variable cycle engine
US4240250A (en) * 1977-12-27 1980-12-23 The Boeing Company Noise reducing air inlet for gas turbine engines
US4704862A (en) * 1985-05-29 1987-11-10 United Technologies Corporation Ducted prop engine
FR2645911B1 (en) * 1989-04-18 1991-06-07 Snecma HIGH DILUTION MOTOR WITH UPSTREAM BLOWER AND DOWNSTREAM BLOWER
GB2353983B (en) * 2000-07-04 2003-10-15 Adrian Alexander Hubbard Variable mode jet engine-suitable for STOVL
US7144221B2 (en) * 2004-07-30 2006-12-05 General Electric Company Method and apparatus for assembling gas turbine engines
US7225607B2 (en) * 2004-08-27 2007-06-05 Pratt & Whitney Canada Corp. Gas turbine braking apparatus and method
US7631484B2 (en) * 2006-03-13 2009-12-15 Rollin George Giffin High pressure ratio aft fan
DE102008021683A1 (en) 2008-04-30 2009-11-05 Rolls-Royce Deutschland Ltd & Co Kg Rotating unit for an axial compressor
BE1022364B1 (en) * 2014-10-27 2016-03-17 Techspace Aero S.A. AXIAL TURBOMACHINE COMPRESSOR WITH DOUBLE CONTRAROTATIVE ROTORS
US10329943B2 (en) 2014-11-18 2019-06-25 Rolls-Royce North American Technologies Inc. Split axial-centrifugal compressor
US9982676B2 (en) 2014-11-18 2018-05-29 Rolls-Royce North American Technologies Inc. Split axial-centrifugal compressor
CN106567746A (en) * 2015-10-10 2017-04-19 熵零控股股份有限公司 Combined-flow impeller mechanism
CN105756716A (en) * 2016-04-22 2016-07-13 中国船舶重工集团公司第七�三研究所 Double-layer integral fixed blade ring for turbine capable of reversing
GB201813671D0 (en) 2018-08-22 2018-10-03 Rolls Royce Plc Turbomachine
GB201813672D0 (en) 2018-08-22 2018-10-03 Rolls Royce Plc Turbomachine
GB201813674D0 (en) 2018-08-22 2018-10-03 Rolls Royce Plc Turbomachine
GB201813670D0 (en) 2018-08-22 2018-10-03 Rolls Royce Plc Turbomachine
GB201813675D0 (en) 2018-08-22 2018-10-03 Rolls Royce Plc Turbomachine
CN110259600A (en) * 2019-06-25 2019-09-20 中国航空发动机研究院 Double outer adaptive cycle engines of culvert

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL65557C (en) *
US2450745A (en) * 1942-11-12 1948-10-05 Vickers Electrical Co Ltd Axial flow compressor
US2702985A (en) * 1944-01-31 1955-03-01 Power Jets Res & Dev Ltd Gas turbine power plant with power take-off from rotatable guide blading
GB676769A (en) * 1948-07-20 1952-08-06 Rolls Royce Improvements relating to gas compressor systems
US2659528A (en) * 1948-09-29 1953-11-17 Lockheed Aircraft Corp Gas turbine compressor system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2506500A1 (en) * 1974-02-25 1975-08-28 Gen Electric TURBO DRIVE WITH VARIABLE BYPASS RATIO
DE102005021446B3 (en) * 2005-05-04 2006-06-29 Technische Universität Dresden Gas turbine, has guide vane grid rotatably supported around rotational axis of gas turbine, and brake provided for reducing number of revolutions of guide vane grid lesser than ten revolution per minute and engaging at grid

Also Published As

Publication number Publication date
US3182898A (en) 1965-05-11
DE1428220A1 (en) 1969-07-17
GB978658A (en) 1964-12-23
DE1428220B2 (en) 1973-10-04
DE1428220C3 (en) 1974-05-09

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