GB1294898A - - Google Patents

Info

Publication number
GB1294898A
GB1294898A GB6089969A GB1294898DA GB1294898A GB 1294898 A GB1294898 A GB 1294898A GB 6089969 A GB6089969 A GB 6089969A GB 1294898D A GB1294898D A GB 1294898DA GB 1294898 A GB1294898 A GB 1294898A
Authority
GB
United Kingdom
Prior art keywords
fan
engine
shaft
rotor
assembly
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
GB6089969A
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 GB1294898A publication Critical patent/GB1294898A/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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F04D29/323—Blade mountings adjustable
    • 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
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1294898 Gas turbine ducted fan engines DOWTY ROTOL Ltd 13 Nov 1970 [13 Dec 1969] 60899/69 Heading F1J The invention relates to a fan assembly for attachment to the front of a main gas turbine engine so as to provide an engine of the ducted fan by-pass type, the assembly being constructed as a unit which can be attached to or removed from the engine. The fan assembly is indicated as A in Fig.1 and the forward part of the gas turbine engine at B, the fan assembly being secured to the engine at the plane C. The fan assembly comprises fixed structure 10 in which the fan rotor assembly is rotatably mounted, the fixed structure also supporting the by-pass duct 13 through a series of stator vanes 14 disposed downstream of the fan rotor blades 12. The fan rotor shaft 28 is supported within the fixed structure 10 by means of bearings 29. The rotor blades 12 are of adjustable pitch, the pitch being adjusted by means of a vane type motor 15 which comprises two oppositely angularly movable members 18,19 formed with bevel gear wheels 22, 23 which mesh with bevel pinions 20 mounted at the roots of the rotor blades 12, angular movement of the members 18,19 thus resulting in adjustment of the pitch of the fan rotor blades. The fan rotor is driven from the engine shaft 31 by means of a quill shaft 30 which is in splined engagement with the engine shaft 31 and the fan rotor shaft 28. A spinner 24 forms part of the rotor assembly. A guard ring 25 is incorporated in the fan duct 13. In Fig.3 the fan rotor 11 is driven from the engine shaft 40 through reduction gearing 37, the stator structure 10 projecting forwardly to provide a bearing support for the fan rotor shaft. The angularly movable members 18,19 of the vane rotor 15 extend rearwardly as shown, the members being formed with bevel gears which engage bevel pinions 20 on the fan rotor blades as in Fig.1. The fan blades are two-tiered comprising an outer part 12 of angularly adjustable pitch and an inner part 32 of fixed pitch, the pitch change shaft of the part 12 extending through the inner part 32. The fan stator structure comprises a splitter member 41 which defines the inner wall of the fan duct and the outer wall of a duct leading air from the inner blade parts 32 to the intake 27 of the engine compressor. In Fig.4 (not shown), a drive for engine auxiliaries is taken from the reduction gearing 37 through a radially-extending shaft (45) and a horizontally-extending shaft (48). (For Figures see next page)
GB6089969A 1969-12-13 1969-12-13 Expired GB1294898A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB6089969 1969-12-13
US9100070A 1970-11-19 1970-11-19

Publications (1)

Publication Number Publication Date
GB1294898A true GB1294898A (en) 1972-11-01

Family

ID=26267838

Family Applications (1)

Application Number Title Priority Date Filing Date
GB6089969A Expired GB1294898A (en) 1969-12-13 1969-12-13

Country Status (4)

Country Link
US (1) US3720060A (en)
DE (1) DE2061425C3 (en)
FR (1) FR2070846B1 (en)
GB (1) GB1294898A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5419112A (en) * 1989-06-05 1995-05-30 General Electric Company Gas turbine powerplant
CN104520542A (en) * 2012-08-09 2015-04-15 斯奈克玛 Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan

