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GB1190364A - Gas Turbine Engines - Google Patents

Gas Turbine Engines

Info

Publication number
GB1190364A
GB1190364A GB41454/66A GB4145466A GB1190364A GB 1190364 A GB1190364 A GB 1190364A GB 41454/66 A GB41454/66 A GB 41454/66A GB 4145466 A GB4145466 A GB 4145466A GB 1190364 A GB1190364 A GB 1190364A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
april
engine
turbine engines
fan
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
GB41454/66A
Inventor
Stuart Duncan Davies
John Alfred Chilman
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.)
Dowty Rotol Ltd
Original Assignee
Dowty Rotol Ltd
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 Dowty Rotol Ltd filed Critical Dowty Rotol Ltd
Priority to US630255A priority Critical patent/US3476486A/en
Priority to DE19671626030 priority patent/DE1626030C/en
Priority to CH535867A priority patent/CH458840A/en
Publication of GB1190364A publication Critical patent/GB1190364A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/30—Non-positive-displacement machines or engines, e.g. steam turbines characterised by having a single rotor operable in either direction of rotation, e.g. by reversing of blades
    • 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
    • F02K3/06—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
    • 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
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,190,364. Reversing propulsive jets. DOWTY ROTOL Ltd. 11 April, 1967 [12 April, 1966; 25 May, 1966(2); 16 Sept., 1966], Nos. 41454/66; 16223/67; 15968/67 and 15969/67. Heading B7G. [Also in Divisions F1 and F2] In a gas turbine ducted fan engine (see Division F1) the pitch of the fan blades may be adjusted from positive to negative so that the fan air which normally flows rearwardly through the duct now flows forwardly thus exerting a braking effect on an aircraft in which the engine is mounted.
GB41454/66A 1966-04-12 1966-04-12 Gas Turbine Engines Expired GB1190364A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US630255A US3476486A (en) 1966-04-12 1967-04-12 Gas turbine engines
DE19671626030 DE1626030C (en) 1966-04-12 1967-04-12 Twin-flow gas turbine jet engine
CH535867A CH458840A (en) 1966-04-12 1967-04-12 Turbo-propellant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1622367 1966-04-12

Publications (1)

Publication Number Publication Date
GB1190364A true GB1190364A (en) 1970-05-06

Family

ID=10073399

Family Applications (1)

Application Number Title Priority Date Filing Date
GB41454/66A Expired GB1190364A (en) 1966-04-12 1966-04-12 Gas Turbine Engines

Country Status (1)

Country Link
GB (1) GB1190364A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2162257A1 (en) * 1971-12-07 1973-07-20 Snecma
GB2145774A (en) * 1983-08-31 1985-04-03 Dowty Rotol Ltd Bladed rotors and ducts associated therewith
EP2426342A3 (en) * 2006-10-12 2012-05-09 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
WO2014137685A1 (en) 2013-03-04 2014-09-12 United Technologies Corporation Gas turbine engine inlet
FR3126734A1 (en) * 2021-09-07 2023-03-10 Safran Aircraft Engines Aircraft engine comprising a propeller having blades orientable according to a propulsion or thrust reversal orientation

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2162257A1 (en) * 1971-12-07 1973-07-20 Snecma
GB2145774A (en) * 1983-08-31 1985-04-03 Dowty Rotol Ltd Bladed rotors and ducts associated therewith
EP2426342A3 (en) * 2006-10-12 2012-05-09 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
US8480350B2 (en) 2006-10-12 2013-07-09 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
WO2014137685A1 (en) 2013-03-04 2014-09-12 United Technologies Corporation Gas turbine engine inlet
EP2964924A4 (en) * 2013-03-04 2016-11-09 United Technologies Corp Gas turbine engine inlet
EP3564507A1 (en) * 2013-03-04 2019-11-06 United Technologies Corporation Gas turbine engine inlet
US11480104B2 (en) 2013-03-04 2022-10-25 Raytheon Technologies Corporation Gas turbine engine inlet
FR3126734A1 (en) * 2021-09-07 2023-03-10 Safran Aircraft Engines Aircraft engine comprising a propeller having blades orientable according to a propulsion or thrust reversal orientation

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee