US3729957A - Fan - Google Patents

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Publication number
US3729957A
US3729957A US00210490A US3729957DA US3729957A US 3729957 A US3729957 A US 3729957A US 00210490 A US00210490 A US 00210490A US 3729957D A US3729957D A US 3729957DA US 3729957 A US3729957 A US 3729957A
Authority
US
United States
Prior art keywords
fan
gas generator
rotor stage
stage
gear
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 - Lifetime
Application number
US00210490A
Other languages
English (en)
Inventor
J Petrie
K Bracey
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.)
UK Secretary of State for Defence
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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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Application granted granted Critical
Publication of US3729957A publication Critical patent/US3729957A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

Definitions

  • a fan comprises first and second rotor stages driven Jan. 8, 1971 Great Britain ..975/71 hr ugh a ifferential gear.
  • the first stage is driven from the sun gear of the differential while the second [52] US. Cl. ..60/226 R, 60/268, 60/39.16 C, stage is driven from the annulus gear of the dif- 74/665 415/122 ferential.
  • the planet carrier is driven from drive [51] Int. Cl. ..F02k 3/06, Fl6h 37/06 means
  • the invention is particularly applicable m gas [58] Field of Search ..60/226 R, 268, 39.16 C;
  • the first stage of the fan may comprise a hub compressor and the drive means may comprise a gas turbine.
  • This invention relates to a fan which is particularly but not exclusively useful in a gas turbine engine.
  • Fans having large capacity are useful in a number of applications and particularly in high by-passratio gas turbine engines.
  • To produce the high capacity it has been the practice to increase the overall diameter of the fans, while to reduce complications entailed with very large hubs it has been the practice to make the hub of a fairly small size.
  • a problem then arises in that to avoid the production of large amounts of noise the tip speed of the fan blades must be less than the speed of sound; this therefore puts a limit on the rotational speed of the fan and consequently causes the inner sections of the fan blades to be moving so slowly that it is difficult to cause them to operate effectively.
  • One solution which has been proposed is to provide an additional fan stage whose diameter is considerably less than that of the main fan, this hub compressor being driven with the main fan or in some cases by a separate turbine.
  • the hub compressor then restores the efficiency of the central portion of the fan, but entails some complication in drive.
  • the present invention provides a fan having such a hub compressor and having a very simple drive which divides the torque available between the main fan and the hub compressor.
  • a fan comprises a first and second rotor stage in flow series and a differential gear comprising a sun gear, a plurality of planet gears carried from a planet carrier, and an annulus gear, the first rotor stage being connected to the sun gear, the second rotor stage being drivingly connected to the annulus gear and drive means connected to rotate the planet carrier.
  • Said first rotor stage may comprise a hub compressor and said second stage may comprise a main rotor stage, the blades of the hub compressor extending over only the central portion of the main rotor stage.
  • the drive means will normally comprise a turbine of the engine.
  • the hub compressor is preferably shrouded; thus the shroud may be carried from the main rotor stage and extend forwardly to encompass the hub compressor.
  • the fan is mounted coaxially with a gas generator section so that the fan compresses air which provides by-pass air and also supercharged inlet air to the gas generator.
  • the gas generator is a two-shaft gas generator and comprises a low pressure turbine which drives the planet carrier.
  • FIG. 1 is a partly broken away view of a gas turbine engine having a fan in accordance with the invention and FIG. 2 is an enlarged view of the fan portion of the engine ofFlG. 1.
  • FIG. 1 shows a gas turbine engine comprising .a gas generator section 10 and a fan generally indicated at 11.
  • the fan compresses air part of which supercharges the gas generator 10 while the remainder passes between the gas generator and a fan cowl 12 to provide propulsive thrust.
  • the gas generator is a two-shaft gas generator; that is it comprises intermediate pressure and high pressure compressors l3 and 14 drivingly connected to intermediate and high pressure turbines 16 and 15 respectively.
  • a third, low pressure turbine 17 is provided and drives an LP shaft 18 which extends coaxially inside the gas generator shafts to drive the fan.
  • the arrangement of the fan is best seen in FIG. 2.
  • the fan comprises a main fan rotor 20 made up of a plurality of blades which carry part way along their extent a shroud ring 21.
  • a hub compressor 22 which again comprises a plurality of rotor blades which only extend over the central part of the main fan rotor 20.
  • the hub compressor 22 is driven from a shaft 23 which is mounted in bearings 24 and 25.
  • the bearing 24 supports the shaft 23 from the shaft 26 of the main fan 20, and this shaft is in turn supported by the bearing 27 from fixed structure of the engine.
  • the shaft 26 supports bearings 29 and 30 whose purpose will become apparent below.
  • the shaft 23 is provided with an external set of teeth .at 31 which form the sun wheel of an epicyclic differential gear.
  • the shaft 26 is attached to an annulus gear 32 whose internal teeth form the annulus gear of the same differential.
  • a plurality of pinions 33 mesh between the sun gear 31 and annulus 32, these components being carried on a pinion carrier 34.
  • the carrier is extended forwardly to mount within the bearing 29 mentioned above, while the rearward portion extends to form the LP shaft 18. This rearward extension is supported in the bearing 30 and itself supports the bearing 25 of the shaft 23.
  • Shaft 18 is driven by the LP turbine and consequently drives the planet carrier 34.
  • Rotation of this carrier causes the pinions to rotate about the fan axis and causes equal driving loads to be exerted on the sun wheel 31 and the annulus gear 32. Because of the difference in the diameters of these wheels, a greater torque will be exerted on the annulus gear than on the sun wheel; consequently more power is passed into the main fan rotor than into the hub compressor. This is the desired splitting of work.
  • Theaerodynamics of the fan and hub compressor are arranged so that at designed speed for the turbine the fan will rotate at a fairly slow speed, thus avoiding any danger of sonic or near sonic fan speeds which would produce noise.
  • the hub compressor is arranged to rotate considerably faster, since with its relatively small diameter blades there is little chance of its blades going sonic. Since the hub compressor rotates at a relatively high speed it can be reasonably efficient over its radial extent; it therefore makes up for the relative inefficiency of the central section of the fan blades. In fact the inner portion of the fan blades may be made simply as struts which perform no work on the air which has been compressed by the hub compressor.
  • this invention is particularly relevant to the fans of gas turbine engines but can be applied to other fans, particularly propulsive fans which may be used for VTO application etc. In any of these cases it is only necessary to provide the drive in the form of a single shaft, the gear arrangement of the invention providing the necessary splitting of power.
  • a fan comprising a first and a second rotor stage in flow series and a differential gear comprising a sun gear, a plurality of planet gears carried from a planet carrier, and an annulus gear, first connection means by which the first rotor stage is connected to the sun gear, second connection means by which the second rotor stage is drivingly connected to the annulus gear and drive means connected to rotate the planetcarrier.
  • the second stage comprises a main bladed rotor stage, the blades of the hub compressor extending over only the central portion of the-main rotor stage.

