SG11201404046PA - Gas turbine engine with modular cores and propulsion unit - Google Patents

Gas turbine engine with modular cores and propulsion unit

Info

Publication number
SG11201404046PA
SG11201404046PA SG11201404046PA SG11201404046PA SG11201404046PA SG 11201404046P A SG11201404046P A SG 11201404046PA SG 11201404046P A SG11201404046P A SG 11201404046PA SG 11201404046P A SG11201404046P A SG 11201404046PA SG 11201404046P A SG11201404046P A SG 11201404046PA
Authority
SG
Singapore
Prior art keywords
gas turbine
turbine engine
propulsion unit
modular cores
cores
Prior art date
Application number
SG11201404046PA
Inventor
Gabriel L Suciu
Christopher Dye
Joseph B Staubach
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 SG11201404046PA publication Critical patent/SG11201404046PA/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
    • F02K3/06—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
    • 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
    • F02C7/04—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
    • 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
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/40—Flow geometry or direction
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/313—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being perpendicular to each other
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
SG11201404046PA 2012-02-10 2013-02-05 Gas turbine engine with modular cores and propulsion unit SG11201404046PA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/370,743 US8955304B2 (en) 2012-02-10 2012-02-10 Gas turbine engine with modular cores and propulsion unit
PCT/US2013/024720 WO2013119535A1 (en) 2012-02-10 2013-02-05 Gas turbine engine with modular cores and propulsion unit

Publications (1)

Publication Number Publication Date
SG11201404046PA true SG11201404046PA (en) 2014-10-30

Family

ID=48944486

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201404046PA SG11201404046PA (en) 2012-02-10 2013-02-05 Gas turbine engine with modular cores and propulsion unit

Country Status (5)

Country Link
US (1) US8955304B2 (en)
EP (1) EP2812557B1 (en)
CN (1) CN104093962B (en)
SG (1) SG11201404046PA (en)
WO (1) WO2013119535A1 (en)

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US10112696B2 (en) * 2012-11-12 2018-10-30 United Technologies Corporation Stabilizer sacrificial surfaces
US10001063B2 (en) * 2012-11-12 2018-06-19 United Technologies Corporation Angled core gas turbine engine mounting
US9726112B2 (en) * 2013-03-07 2017-08-08 United Technologies Corporation Reverse flow gas turbine engine airflow bypass
US9845159B2 (en) * 2013-03-07 2017-12-19 United Technologies Corporation Conjoined reverse core flow engine arrangement
US9897040B2 (en) * 2013-03-07 2018-02-20 United Technologies Corporation Rear mounted reverse core engine thrust reverser
WO2015006009A1 (en) 2013-07-08 2015-01-15 United Technologies Corporation Angled core engine
WO2015134081A2 (en) * 2013-12-13 2015-09-11 United Technologies Corporation Transverse-mounted power turbine drive system
US10024235B2 (en) * 2014-03-03 2018-07-17 United Technologies Corporation Offset core engine architecture
US10202856B2 (en) 2014-09-02 2019-02-12 United Technologies Corporation Decoupled gas turbine engine
US10415466B2 (en) * 2014-10-27 2019-09-17 United Technologies Corporation Offset cores for gas turbine engines
CN106286010B (en) * 2015-06-26 2018-10-26 中航空天发动机研究院有限公司 A kind of gear drive fanjet of reversed installation core engine
US10683809B2 (en) * 2016-05-10 2020-06-16 General Electric Company Impeller-mounted vortex spoiler
US11421627B2 (en) * 2017-02-22 2022-08-23 General Electric Company Aircraft and direct drive engine under wing installation
US20200039657A1 (en) * 2018-08-02 2020-02-06 Southwest Research Institute Variable Cycle Hybrid Power and Propulsion System for Aircraft
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
CN117320962A (en) * 2021-05-20 2023-12-29 通用电气公司 Method and apparatus for mounting a gas turbine engine
US20240141837A1 (en) * 2022-05-19 2024-05-02 Raytheon Technologies Corporation Reverse flow hydrogen steam injected turbine engine

Family Cites Families (13)

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Publication number Priority date Publication date Assignee Title
US4030288A (en) 1975-11-10 1977-06-21 Caterpillar Tractor Co. Modular gas turbine engine assembly
GB2062762B (en) 1979-11-03 1983-03-30 Rolls Royce Bearing arrangement in a modular gas turbine engine
CA1189397A (en) 1981-12-21 1985-06-25 Robert W. Voight Electronic interface for a pneumatic fuel control of a gas turbine engine
US4934140A (en) 1988-05-13 1990-06-19 United Technologies Corporation Modular gas turbine engine
WO2002081883A2 (en) * 2001-04-03 2002-10-17 Uwe Christian Seefluth Bypass flow jet engine for pre-driving aircrafts
FR2826054B1 (en) * 2001-06-14 2003-12-19 Snecma Moteurs VARIABLE CYCLE PROPULSION DEVICE BY GAS DIVERSION FOR SUPERSONIC AIRCRAFT AND OPERATING METHOD
US6971229B2 (en) 2003-02-26 2005-12-06 The Nordam Group, Inc. Confluent exhaust nozzle
GB2400411B (en) * 2003-04-10 2006-09-06 Rolls Royce Plc Turbofan arrangement
FR2858999B1 (en) * 2003-08-18 2005-11-11 Snecma Moteurs TURBOMACHINE FOR AIRCRAFT WITH REDUCED NOISE EMISSIONS
WO2006059988A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
US7802757B2 (en) 2005-11-09 2010-09-28 Pratt & Whitney Canada Corp. Method and system for taxiing an aircraft
US8336289B2 (en) 2007-08-30 2012-12-25 United Technologies Corporation Gas turbine engine systems and related methods involving multiple gas turbine cores
US8176725B2 (en) 2009-09-09 2012-05-15 United Technologies Corporation Reversed-flow core for a turbofan with a fan drive gear system

Also Published As

Publication number Publication date
EP2812557A4 (en) 2015-10-14
US20130205747A1 (en) 2013-08-15
EP2812557B1 (en) 2022-12-14
US8955304B2 (en) 2015-02-17
CN104093962A (en) 2014-10-08
EP2812557A1 (en) 2014-12-17
CN104093962B (en) 2016-04-06
WO2013119535A1 (en) 2013-08-15

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