SG11201404962PA - Geared turbofan architecture for improved thrust density - Google Patents

Geared turbofan architecture for improved thrust density

Info

Publication number
SG11201404962PA
SG11201404962PA SG11201404962PA SG11201404962PA SG11201404962PA SG 11201404962P A SG11201404962P A SG 11201404962PA SG 11201404962P A SG11201404962P A SG 11201404962PA SG 11201404962P A SG11201404962P A SG 11201404962PA SG 11201404962P A SG11201404962P A SG 11201404962PA
Authority
SG
Singapore
Prior art keywords
geared turbofan
improved thrust
thrust density
turbofan architecture
architecture
Prior art date
Application number
SG11201404962PA
Inventor
Frederick M Schwarz
Daniel Bernard Kupratis
Gabriel L Suciu
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 SG11201404962PA publication Critical patent/SG11201404962PA/en

Links

Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • 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
    • 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
SG11201404962PA 2012-02-29 2013-02-22 Geared turbofan architecture for improved thrust density SG11201404962PA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/408,109 US20130219907A1 (en) 2012-02-29 2012-02-29 Geared turbofan architecture for improved thrust density
PCT/US2013/027221 WO2013172902A1 (en) 2012-02-29 2013-02-22 Geared turbofan architecture for improved thrust density

Publications (1)

Publication Number Publication Date
SG11201404962PA true SG11201404962PA (en) 2014-10-30

Family

ID=49001340

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201404962PA SG11201404962PA (en) 2012-02-29 2013-02-22 Geared turbofan architecture for improved thrust density

Country Status (4)

Country Link
US (2) US20130219907A1 (en)
EP (1) EP2820264A4 (en)
SG (1) SG11201404962PA (en)
WO (1) WO2013172902A1 (en)

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JP6222993B2 (en) * 2013-05-28 2017-11-01 三菱日立パワーシステムズ株式会社 2-shaft gas turbine
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
US20160237903A1 (en) * 2015-02-13 2016-08-18 United Technologies Corporation High Pressure Compressor Rotor Thermal Conditioning Using Conditioned Compressor Air
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system
DE102022124926A1 (en) * 2022-09-28 2024-03-28 Rolls-Royce Deutschland Ltd & Co Kg Device for generating electrical energy for an aircraft and aircraft

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US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine
GB2259660A (en) * 1991-09-17 1993-03-24 Rolls Royce Plc A mould for casting components
US5433674A (en) * 1994-04-12 1995-07-18 United Technologies Corporation Coupling system for a planetary gear train
JPH07286503A (en) * 1994-04-20 1995-10-31 Hitachi Ltd Highly efficient gas turbine
US6647707B2 (en) 2000-09-05 2003-11-18 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
US7937927B2 (en) * 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
WO2006060005A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Fan-turbine rotor assembly with integral inducer section for a tip turbine engine
FR2879720B1 (en) * 2004-12-17 2007-04-06 Snecma Moteurs Sa COMPRESSION-EVAPORATION SYSTEM FOR LIQUEFIED GAS
US20070022735A1 (en) * 2005-07-29 2007-02-01 General Electric Company Pto assembly for a gas turbine engine
EP1934457A2 (en) * 2005-09-09 2008-06-25 Richard H. Lugg Advanced hypersonic magnetic jet/electric turbine engine
US7591754B2 (en) * 2006-03-22 2009-09-22 United Technologies Corporation Epicyclic gear train integral sun gear coupling design
US7815417B2 (en) * 2006-09-01 2010-10-19 United Technologies Corporation Guide vane for a gas turbine engine
US7632064B2 (en) * 2006-09-01 2009-12-15 United Technologies Corporation Variable geometry guide vane for a gas turbine engine
US7966806B2 (en) * 2006-10-31 2011-06-28 General Electric Company Turbofan engine assembly and method of assembling same
US7841165B2 (en) 2006-10-31 2010-11-30 General Electric Company Gas turbine engine assembly and methods of assembling same
US7882693B2 (en) * 2006-11-29 2011-02-08 General Electric Company Turbofan engine assembly and method of assembling same
US8262817B2 (en) * 2007-06-11 2012-09-11 Honeywell International Inc. First stage dual-alloy turbine wheel
US8104265B2 (en) * 2007-06-28 2012-01-31 United Technologies Corporation Gas turbines with multiple gas flow paths
US8075261B2 (en) * 2007-09-21 2011-12-13 United Technologies Corporation Gas turbine engine compressor case mounting arrangement
US8973364B2 (en) * 2008-06-26 2015-03-10 United Technologies Corporation Gas turbine engine with noise attenuating variable area fan nozzle
US8061980B2 (en) * 2008-08-18 2011-11-22 United Technologies Corporation Separation-resistant inlet duct for mid-turbine frames
US8166748B2 (en) * 2008-11-21 2012-05-01 General Electric Company Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes

Also Published As

Publication number Publication date
US20130219907A1 (en) 2013-08-29
WO2013172902A1 (en) 2013-11-21
US20130219908A1 (en) 2013-08-29
EP2820264A4 (en) 2015-11-18
EP2820264A1 (en) 2015-01-07

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