SG11201404090SA - Gas turbine engine with separate core and propulsion unit - Google Patents

Gas turbine engine with separate core and propulsion unit

Info

Publication number
SG11201404090SA
SG11201404090SA SG11201404090SA SG11201404090SA SG11201404090SA SG 11201404090S A SG11201404090S A SG 11201404090SA SG 11201404090S A SG11201404090S A SG 11201404090SA SG 11201404090S A SG11201404090S A SG 11201404090SA SG 11201404090S A SG11201404090S A SG 11201404090SA
Authority
SG
Singapore
Prior art keywords
gas turbine
turbine engine
propulsion unit
separate core
core
Prior art date
Application number
SG11201404090SA
Other languages
English (en)
Inventor
Gabriel L Suciu
Wesley K Lord
Christopher Dye
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 SG11201404090SA publication Critical patent/SG11201404090SA/en

Links

Classifications

    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/145—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chamber being in the reverse flow-type
    • 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
    • F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
    • 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

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)
SG11201404090SA 2012-02-10 2013-02-05 Gas turbine engine with separate core and propulsion unit SG11201404090SA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/370,750 US8789354B2 (en) 2012-02-10 2012-02-10 Gas turbine engine with separate core and propulsion unit
PCT/US2013/024704 WO2013119527A1 (fr) 2012-02-10 2013-02-05 Moteur à turbine à gaz à ensemble haute pression et unité de propulsion distincts

Publications (1)

Publication Number Publication Date
SG11201404090SA true SG11201404090SA (en) 2014-10-30

Family

ID=48944488

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201404090SA SG11201404090SA (en) 2012-02-10 2013-02-05 Gas turbine engine with separate core and propulsion unit

Country Status (5)

Country Link
US (1) US8789354B2 (fr)
EP (1) EP2812558B1 (fr)
CN (1) CN104220738B (fr)
SG (1) SG11201404090SA (fr)
WO (1) WO2013119527A1 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140053533A1 (en) * 2012-08-21 2014-02-27 Gabriel L. Suciu Reverse flow gas turbine engine with thrust reverser
US9637218B2 (en) * 2012-11-12 2017-05-02 United Technologies Corporation Aircraft with forward sweeping T-tail
US10112696B2 (en) * 2012-11-12 2018-10-30 United Technologies Corporation Stabilizer sacrificial surfaces
US9574520B2 (en) * 2013-03-07 2017-02-21 United Technologies Corporation Reverse core engine thrust reverser for under wing
US20140252160A1 (en) * 2013-03-07 2014-09-11 United Technologies Corporation Reverse flow gas turbine engine removable core
US9897040B2 (en) * 2013-03-07 2018-02-20 United Technologies Corporation Rear mounted reverse core engine thrust reverser
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
WO2015006009A1 (fr) * 2013-07-08 2015-01-15 United Technologies Corporation Bloc réacteur incliné
US10156206B2 (en) * 2013-10-24 2018-12-18 United Technologies Corporation Pivoting blocker door
WO2015088606A2 (fr) * 2013-12-13 2015-06-18 United Technologies Corporation Architecture pour un système de propulsion axialement compact et à performances élevées
US10024235B2 (en) * 2014-03-03 2018-07-17 United Technologies Corporation Offset core engine architecture
US10087886B2 (en) * 2014-05-22 2018-10-02 United Technologies Corporation Turbofan thrust reverser system
US10202856B2 (en) 2014-09-02 2019-02-12 United Technologies Corporation Decoupled gas turbine engine
FR3045010A1 (fr) * 2015-12-15 2017-06-16 Airbus Operations Sas Turboreacteur multi-axial et partie arriere d'aeronef pourvue de tels turboreacteurs
CN110905659A (zh) * 2016-02-18 2020-03-24 Apgn公司 燃气涡轮鼓风机/泵
US10533559B2 (en) * 2016-12-20 2020-01-14 Pratt & Whitney Canada Corp. Reverse flow engine architecture
US10746188B2 (en) * 2017-03-14 2020-08-18 Pratt & Whitney Canada Corp. Inter-shaft bearing connected to a compressor boost system
US12221932B1 (en) * 2024-04-30 2025-02-11 Saudi Arabian Oil Company Integrated gas turbine energy recovery system for efficiency enhancement

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3068647A (en) 1960-03-23 1962-12-18 Ling Temco Vought Inc Propulsion and control system for multi-engine turbine powered aircraft
US3318095A (en) * 1964-05-14 1967-05-09 Bristol Siddeley Engines Ltd Jet propulsion plant for aircraft with gas turbine engine and with fan driven by exhaust of such engine
GB1024969A (en) * 1964-09-14 1966-04-06 Rolls Royce Helicopter power plant
US3893638A (en) * 1974-02-14 1975-07-08 Boeing Co Dual cycle fan jet engine for stol aircraft with augmentor wings
GB1545365A (en) * 1977-02-24 1979-05-10 Rolls Royce Gas turbine engines
CA1189397A (fr) 1981-12-21 1985-06-25 Robert W. Voight Interface electronique pour regulateur pneumatique d'admission du carburant d'un turbomoteur a gaz
US6571563B2 (en) 2000-12-19 2003-06-03 Honeywell Power Systems, Inc. Gas turbine engine with offset shroud
FR2826054B1 (fr) * 2001-06-14 2003-12-19 Snecma Moteurs Dispositif de propulsion a cycle variable par derivation de gaz pour avion supersonique et procede de fonctionnement
US6735954B2 (en) 2001-12-21 2004-05-18 Pratt & Whitney Canada Corp. Offset drive for gas turbine engine
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
US6895741B2 (en) * 2003-06-23 2005-05-24 Pratt & Whitney Canada Corp. Differential geared turbine engine with torque modulation capability
FR2858999B1 (fr) * 2003-08-18 2005-11-11 Snecma Moteurs Turbomachine pour aeronef a emissions de bruit reduites
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
EP2812558B1 (fr) 2019-04-03
US8789354B2 (en) 2014-07-29
WO2013119527A1 (fr) 2013-08-15
EP2812558A4 (fr) 2015-11-04
CN104220738B (zh) 2017-07-11
EP2812558A1 (fr) 2014-12-17
CN104220738A (zh) 2014-12-17
US20130205752A1 (en) 2013-08-15

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