GB1290485A - - Google Patents

Info

Publication number
GB1290485A
GB1290485A GB1290485DA GB1290485A GB 1290485 A GB1290485 A GB 1290485A GB 1290485D A GB1290485D A GB 1290485DA GB 1290485 A GB1290485 A GB 1290485A
Authority
GB
United Kingdom
Prior art keywords
fan
turbine
blade
shaft
actuator
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
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 filed Critical
Publication of GB1290485A publication Critical patent/GB1290485A/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
    • 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
    • F02K3/062—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 aft 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

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

1290485 Gas turbine ducted fan engines DEFENCE SECRETARY OF STATE FOR 21 Oct 1969 [22 Oct 1968] 49974/68 Heading F1J A by-pass gas turbine power plant having a multi-bladed ducted fan comprises an actuator whereby the blades of the fan may be rotated about their longitudinal axes from a forward thrust position to a reverse thrust position. The engine shown comprises LP compressor 2, HP compressor 5, combustion equipment 8, HP turbine 7 and LP turbine 4, all in series flow, part of the air from the LP compressor passing through bypass duct 9, the by-pass air and the exhaust gases from LP turbine 4 acting on turbine 30 which drives ducted fan 21. The turbine 30 and fan are mounted on shaft 23 which is supported in bearings 24, 25. The fan casing 26 is supported by struts 27, 28. Each fan blade is mounted on a shaft 31 which is mounted for angular movement in a bearing 32, the shaft 31 being enclosed by a fairing 33. An actuator 34 comprising a piston 40 is mounted on stationary structure 35, the piston being connected through a bearing 36 to a frustoconical link member 41 which is in splined engagement at 42 with a flange portion 43 of the shaft 23. The member 41 is connected to arm 47 on the blade shaft 31 by a link 45 pivotally mounted at 44, 46. The actuator moves the blade between a forward thrust position and a reverse thrust position. A circular chamber 50 is provided at the root of each blade 21 and a vane piston member 51 is disposed in the chamber, being connected to the blade. The vane 51 is disposed between a pair of stop members 52 being shown in contact with the surfaces 53 of the stops. Air under pressure may be passed through the hollow shaft 31 through ports 55 so as to cause the vane 51 to move towards its other end position against stop surfaces 54 so rotating the fan blade about its axis and assisting the action of the actuator 34.
GB1290485D 1968-10-22 1968-10-22 Expired GB1290485A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4997468 1968-10-22

Publications (1)

Publication Number Publication Date
GB1290485A true GB1290485A (en) 1972-09-27

Family

ID=10454174

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1290485D Expired GB1290485A (en) 1968-10-22 1968-10-22

Country Status (1)

Country Link
GB (1) GB1290485A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4913623A (en) * 1985-11-12 1990-04-03 General Electric Company Propeller/fan-pitch feathering apparatus
GB2264751A (en) * 1992-03-04 1993-09-08 Snecma Jet propulsion engine.
ES2370308A1 (en) * 2008-12-31 2011-12-14 Futur Investment Partners, S.A. Aeronautical motor. (Machine-translation by Google Translate, not legally binding)
EP3037622A1 (en) * 2014-12-24 2016-06-29 United Technologies Corporation A turbine engine with guide vanes forward of its fan blades

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4913623A (en) * 1985-11-12 1990-04-03 General Electric Company Propeller/fan-pitch feathering apparatus
GB2264751A (en) * 1992-03-04 1993-09-08 Snecma Jet propulsion engine.
GB2264751B (en) * 1992-03-04 1996-01-24 Snecma Propulsion engine
ES2370308A1 (en) * 2008-12-31 2011-12-14 Futur Investment Partners, S.A. Aeronautical motor. (Machine-translation by Google Translate, not legally binding)
EP3037622A1 (en) * 2014-12-24 2016-06-29 United Technologies Corporation A turbine engine with guide vanes forward of its fan blades
US10711631B2 (en) 2014-12-24 2020-07-14 Raytheon Technologies Corporation Turbine engine with guide vanes forward of its fan blades

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees