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GB1309721A - Fan - Google Patents

Fan

Info

Publication number
GB1309721A
GB1309721A GB97571A GB1309721DA GB1309721A GB 1309721 A GB1309721 A GB 1309721A GB 97571 A GB97571 A GB 97571A GB 1309721D A GB1309721D A GB 1309721DA GB 1309721 A GB1309721 A GB 1309721A
Authority
GB
United Kingdom
Prior art keywords
fan
shaft
stage
carries
gas turbine
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
GB97571A
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.)
SECR DEFENCE
UK Secretary of State for Defence
Original Assignee
SECR DEFENCE
UK Secretary of State for Defence
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 SECR DEFENCE, UK Secretary of State for Defence filed Critical SECR DEFENCE
Publication of GB1309721A publication Critical patent/GB1309721A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/026—Multi-stage pumps with a plurality of shafts rotating at different speeds
    • 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
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/028—Units comprising pumps and their driving means the driving means being a planetary gear
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/19—Gearing
    • Y10T74/19023—Plural power paths to and/or from gearing
    • Y10T74/19074—Single drive plural driven
    • Y10T74/19121—Concentric

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

1309721 Fans; gas turbine ducted fan engines DEFENCE SECRETARY OF STATE FOR 16 Dec 1971 [8 Jan 1971] 975/71 Headings F1C and F1J The invention relates to a two-stage fan and to means for driving the fan comprising an epicyclic gearing. The invention is shown applied to the twostage fan 22, 20 of a gas turbine ducted fan engine which comprises a gas turbine type gas generator of the two-shaft type gases from which drive the fan turbine (17) which in turn drives the fan through shaft 18. The first-stage fan 22 is of relatively small diameter compared with the second-stage fan 20 and the shroud 21 for the firststage fan is carried by the second-stage fan. The first-stage fan comprises a shaft 23 which is supported in bearings 24, 25 and carries a sun gear 31. The second-stage fan comprises a shaft 26 which is supported in bearings 24, 27, 29 and 30 and carries an annulus gear 32. The drive shaft 18 is formed with a planet carrier 34 which carries planet pinions 33 which engage with the sun gear 31 and the annulus gear 32 whereby the fan stages 22 and 20 are driven at different speeds.
GB97571A 1971-01-08 1971-01-08 Fan Expired GB1309721A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB97571 1971-01-08

Publications (1)

Publication Number Publication Date
GB1309721A true GB1309721A (en) 1973-03-14

Family

ID=9713823

Family Applications (1)

Application Number Title Priority Date Filing Date
GB97571A Expired GB1309721A (en) 1971-01-08 1971-01-08 Fan

Country Status (6)

Country Link
US (1) US3729957A (en)
JP (1) JPS5233323B1 (en)
DE (1) DE2200497C3 (en)
FR (1) FR2121524B1 (en)
GB (1) GB1309721A (en)
IT (1) IT944367B (en)

Cited By (10)

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US4964844A (en) * 1987-09-05 1990-10-23 Rolls-Royce Plc Gearbox arrangement for driving coaxial contra rotating multi-bladed rotors
US6722847B2 (en) 2001-11-23 2004-04-20 Rolls-Royce Plc Fan for a turbofan gas turbine engine
GB2473530A (en) * 2009-09-09 2011-03-16 Boeing Co Aircraft propulsor with an augmentor fan circumscribing a turbofan
EP1887199A3 (en) * 2006-07-31 2013-01-23 General Electric Company Gas turbine engine assembly
US8684303B2 (en) 2008-06-02 2014-04-01 United Technologies Corporation Gas turbine engine compressor arrangement
US8756908B2 (en) 2012-05-31 2014-06-24 United Technologies Corporation Fundamental gear system architecture
US8911203B2 (en) 2009-11-20 2014-12-16 United Technologies Corporation Fan rotor support
US9840969B2 (en) 2012-05-31 2017-12-12 United Technologies Corporation Gear system architecture for gas turbine engine
US10221770B2 (en) 2012-05-31 2019-03-05 United Technologies Corporation Fundamental gear system architecture
US10451004B2 (en) 2008-06-02 2019-10-22 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine

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Also Published As

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FR2121524B1 (en) 1975-07-18
DE2200497C3 (en) 1978-06-29
DE2200497A1 (en) 1972-09-07
US3729957A (en) 1973-05-01
IT944367B (en) 1973-04-20
JPS5233323B1 (en) 1977-08-27
DE2200497B2 (en) 1977-11-10
FR2121524A1 (en) 1972-08-25

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