GB978658A - Gas turbine by-pass engines - Google Patents

Gas turbine by-pass engines

Info

Publication number
GB978658A
GB978658A GB21106/62A GB2110662A GB978658A GB 978658 A GB978658 A GB 978658A GB 21106/62 A GB21106/62 A GB 21106/62A GB 2110662 A GB2110662 A GB 2110662A GB 978658 A GB978658 A GB 978658A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
rotatable
fan
driven
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
GB21106/62A
Inventor
Colin Taylor Hewson
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 GB21106/62A priority Critical patent/GB978658A/en
Priority to US282788A priority patent/US3182898A/en
Priority to CH657363A priority patent/CH418733A/en
Priority to DE1428220A priority patent/DE1428220C3/en
Publication of GB978658A publication Critical patent/GB978658A/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
    • 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)

Abstract

978,658. Axial-flow fans and compressors; gas turbine jet propulsion plant. ROLLS-ROYCE Ltd. May 10, 1963 [May 31, 1962], No. 21106/62. Headings FIC, F1G and F1J. A gas turbine by-pass engine comprises a high-pressure compressor and a high-pressure turbine each of which has at least one row of rotor blades drivingly engaged with a first shaft, a low-pressure compressor and a lowpressure turbine each of which has at least one row of rotor blades drivingly engaged with a second shaft which is mounted within the first shaft, a by-pass duct which communicates with the downstream end of the low-pressure compressor so as to receive part of the air compressed thereby, a rotatable casing which forms part of the low-pressure compressor and which carries at least one row of rotatable stator blades which are driven by air passing through the low-pressure compressor, and a driven part which requires substantial torque to drive it and which is drivingly connected to the rotatable casing. The aircraft gas turbine by-pass engine shown in Fig. 5 comprises an L.P. compressor 141m and an H.P. compressor 134m driven, through concentric shafts 137m, 132m by an L.P. turbine 131m and an H.P. turbine 130m respectively. The stator blades 142m of the L.P. compressor are carried by a rotatable annular casing 143m which also carries the rotor blades 144m of a fan disposed within fan duct 145m. The air passing through the L.P. compressor rotates the stator blades 142m, and hence also the fan rotor blades 144m, at a speed which may be 30 to 40% of the speed of the rotor blades of the L.P. compressor. A by-pass duct 165m receiving part of the discharge of the L.P. compressor communicates with the jet pipe 207 of the engine via short mixer shoots 208. The fan duct 145m communicates with the jet pipe 207 via short mixer shoots 209 arranged downstream of the mixer shoots 208. A thrust reverser or deflector may be arranged at the end of the jet pipe 207. In alternative embodiments, the by-pass duct does not communicate with the jet pipe, and discharges through an annular orifice concentric with the jet pipe orifice. The fan may be used for. boundary layer suction, for supplying air to vertical-lift fans or to provide altitude control of the aircraft. The fan duct may discharge direct to atmosphere. An intermediate-pressure compressor, driven by the L.P. turbine, may be provided and its stator blading may be rotatable and coupled to the rotatable stator blading of the L.P. compressor. Instead of driving a fan, the rotatable stator blades may drive a propeller, a helicopter rotor, a rudder, an electrical generator or other engine auxiliaries. The drive may be transmitted through a gear box. A brake may be provided for preventing rotation of the rotatable stator blades. The Provisional Specification describes a number of single-shaft embodiments in which the L.P. turbine is omitted. In one such embodiment, the engine can be turned through 90 degrees about trunnions to provide vertical lift. When the engine is used for forward propulsion, a brake is applied to the rotatable stator to put the fan out of action. In another embodiment, L.P. and H.P. compressors are provided. The H.P. compressor rotor is driven by the turbine but the L.P. compressor rotor is driven by the rotatable stator of the H.P. compressor.
GB21106/62A 1962-05-31 1962-05-31 Gas turbine by-pass engines Expired GB978658A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB21106/62A GB978658A (en) 1962-05-31 1962-05-31 Gas turbine by-pass engines
US282788A US3182898A (en) 1962-05-31 1963-05-23 Axial flow compressor or fan and gas turbine engine provided therewith
CH657363A CH418733A (en) 1962-05-31 1963-05-27 Bypass gas turbine engine
DE1428220A DE1428220C3 (en) 1962-05-31 1963-05-28 By-pass gas turbine jet engine in two-shaft design

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
GB978658A true GB978658A (en) 1964-12-23

Family

ID=26255145

Family Applications (1)

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

Country Status (4)

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

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0203881A1 (en) * 1985-05-29 1986-12-03 United Technologies Corporation Ducted prop engine
EP2113637A2 (en) 2008-04-30 2009-11-04 Rolls-Royce Deutschland Ltd & Co KG Rotating unit for an axial compressor
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
CN106567746A (en) * 2015-10-10 2017-04-19 熵零控股股份有限公司 Combined-flow impeller mechanism
US11247780B2 (en) 2018-08-22 2022-02-15 Rolls-Royce Plc Turbomachine having inner and outer fans with hub-tip ratios
US11306682B2 (en) 2018-08-22 2022-04-19 Rolls-Royce Plc Concentric turbomachine with trailing edge
US11313327B2 (en) 2018-08-22 2022-04-26 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371350B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371467B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine

Families Citing this family (19)

* 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
CA1020365A (en) * 1974-02-25 1977-11-08 James E. Johnson Modulating bypass variable cycle turbofan engine
US4043121A (en) * 1975-01-02 1977-08-23 General Electric Company Two-spool variable cycle engine
GB1535765A (en) * 1975-01-02 1978-12-13 Gen Electric Variable cycle turbofan engines
US4240250A (en) * 1977-12-27 1980-12-23 The Boeing Company Noise reducing air inlet for gas turbine engines
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
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
US7631484B2 (en) * 2006-03-13 2009-12-15 Rollin George Giffin High pressure ratio aft fan
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
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 (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0203881A1 (en) * 1985-05-29 1986-12-03 United Technologies Corporation Ducted prop engine
US4704862A (en) * 1985-05-29 1987-11-10 United Technologies Corporation Ducted prop engine
EP2113637A2 (en) 2008-04-30 2009-11-04 Rolls-Royce Deutschland Ltd & Co KG Rotating unit for an axial compressor
DE102008021683A1 (en) 2008-04-30 2009-11-05 Rolls-Royce Deutschland Ltd & Co Kg Rotating unit for an axial 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
US11247780B2 (en) 2018-08-22 2022-02-15 Rolls-Royce Plc Turbomachine having inner and outer fans with hub-tip ratios
US11306682B2 (en) 2018-08-22 2022-04-19 Rolls-Royce Plc Concentric turbomachine with trailing edge
US11313327B2 (en) 2018-08-22 2022-04-26 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371350B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371467B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine

Also Published As

Publication number Publication date
DE1428220B2 (en) 1973-10-04
DE1428220A1 (en) 1969-07-17
DE1428220C3 (en) 1974-05-09
US3182898A (en) 1965-05-11
CH418733A (en) 1966-08-15

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