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  • 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)
US00210490A 1971-01-08 1971-12-21 Fan Expired - Lifetime US3729957A (en)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
US3729957A true US3729957A (en) 1973-05-01

Family

ID=9713823

Family Applications (1)

Application Number Title Priority Date Filing Date
US00210490A Expired - Lifetime US3729957A (en) 1971-01-08 1971-12-21 Fan

Country Status (6)

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

Cited By (158)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3861139A (en) * 1973-02-12 1975-01-21 Gen Electric Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
US4005575A (en) * 1974-09-11 1977-02-01 Rolls-Royce (1971) Limited Differentially geared reversible fan for ducted fan gas turbine engines
US4254619A (en) * 1978-05-01 1981-03-10 General Electric Company Partial span inlet guide vane for cross-connected engines
US4286430A (en) * 1979-09-17 1981-09-01 Teledyne Industries, Inc. Gas turbine engine
US4563129A (en) * 1983-12-08 1986-01-07 United Technologies Corporation Integrated reduction gear and counterrotation propeller
US4751816A (en) * 1986-10-08 1988-06-21 Rolls-Royce Plc Turbofan gas turbine engine
US4767270A (en) * 1986-04-16 1988-08-30 The Boeing Company Hoop fan jet engine
US4916894A (en) * 1989-01-03 1990-04-17 General Electric Company High bypass turbofan engine having a partially geared fan drive turbine
US4969325A (en) * 1989-01-03 1990-11-13 General Electric Company Turbofan engine having a counterrotating partially geared fan drive turbine
US5010729A (en) * 1989-01-03 1991-04-30 General Electric Company Geared counterrotating turbine/fan propulsion system
US5261227A (en) * 1992-11-24 1993-11-16 General Electric Company Variable specific thrust turbofan engine
US5388964A (en) * 1993-09-14 1995-02-14 General Electric Company Hybrid rotor blade
US5649419A (en) * 1995-01-27 1997-07-22 The Boeing Company Rotating acoustically lined inlet splitter for a turbo-fan engine
US6209311B1 (en) * 1998-04-13 2001-04-03 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
US20040011019A1 (en) * 2000-10-17 2004-01-22 Schoettler Michael Device and method for preheating combustibles in combined gas and steam turbine installations
US20040216445A1 (en) * 2003-04-30 2004-11-04 Anthony Jones Combined stage single shaft turbofan engine
US20040255590A1 (en) * 2003-06-23 2004-12-23 Pratt & Whiney Canada Corp. Differential geared turbine engine with torque modulation capability
US20050241292A1 (en) * 2004-03-19 2005-11-03 Rolls-Royce Plc Turbine engine arrangements
US20060024162A1 (en) * 2004-07-30 2006-02-02 Giffin Rollin G Method and apparatus for assembling gas turbine engines
US20060059887A1 (en) * 2004-09-03 2006-03-23 Hermann Klingels Aircraft engine with separate auxiliary rotor and fan rotor
US20060093469A1 (en) * 2004-10-29 2006-05-04 Moniz Thomas O Counter-rotating gas turbine engine and method of assembling same
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US20060242943A1 (en) * 2005-04-29 2006-11-02 General Electric Company Supersonic missile turbojet engine
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US20130219859A1 (en) * 2012-02-29 2013-08-29 Gabriel L. Suciu Counter rotating low pressure compressor and turbine each having a gear system
US20130224049A1 (en) * 2012-02-29 2013-08-29 Frederick M. Schwarz Lightweight fan driving turbine
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US20130287545A1 (en) * 2012-04-25 2013-10-31 Gabriel L. Suciu Geared turbofan with three turbines all counter-rotating
WO2013165862A1 (en) 2012-04-30 2013-11-07 United Technologies Corporation Geared turbofan with three turbines all co-rotating
US20130298522A1 (en) * 2012-05-11 2013-11-14 Andreas Eleftheriou Geared fan assembly
US20130318998A1 (en) * 2012-05-31 2013-12-05 Frederick M. Schwarz Geared turbofan with three turbines with high speed fan drive turbine
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
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DE2200497C3 (de) 1978-06-29
FR2121524A1 (de) 1972-08-25
IT944367B (it) 1973-04-20
FR2121524B1 (de) 1975-07-18
GB1309721A (en) 1973-03-14
DE2200497B2 (de) 1977-11-10
DE2200497A1 (de) 1972-09-07
JPS5233323B1 (de) 1977-08-27

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