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US3811791A (en) * 1971-08-12 1974-05-21 R Cotton Thrust augmenting device for jet aircraft
DE2218874C3 (en) * 1972-04-19 1979-05-17 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Device for adjusting the fan blades of a turbine jet engine
DE2307656C3 (en) * 1973-02-16 1979-01-04 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Device for adjusting the fan blades of an impeller for turbine jet engines
US3942911A (en) * 1973-02-17 1976-03-09 Dowty Rotol Limited Bladed rotors
US3893783A (en) * 1973-02-17 1975-07-08 Dowty Rotol Ltd Gas turbine engines and bladed rotors therefor
GB1444754A (en) * 1973-04-18 1976-08-04 Dowty Rotol Ltd Rotary actuators suitable for bladed rotors
GB1444753A (en) * 1973-04-18 1976-08-04 Dowty Rotol Ltd Rotary actuators suitable for bladed rotors
US3904315A (en) * 1974-07-31 1975-09-09 United Aircraft Corp Pitch change signal means with differential gearing
US3912418A (en) * 1974-10-01 1975-10-14 United Technologies Corp Lubrication system for a rotor
US4005574A (en) * 1975-04-21 1977-02-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reverse pitch fan with divided splitter
US4010919A (en) * 1975-12-05 1977-03-08 Breuner Gerald L Autogyro having blade tip jets
US4239452A (en) * 1978-06-26 1980-12-16 United Technologies Corporation Blade tip shroud for a compression stage of a gas turbine engine
JPS6318799Y2 (en) * 1980-12-02 1988-05-26
US4566269A (en) * 1983-10-11 1986-01-28 United Technologies Corporation Jet engine removable support assembly
GB2192233B (en) * 1986-07-02 1990-11-28 Rolls Royce Plc A gas turbine engine load transfer structure
US4750862A (en) * 1986-11-28 1988-06-14 United Technologies Corporation Modular propeller blade pitch actuation system
US4744214A (en) * 1987-06-29 1988-05-17 United Technologies Corporation Engine modularity
US4976102A (en) * 1988-05-09 1990-12-11 General Electric Company Unducted, counterrotating gearless front fan engine
US4934140A (en) * 1988-05-13 1990-06-19 United Technologies Corporation Modular gas turbine engine
US4968217A (en) * 1989-09-06 1990-11-06 Rolls-Royce Plc Variable pitch arrangement for a gas turbine engine
US5222360A (en) * 1991-10-30 1993-06-29 General Electric Company Apparatus for removably attaching a core frame to a vane frame with a stable mid ring
US5205513A (en) * 1991-09-26 1993-04-27 General Electric Company Method and system for the removal of large turbine engines
JP2007500298A (en) * 2003-07-29 2007-01-11 プラット　アンド　ホイットニー　カナダ　コーポレイション Turbofan case and manufacturing method
US7370467B2 (en) * 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making
EP1828591B1 (en) * 2004-12-01 2010-07-21 United Technologies Corporation Peripheral combustor for tip turbine engine
WO2006060000A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US7878762B2 (en) * 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
DE602004020125D1 (en) * 2004-12-01 2009-04-30 United Technologies Corp LUBRICANT SUPPLY SYSTEM FOR THE TRANSMISSION OF A TIP TURBINE ENGINE
WO2006059979A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral case, vane, mount, and mixer
EP1825113B1 (en) * 2004-12-01 2012-10-24 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
EP1825114B1 (en) * 2004-12-01 2008-08-20 United Technologies Corporation Tip turbine engine with a heat exchanger
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
EP1825116A2 (en) * 2004-12-01 2007-08-29 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
EP2333287A1 (en) * 2004-12-01 2011-06-15 United Technologies Corporation Vectoring transition duct for turbine engine
WO2006060013A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US8096753B2 (en) * 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
WO2006059969A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
US9003759B2 (en) * 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
EP1819907A2 (en) * 2004-12-01 2007-08-22 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
WO2006059970A2 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
WO2006060010A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Compressor inlet guide vane for tip turbine engine and corresponding control method
US7921636B2 (en) * 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
WO2006059997A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Annular turbine ring rotor
US7934902B2 (en) * 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7976273B2 (en) * 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
WO2006059971A2 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
EP1834071B1 (en) * 2004-12-01 2013-03-13 United Technologies Corporation Inducer for a fan blade of a tip turbine engine
