CN1333165C - 具有串联非交叉逆向转动的低压涡轮的飞行器气体涡轮发动机 - Google Patents

具有串联非交叉逆向转动的低压涡轮的飞行器气体涡轮发动机 Download PDF

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Publication number
CN1333165C
CN1333165C CNB031548059A CN03154805A CN1333165C CN 1333165 C CN1333165 C CN 1333165C CN B031548059 A CNB031548059 A CN B031548059A CN 03154805 A CN03154805 A CN 03154805A CN 1333165 C CN1333165 C CN 1333165C
Authority
CN
China
Prior art keywords
low
pressure turbine
turbine blade
blade row
pressure
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 - Fee Related
Application number
CNB031548059A
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English (en)
Chinese (zh)
Other versions
CN1485535A (zh
Inventor
R·J·奥尔兰多
T·O·莫尼兹
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of CN1485535A publication Critical patent/CN1485535A/zh
Application granted granted Critical
Publication of CN1333165C publication Critical patent/CN1333165C/zh
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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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
    • F02K3/072—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 counter-rotating, e.g. fan rotors
    • 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
    • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
    • F01D1/26—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like traversed by the working-fluid substantially axially
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • 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

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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)
  • Turbine Rotor Nozzle Sealing (AREA)
CNB031548059A 2002-08-19 2003-08-19 具有串联非交叉逆向转动的低压涡轮的飞行器气体涡轮发动机 Expired - Fee Related CN1333165C (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/223163 2002-08-19
US10/223,163 US6711887B2 (en) 2002-08-19 2002-08-19 Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines

Publications (2)

Publication Number Publication Date
CN1485535A CN1485535A (zh) 2004-03-31
CN1333165C true CN1333165C (zh) 2007-08-22

Family

ID=31495293

Family Applications (1)

Application Number Title Priority Date Filing Date
CNB031548059A Expired - Fee Related CN1333165C (zh) 2002-08-19 2003-08-19 具有串联非交叉逆向转动的低压涡轮的飞行器气体涡轮发动机

Country Status (6)

Country Link
US (1) US6711887B2 (https=)
EP (1) EP1394385B1 (https=)
JP (1) JP4588306B2 (https=)
CN (1) CN1333165C (https=)
CA (1) CA2436664C (https=)
DE (1) DE60300804T2 (https=)

