SG11201404090SA - Gas turbine engine with separate core and propulsion unit - Google Patents
Gas turbine engine with separate core and propulsion unitInfo
- 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
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)
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 (en) | 2012-02-10 | 2013-02-05 | Gas turbine engine with separate core and propulsion unit |
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 (en) |
EP (1) | EP2812558B1 (en) |
CN (1) | CN104220738B (en) |
SG (1) | SG11201404090SA (en) |
WO (1) | WO2013119527A1 (en) |
Families Citing this family (18)
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 |
WO2014074149A1 (en) * | 2012-11-12 | 2014-05-15 | United Technologies Corporation | Stabilizer sacrificial surfaces |
WO2014074143A1 (en) * | 2012-11-12 | 2014-05-15 | United Technologies Corporation | Aircraft with forward sweeping t-tail |
US20140252160A1 (en) * | 2013-03-07 | 2014-09-11 | United Technologies Corporation | Reverse flow gas turbine engine removable core |
US9574520B2 (en) * | 2013-03-07 | 2017-02-21 | United Technologies Corporation | Reverse core engine thrust reverser for under wing |
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 |
EP3019716B1 (en) * | 2013-07-08 | 2018-12-12 | United Technologies Corporation | Angled core engine |
US10156206B2 (en) * | 2013-10-24 | 2018-12-18 | United Technologies Corporation | Pivoting blocker door |
EP3080424B1 (en) * | 2013-12-13 | 2022-05-04 | Raytheon Technologies Corporation | Architecture for an axially compact, high performance propulsion system |
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 (en) * | 2015-12-15 | 2017-06-16 | Airbus Operations Sas | MULTI-AXIAL TURBOREACTOR AND REAR AIRCRAFT PART PROVIDED WITH SUCH TURBOJET ENGINES |
CN110905659A (en) * | 2016-02-18 | 2020-03-24 | Apgn公司 | Gas turbine blower/pump |
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 |
Family Cites Families (16)
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 (en) | 1981-12-21 | 1985-06-25 | Robert W. Voight | Electronic interface for a pneumatic fuel control of a gas turbine engine |
US6571563B2 (en) | 2000-12-19 | 2003-06-03 | Honeywell Power Systems, Inc. | Gas turbine engine with offset shroud |
FR2826054B1 (en) * | 2001-06-14 | 2003-12-19 | Snecma Moteurs | VARIABLE CYCLE PROPULSION DEVICE BY GAS DIVERSION FOR SUPERSONIC AIRCRAFT AND OPERATING METHOD |
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 (en) * | 2003-08-18 | 2005-11-11 | Snecma Moteurs | TURBOMACHINE FOR AIRCRAFT WITH REDUCED NOISE EMISSIONS |
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 |
-
2012
- 2012-02-10 US US13/370,750 patent/US8789354B2/en active Active
-
2013
- 2013-02-05 EP EP13747051.4A patent/EP2812558B1/en active Active
- 2013-02-05 WO PCT/US2013/024704 patent/WO2013119527A1/en active Application Filing
- 2013-02-05 CN CN201380008749.4A patent/CN104220738B/en active Active
- 2013-02-05 SG SG11201404090SA patent/SG11201404090SA/en unknown
Also Published As
Publication number | Publication date |
---|---|
US20130205752A1 (en) | 2013-08-15 |
US8789354B2 (en) | 2014-07-29 |
EP2812558A4 (en) | 2015-11-04 |
EP2812558A1 (en) | 2014-12-17 |
EP2812558B1 (en) | 2019-04-03 |
CN104220738A (en) | 2014-12-17 |
WO2013119527A1 (en) | 2013-08-15 |
CN104220738B (en) | 2017-07-11 |
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