SG11201405924VA - Geared turbofan with three co-rotating turbines - Google Patents

Geared turbofan with three co-rotating turbines

Info

Publication number
SG11201405924VA
SG11201405924VA SG11201405924VA SG11201405924VA SG11201405924VA SG 11201405924V A SG11201405924V A SG 11201405924VA SG 11201405924V A SG11201405924V A SG 11201405924VA SG 11201405924V A SG11201405924V A SG 11201405924VA SG 11201405924V A SG11201405924V A SG 11201405924VA
Authority
SG
Singapore
Prior art keywords
geared turbofan
rotating turbines
turbines
rotating
turbofan
Prior art date
Application number
SG11201405924VA
Inventor
Frederick M Schwarz
Daniel Bernard Kupratis
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of SG11201405924VA publication Critical patent/SG11201405924VA/en

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
    • F02K3/075—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 controlling flow ratio between flows
    • 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
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • 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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • 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
SG11201405924VA 2012-04-02 2013-03-29 Geared turbofan with three co-rotating turbines SG11201405924VA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/437,304 US10036351B2 (en) 2012-04-02 2012-04-02 Geared turbofan with three co-rotating turbines
PCT/US2013/034537 WO2014007896A2 (en) 2012-04-02 2013-03-29 Geared turbofan with three co-rotating turbines

Publications (1)

Publication Number Publication Date
SG11201405924VA true SG11201405924VA (en) 2014-10-30

Family

ID=49233012

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201405924VA SG11201405924VA (en) 2012-04-02 2013-03-29 Geared turbofan with three co-rotating turbines

Country Status (4)

Country Link
US (1) US10036351B2 (en)
EP (2) EP2834493B1 (en)
SG (1) SG11201405924VA (en)
WO (1) WO2014007896A2 (en)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11149650B2 (en) * 2007-08-01 2021-10-19 Raytheon Technologies Corporation Turbine section of high bypass turbofan
US11242805B2 (en) * 2007-08-01 2022-02-08 Raytheon Technologies Corporation Turbine section of high bypass turbofan
US20150377123A1 (en) 2007-08-01 2015-12-31 United Technologies Corporation Turbine section of high bypass turbofan
US11486311B2 (en) * 2007-08-01 2022-11-01 Raytheon Technologies Corporation Turbine section of high bypass turbofan
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US20150345426A1 (en) 2012-01-31 2015-12-03 United Technologies Corporation Geared turbofan gas turbine engine architecture
US20150204238A1 (en) * 2012-01-31 2015-07-23 United Technologies Corporation Low noise turbine for geared turbofan engine
US8935913B2 (en) 2012-01-31 2015-01-20 United Technologies Corporation Geared turbofan gas turbine engine architecture
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US10138809B2 (en) 2012-04-02 2018-11-27 United Technologies Corporation Geared turbofan engine with a high ratio of thrust to turbine volume
US11719161B2 (en) 2013-03-14 2023-08-08 Raytheon Technologies Corporation Low noise turbine for geared gas turbine engine
US10605172B2 (en) 2013-03-14 2020-03-31 United Technologies Corporation Low noise turbine for geared gas turbine engine
CA2879244C (en) * 2014-01-21 2018-04-03 United Technologies Corporation Low noise compressor rotor for geared turbofan engine
CA2916866C (en) * 2015-01-09 2020-02-18 United Technologies Corporation Geared turbofan engine with power density range
CA2915343A1 (en) * 2015-01-09 2016-07-09 Frederick M. Schwarz Geared turbofan engine with a high ratio of thrust to turbine volume
CA2923331A1 (en) * 2015-03-19 2016-09-19 David P. Houston Geared turbofan gas turbine engine architecture
CN112196671B (en) * 2020-09-18 2021-08-20 中国航发四川燃气涡轮研究院 Adjustable internal and external culvert force transmission mechanism

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3287906A (en) 1965-07-20 1966-11-29 Gen Motors Corp Cooled gas turbine vanes
GB1436796A (en) * 1972-08-22 1976-05-26 Mtu Muenchen Gmbh Gas turbine ducted fan engines of multi-shaft and multi-flow construction
GB1516041A (en) 1977-02-14 1978-06-28 Secr Defence Multistage axial flow compressor stators
GB2041090A (en) 1979-01-31 1980-09-03 Rolls Royce By-pass gas turbine engines
US4651521A (en) 1985-11-21 1987-03-24 Avco Corporation Convertible turbo-fan, turbo-shaft aircraft propulsion system
US5160251A (en) 1991-05-13 1992-11-03 General Electric Company Lightweight engine turbine bearing support assembly for withstanding radial and axial loads
US5388964A (en) 1993-09-14 1995-02-14 General Electric Company Hybrid rotor blade
EP0839285B1 (en) 1994-12-14 2001-07-18 United Technologies Corporation Compressor stall and surge control using airflow asymmetry measruement
US5806303A (en) 1996-03-29 1998-09-15 General Electric Company Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle
EP1780387A3 (en) 2000-09-05 2007-07-18 Sudarshan Paul Dev Nested core gas turbine engine
US6732502B2 (en) 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor
FR2866387B1 (en) 2004-02-12 2008-03-14 Snecma Moteurs AERODYNAMIC ADAPTATION OF THE BACK BLOW OF A DOUBLE BLOWER TURBOREACTOR
US7594388B2 (en) 2005-06-06 2009-09-29 General Electric Company Counterrotating turbofan engine
WO2007038674A1 (en) 2005-09-28 2007-04-05 Entrotech Composites, Llc Braid-reinforced composites and processes for their preparation
DE102006021436A1 (en) * 2006-05-09 2007-11-15 Mtu Aero Engines Gmbh Gas turbine engine
US7594404B2 (en) 2006-07-27 2009-09-29 United Technologies Corporation Embedded mount for mid-turbine frame
US7632064B2 (en) * 2006-09-01 2009-12-15 United Technologies Corporation Variable geometry guide vane for a gas turbine engine
US7905083B2 (en) * 2006-10-31 2011-03-15 General Electric Company Turbofan engine assembly and method of assembling same
US8017188B2 (en) 2007-04-17 2011-09-13 General Electric Company Methods of making articles having toughened and untoughened regions
US8015798B2 (en) 2007-12-13 2011-09-13 United Technologies Corporation Geared counter-rotating gas turbofan engine
EP2177735A3 (en) * 2008-10-20 2012-02-15 Rolls-Royce North American Technologies, Inc. Turbofan
US8191352B2 (en) 2008-12-19 2012-06-05 General Electric Company Geared differential speed counter-rotatable low pressure turbine
US8172716B2 (en) 2009-06-25 2012-05-08 United Technologies Corporation Epicyclic gear system with superfinished journal bearing
US8176725B2 (en) 2009-09-09 2012-05-15 United Technologies Corporation Reversed-flow core for a turbofan with a fan drive gear system
US8887487B2 (en) * 2012-01-31 2014-11-18 United Technologies Corporation Geared turbofan gas turbine engine architecture

Also Published As

Publication number Publication date
EP2834493A2 (en) 2015-02-11
EP2834493A4 (en) 2015-04-15
WO2014007896A2 (en) 2014-01-09
EP2834493B1 (en) 2019-07-17
US10036351B2 (en) 2018-07-31
WO2014007896A3 (en) 2014-04-10
EP3591190A1 (en) 2020-01-08
US20130255219A1 (en) 2013-10-03
EP3591190B1 (en) 2023-09-06

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