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US7458202B2 (en) * 2004-10-29 2008-12-02 General Electric Company Lubrication system for a counter-rotating turbine engine and method of assembling same
US7195446B2 (en) * 2004-10-29 2007-03-27 General Electric Company Counter-rotating turbine engine and method of assembling same
US7296398B2 (en) * 2004-10-29 2007-11-20 General Electric Company Counter-rotating turbine engine and method of assembling same
US7290386B2 (en) * 2004-10-29 2007-11-06 General Electric Company Counter-rotating gas turbine engine and method of assembling same
US7334392B2 (en) * 2004-10-29 2008-02-26 General Electric Company Counter-rotating gas turbine engine and method of assembling same
US7334981B2 (en) * 2004-10-29 2008-02-26 General Electric Company Counter-rotating gas turbine engine and method of assembling same
US7513103B2 (en) * 2005-10-19 2009-04-07 General Electric Company Gas turbine engine assembly and methods of assembling same
US7526913B2 (en) * 2005-10-19 2009-05-05 General Electric Company Gas turbine engine assembly and methods of assembling same
US7752836B2 (en) * 2005-10-19 2010-07-13 General Electric Company Gas turbine assembly and methods of assembling same
US7603844B2 (en) * 2005-10-19 2009-10-20 General Electric Company Gas turbine engine assembly and methods of assembling same
US7490461B2 (en) * 2005-10-19 2009-02-17 General Electric Company Gas turbine engine assembly and methods of assembling same
US7726113B2 (en) * 2005-10-19 2010-06-01 General Electric Company Gas turbine engine assembly and methods of assembling same
US7490460B2 (en) * 2005-10-19 2009-02-17 General Electric Company Gas turbine engine assembly and methods of assembling same
US7493754B2 (en) * 2005-10-19 2009-02-24 General Electric Company Gas turbine engine assembly and methods of assembling same
US7493753B2 (en) * 2005-10-19 2009-02-24 General Electric Company Gas turbine engine assembly and methods of assembling same
US7685808B2 (en) 2005-10-19 2010-03-30 General Electric Company Gas turbine engine assembly and methods of assembling same
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US7882693B2 (en) * 2006-11-29 2011-02-08 General Electric Company Turbofan engine assembly and method of assembling same
US7716914B2 (en) * 2006-12-21 2010-05-18 General Electric Company Turbofan engine assembly and method of assembling same
US7942632B2 (en) * 2007-06-20 2011-05-17 United Technologies Corporation Variable-shape variable-stagger inlet guide vane flap
US8105019B2 (en) * 2007-12-10 2012-01-31 United Technologies Corporation 3D contoured vane endwall for variable area turbine vane arrangement
US8015798B2 (en) * 2007-12-13 2011-09-13 United Technologies Corporation Geared counter-rotating gas turbofan engine
CN101903619B (zh) * 2007-12-20 2014-06-11 沃尔沃航空公司 燃气涡轮发动机
US8292570B2 (en) * 2008-01-25 2012-10-23 United Technologies Corporation Low pressure turbine with counter-rotating drives for single spool
US8534074B2 (en) * 2008-05-13 2013-09-17 Rolls-Royce Corporation Dual clutch arrangement and method
US20100005810A1 (en) * 2008-07-11 2010-01-14 Rob Jarrell Power transmission among shafts in a turbine engine
US8480527B2 (en) * 2008-08-27 2013-07-09 Rolls-Royce Corporation Gearing arrangement
US8075438B2 (en) * 2008-12-11 2011-12-13 Rolls-Royce Corporation Apparatus and method for transmitting a rotary input into counter-rotating outputs
US8021267B2 (en) * 2008-12-11 2011-09-20 Rolls-Royce Corporation Coupling assembly
US8191352B2 (en) * 2008-12-19 2012-06-05 General Electric Company Geared differential speed counter-rotatable low pressure turbine
US8744228B2 (en) * 2009-05-22 2014-06-03 Commscope, Inc. Of North Carolina Telecommunications patching system with cable management system and related cable management equipment
CA2819586C (en) * 2010-12-10 2014-09-16 10241423 Canada Inc. Turbine assembly, and kit with components for assembling the same
US9506402B2 (en) 2011-07-29 2016-11-29 United Technologies Corporation Three spool engine bearing configuration
US10287976B2 (en) 2014-07-15 2019-05-14 United Technologies Corporation Split gear system for a gas turbine engine
US9932902B2 (en) 2014-07-15 2018-04-03 United Technologies Corporation Turbine section support for a gas turbine engine
BE1022364B1 (fr) * 2014-10-27 2016-03-17 Techspace Aero S.A. Compresseur de turbomachine axiale avec double rotors contrarotatifs
PL412269A1 (pl) * 2015-05-11 2016-11-21 General Electric Company Zanurzony wlot kanału przepływu między łopatką wirnika i łopatką kierowniczą dla turbiny gazowej z otwartym wentylatorem
DE102016113568A1 (de) 2016-07-22 2018-01-25 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zum Herstellen eines Tandem-Leitschaufelsegments
US11053797B2 (en) * 2017-01-23 2021-07-06 General Electric Company Rotor thrust balanced turbine engine
US10654577B2 (en) * 2017-02-22 2020-05-19 General Electric Company Rainbow flowpath low pressure turbine rotor assembly
US11085309B2 (en) 2017-09-22 2021-08-10 General Electric Company Outer drum rotor assembly
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
US12071889B2 (en) 2022-04-05 2024-08-27 General Electric Company Counter-rotating turbine
US12497917B2 (en) 2022-05-18 2025-12-16 General Electric Company Counter-rotating turbine
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US12326114B2 (en) 2023-08-15 2025-06-10 Rtx Corporation Gas turbine engine with core debris protection

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Also Published As

Publication number Publication date
JP4588306B2 (ja) 2010-12-01
EP1394385A1 (en) 2004-03-03
US6711887B2 (en) 2004-03-30
CN1485535A (zh) 2004-03-31
US20040031260A1 (en) 2004-02-19
CA2436664A1 (en) 2004-02-19
DE60300804D1 (de) 2005-07-14
EP1394385B1 (en) 2005-06-08
CA2436664C (en) 2009-09-22
JP2004076739A (ja) 2004-03-11
DE60300804T2 (de) 2006-03-23

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C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant
C17 Cessation of patent right
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20070822

Termination date: 20110819