GB8505193D0 - Turbofan engine - Google Patents

Turbofan engine

Info

Publication number
GB8505193D0
GB8505193D0 GB858505193A GB8505193A GB8505193D0 GB 8505193 D0 GB8505193 D0 GB 8505193D0 GB 858505193 A GB858505193 A GB 858505193A GB 8505193 A GB8505193 A GB 8505193A GB 8505193 D0 GB8505193 D0 GB 8505193D0
Authority
GB
United Kingdom
Prior art keywords
turbofan engine
turbofan
engine
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.)
Withdrawn
Application number
GB858505193A
Other versions
GB2155110A (en
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB8505193D0 publication Critical patent/GB8505193D0/en
Publication of GB2155110A publication Critical patent/GB2155110A/en
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • 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
    • F02K1/64—Reversing fan flow
    • F02K1/66—Reversing fan flow using reversing fan blades
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources

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)
  • Turbine Rotor Nozzle Sealing (AREA)
GB08505193A 1984-03-02 1985-02-28 High bypass ratio counter-rotating turbofan engine Withdrawn GB2155110A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US58568784A 1984-03-02 1984-03-02

Publications (2)

Publication Number Publication Date
GB8505193D0 true GB8505193D0 (en) 1985-04-03
GB2155110A GB2155110A (en) 1985-09-18

Family

ID=24342533

Family Applications (1)

Application Number Title Priority Date Filing Date
GB08505193A Withdrawn GB2155110A (en) 1984-03-02 1985-02-28 High bypass ratio counter-rotating turbofan engine

Country Status (5)

Country Link
JP (1) JPS60256521A (en)
DE (1) DE3507035A1 (en)
FR (1) FR2560642A1 (en)
GB (1) GB2155110A (en)
IT (1) IT1183455B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113728156A (en) * 2019-04-30 2021-11-30 赛峰航空器发动机 Improved structure of turbine engine with counter-rotating turbine

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1262409A (en) * 1985-05-01 1989-10-24 Kenneth Odell Johnson Counter rotation power turbine
GB2194593B (en) * 1986-08-29 1991-05-15 Gen Electric High bypass ratio, counter rotating gearless front fan engine
GB2194292A (en) * 1986-08-29 1988-03-02 Gen Electric High bypass ratio counterrotating turbofan engine
GB2195712B (en) * 1986-10-08 1990-08-29 Rolls Royce Plc A turbofan gas turbine engine
GB2196390B (en) * 1986-10-16 1991-06-26 Rolls Royce Plc Intake for turbopropeller gas turbine engine.
FR2605679B1 (en) * 1986-10-24 1991-11-15 Culica Georges Francois TURBO ROTOR TURBOREACTOR, MULTIPLE BODIES AND MULTIPLE FLOWS
FR2606081A1 (en) * 1986-10-29 1988-05-06 Snecma PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES
GB8630754D0 (en) * 1986-12-23 1987-02-04 Rolls Royce Plc Turbofan gas turbine engine
DE3738703A1 (en) * 1987-05-27 1988-12-08 Mtu Muenchen Gmbh COMBINED, SWITCHABLE JET ENGINE FOR DRIVING PLANES AND SPACES
GB2207191B (en) * 1987-07-06 1992-03-04 Gen Electric Gas turbine engine
DE3834511A1 (en) * 1987-10-13 1990-04-12 Kastens Karl Propeller fan
DE3905282C1 (en) * 1987-10-13 1990-05-31 Karl Dipl.-Ing. 2742 Gnarrenburg De Kastens Propeller fan
DE3734624A1 (en) * 1987-10-13 1989-05-03 Kastens Karl Propeller fan
US4976102A (en) * 1988-05-09 1990-12-11 General Electric Company Unducted, counterrotating gearless front fan engine
FR2646473B1 (en) * 1989-04-26 1991-07-05 Snecma MOTOR WITH CONTRAROTATIVE TRACTOR BLOWERS
JPH03217625A (en) * 1990-01-22 1991-09-25 Hiroyasu Tanigawa All moving blade gas turbine
DE4012103C1 (en) * 1990-04-14 1991-07-25 Karl Dipl.-Ing. 2742 Gnarrenburg De Kastens Hypersonic aircraft reaction drive - has flow tube with frontal air entry slot and trough at trailing end
DE19828562B4 (en) * 1998-06-26 2005-09-08 Mtu Aero Engines Gmbh Engine with counter-rotating rotors
US6684626B1 (en) * 2002-07-30 2004-02-03 General Electric Company Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines
US6711887B2 (en) * 2002-08-19 2004-03-30 General Electric Co. Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines
GB2408072A (en) * 2003-11-15 2005-05-18 Rolls Royce Plc Contra rotatable turbine system
FR2866387B1 (en) 2004-02-12 2008-03-14 Snecma Moteurs AERODYNAMIC ADAPTATION OF THE BACK BLOW OF A DOUBLE BLOWER TURBOREACTOR
DE102004040275B4 (en) * 2004-08-19 2007-11-08 Kevork Nercessian Turbine engine
DE102008013542A1 (en) 2008-03-11 2009-09-17 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with multi-rotor arrangement
FR2946010B1 (en) 2009-05-29 2011-06-24 Snecma FIXED CYLINDER DEVICE FOR CONTROLLING BLOWER BLADES OF A TURBOPROPULSER
FR2946011B1 (en) 2009-05-29 2013-01-11 Snecma MOBILE ROLLER DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSOR
FR2946012B1 (en) 2009-05-29 2011-06-24 Snecma DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR
US10677158B2 (en) * 2015-12-29 2020-06-09 General Electric Company Method and system for in-line distributed propulsion
DE102018109357B4 (en) * 2018-04-19 2023-12-21 Arianegroup Gmbh Method for operating an aircraft with at least one engine comprising a turbomachine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB582620A (en) * 1942-04-29 1946-11-22 Karl Baumann Improvements in and relating to power plant comprising elastic fluid turbines driving load shafts through speed reduction transmission gearing
GB586570A (en) * 1943-03-18 1947-03-24 Karl Baumann Improvements in internal combustion turbine plant for propulsion

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113728156A (en) * 2019-04-30 2021-11-30 赛峰航空器发动机 Improved structure of turbine engine with counter-rotating turbine
CN113728156B (en) * 2019-04-30 2023-06-16 赛峰航空器发动机 Improved structure of turbine engine with reverse rotation turbine

Also Published As

Publication number Publication date
IT1183455B (en) 1987-10-22
GB2155110A (en) 1985-09-18
IT8519739A0 (en) 1985-03-01
FR2560642A1 (en) 1985-09-06
JPS60256521A (en) 1985-12-18
DE3507035A1 (en) 1985-09-12

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)