EP1828683B1 (en) 2004-12-01 2013-04-10 United Technologies Corporation Combustor for turbine engine
US7874802B2 (en) * 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
WO2006059996A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
DE602004029950D1 (en) * 2004-12-01 2010-12-16 United Technologies Corp SLIDED GEAR ASSEMBLY FOR A TOP TURBINE ENGINE
WO2006059988A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
US20090169385A1 (en) * 2004-12-01 2009-07-02 Suciu Gabriel L Fan-turbine rotor assembly with integral inducer section for a tip turbine engine
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
WO2006110125A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Stacked annular components for turbine engines
EP1831519B1 (en) * 2004-12-01 2010-08-04 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US7874163B2 (en) * 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
DE602004027766D1 (en) * 2004-12-01 2010-07-29 United Technologies Corp HYDRAULIC SEAL FOR A GEARBOX OF A TOP TURBINE ENGINE
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7883314B2 (en) * 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US8757959B2 (en) * 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
DE602004031679D1 (en) * 2004-12-01 2011-04-14 United Technologies Corp Regenerative cooling of a guide and blade for a tipturbine engine
WO2006060006A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
EP1825112B1 (en) * 2004-12-01 2013-10-23 United Technologies Corporation Cantilevered tip turbine engine
EP1828568B1 (en) * 2004-12-01 2011-03-23 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
EP1828567B1 (en) 2004-12-01 2011-10-12 United Technologies Corporation Diffuser aspiration for a tip turbine engine
WO2006062497A1 (en) * 2004-12-04 2006-06-15 United Technologies Corporation Tip turbine engine mount
FR2911644B1 (en) * 2007-01-23 2012-06-01 Snecma TURBOPROPULSEUR COMPRISING A PROPELLED PROPELLER OF BLADES WITH ADJUSTABLE ORIENTATION.
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US20100187825A1 (en) * 2009-01-28 2010-07-29 Fred Carr Microprocessor system for controlling rotor pitch
RU2523928C2 (en) * 2009-02-27 2014-07-27 Снекма Fan blades with variable pitch angle
US8602731B2 (en) * 2009-12-30 2013-12-10 Fred K. Carr Microprocessor system for controlling rotor pitch
DE102012000889A1 (en) * 2012-01-18 2013-07-18 Rolls-Royce Deutschland Ltd & Co Kg Air turbine with adjustable fan
US9476323B2 (en) 2012-05-31 2016-10-25 United Technologies Corporation Turbine gear assembly support having symmetrical removal features
US9103376B2 (en) * 2013-10-23 2015-08-11 Hamilton Sundstrand Corporation Chambered shaft for improved bearing lubrication
US10215096B2 (en) * 2015-11-04 2019-02-26 United Technologies Corporation Engine with nose cone heat exchanger and radially outer discharge
US10436151B2 (en) * 2015-11-17 2019-10-08 General Electric Company Modular fan for a gas turbine engine
US20170218975A1 (en) * 2016-01-29 2017-08-03 United Technologies Corporation Variable pitch fan blade arrangement for gas turbine engine
US11007955B2 (en) * 2016-05-18 2021-05-18 Rolls-Royce North American Technologies Inc. Low pressure generator with electrical assembly for gas turbine engine
US11022042B2 (en) 2016-08-29 2021-06-01 Rolls-Royce North American Technologies Inc. Aircraft having a gas turbine generator with power assist
US10415405B2 (en) * 2017-04-21 2019-09-17 United Technologies Corporation Variable pitch fan blade system
US11255215B2 (en) 2017-07-06 2022-02-22 Rolls-Royce North American Technologies Inc. Gas turbine engine with microchannel cooled electric device
FR3080886B1 (en) * 2018-05-02 2020-10-30 Safran Aircraft Engines FAIRING BLOWER TURBOMACHINE
FR3087232B1 (en) * 2018-10-12 2021-06-25 Safran Aircraft Engines TURBOMACHINE INCLUDING A ROTOR WITH VARIABLE TIMING BLADES
FR3100563B1 (en) * 2019-09-06 2021-08-06 Safran Aircraft Engines Polyspherical turbomachine hub for variable pitch blades

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5419112A (en) * 1989-06-05 1995-05-30 General Electric Company Gas turbine powerplant
CN104520542A (en) * 2012-08-09 2015-04-15 斯奈克玛 Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
CN104520542B (en) * 2012-08-09 2016-04-13 斯奈克玛 Comprise multiple turbines being installed in the fixed radial blades of fan upstream

Also Published As

Publication number Publication date
FR2070846A1 (en) 1971-09-17
FR2070846B1 (en) 1975-02-21
DE2061425C3 (en) 1980-01-03
DE2061425A1 (en) 1971-06-24
US3720060A (en) 1973-03-13
DE2061425B2 (en) 1977-05-18

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee