SG11201405143XA - Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sections - Google Patents
Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sectionsInfo
- Publication number
- SG11201405143XA SG11201405143XA SG11201405143XA SG11201405143XA SG11201405143XA SG 11201405143X A SG11201405143X A SG 11201405143XA SG 11201405143X A SG11201405143X A SG 11201405143XA SG 11201405143X A SG11201405143X A SG 11201405143XA SG 11201405143X A SG11201405143X A SG 11201405143XA
- Authority
- SG
- Singapore
- Prior art keywords
- tied
- fan
- low pressure
- multiple low
- gas turbine
- 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
- 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
- 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
- F02K3/06—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
- 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
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)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/407,899 US8915700B2 (en) | 2012-02-29 | 2012-02-29 | Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sections |
PCT/US2013/026075 WO2013165521A2 (en) | 2012-02-29 | 2013-02-14 | Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sections |
Publications (1)
Publication Number | Publication Date |
---|---|
SG11201405143XA true SG11201405143XA (en) | 2014-10-30 |
Family
ID=49003061
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SG11201405143XA SG11201405143XA (en) | 2012-02-29 | 2013-02-14 | Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sections |
Country Status (4)
Country | Link |
---|---|
US (1) | US8915700B2 (en) |
EP (1) | EP2820249B1 (en) |
SG (1) | SG11201405143XA (en) |
WO (1) | WO2013165521A2 (en) |
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US10240526B2 (en) | 2012-01-31 | 2019-03-26 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
US20150204238A1 (en) * | 2012-01-31 | 2015-07-23 | United Technologies Corporation | Low noise turbine for geared turbofan engine |
US9816442B2 (en) | 2012-01-31 | 2017-11-14 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
US9845726B2 (en) | 2012-01-31 | 2017-12-19 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
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 |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US10036316B2 (en) | 2012-10-02 | 2018-07-31 | United Technologies Corporation | Geared turbofan engine with high compressor exit temperature |
EP2904254B8 (en) * | 2012-10-02 | 2020-11-04 | Raytheon Technologies Corporation | Geared turbofan engine with high compressor exit temperature |
US9752500B2 (en) * | 2013-03-14 | 2017-09-05 | Pratt & Whitney Canada Corp. | Gas turbine engine with transmission and method of adjusting rotational speed |
US9650954B2 (en) * | 2014-02-07 | 2017-05-16 | United Technologies Corporation | Gas turbine engine with distributed fans |
US10287976B2 (en) * | 2014-07-15 | 2019-05-14 | United Technologies Corporation | Split gear system for a gas turbine engine |
EP3032084A1 (en) * | 2014-12-12 | 2016-06-15 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
EP3034849A1 (en) * | 2014-12-17 | 2016-06-22 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
US10337401B2 (en) | 2015-02-13 | 2019-07-02 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US10125722B2 (en) | 2015-02-13 | 2018-11-13 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US10100731B2 (en) * | 2015-02-13 | 2018-10-16 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US20160245184A1 (en) * | 2015-02-19 | 2016-08-25 | United Technologies Corporation | Geared turbine engine |
US11225913B2 (en) | 2015-02-19 | 2022-01-18 | Raytheon Technologies Corporation | Method of providing turbine engines with different thrust ratings |
US10161316B2 (en) | 2015-04-13 | 2018-12-25 | United Technologies Corporation | Engine bypass valve |
EP3109433B1 (en) * | 2015-06-19 | 2018-08-15 | Rolls-Royce Corporation | Engine driven by sc02 cycle with independent shafts for combustion cycle elements and propulsion elements |
US10329946B2 (en) | 2016-03-24 | 2019-06-25 | United Technologies Corporation | Sliding gear actuation for variable vanes |
US10190599B2 (en) | 2016-03-24 | 2019-01-29 | United Technologies Corporation | Drive shaft for remote variable vane actuation |
US10288087B2 (en) | 2016-03-24 | 2019-05-14 | United Technologies Corporation | Off-axis electric actuation for variable vanes |
US10301962B2 (en) | 2016-03-24 | 2019-05-28 | United Technologies Corporation | Harmonic drive for shaft driving multiple stages of vanes via gears |
US10415596B2 (en) | 2016-03-24 | 2019-09-17 | United Technologies Corporation | Electric actuation for variable vanes |
US10329947B2 (en) | 2016-03-24 | 2019-06-25 | United Technologies Corporation | 35Geared unison ring for multi-stage variable vane actuation |
US10443430B2 (en) | 2016-03-24 | 2019-10-15 | United Technologies Corporation | Variable vane actuation with rotating ring and sliding links |
US10458271B2 (en) | 2016-03-24 | 2019-10-29 | United Technologies Corporation | Cable drive system for variable vane operation |
US10443431B2 (en) | 2016-03-24 | 2019-10-15 | United Technologies Corporation | Idler gear connection for multi-stage variable vane actuation |
US10294813B2 (en) | 2016-03-24 | 2019-05-21 | United Technologies Corporation | Geared unison ring for variable vane actuation |
US10107130B2 (en) | 2016-03-24 | 2018-10-23 | United Technologies Corporation | Concentric shafts for remote independent variable vane actuation |
US10544734B2 (en) * | 2017-01-23 | 2020-01-28 | General Electric Company | Three spool gas turbine engine with interdigitated turbine section |
US10655537B2 (en) * | 2017-01-23 | 2020-05-19 | General Electric Company | Interdigitated counter rotating turbine system and method of operation |
US11421627B2 (en) | 2017-02-22 | 2022-08-23 | General Electric Company | Aircraft and direct drive engine under wing installation |
US10654577B2 (en) | 2017-02-22 | 2020-05-19 | General Electric Company | Rainbow flowpath low pressure turbine rotor assembly |
US11105269B2 (en) | 2017-05-12 | 2021-08-31 | General Electric Company | Method of control of three spool gas turbine engine |
US10711797B2 (en) | 2017-06-16 | 2020-07-14 | General Electric Company | Inlet pre-swirl gas turbine engine |
US10724435B2 (en) | 2017-06-16 | 2020-07-28 | General Electric Co. | Inlet pre-swirl gas turbine engine |
US10794396B2 (en) | 2017-06-16 | 2020-10-06 | General Electric Company | Inlet pre-swirl gas turbine engine |
US10815886B2 (en) | 2017-06-16 | 2020-10-27 | General Electric Company | High tip speed gas turbine engine |
US20210348555A1 (en) | 2020-03-26 | 2021-11-11 | Rolls-Royce Plc | High pressure ratio gas turbine engine |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
CN115405421B (en) * | 2022-11-01 | 2023-02-03 | 北京航空航天大学 | Three-rotor variable-cycle engine overall structure with interstage combustion chamber |
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US4916894A (en) | 1989-01-03 | 1990-04-17 | General Electric Company | High bypass turbofan engine having a partially geared fan drive turbine |
GB2259328B (en) | 1991-09-03 | 1995-07-19 | Gen Electric | Gas turbine engine variable bleed pivotal flow splitter |
DE4241613A1 (en) * | 1992-12-10 | 1994-06-16 | Asea Brown Boveri | Aircraft engine with fan or propeller drive - has two independently rotating coaxial shafts with fuel combustion in compressed air fuel-enriching machine with bucket wheel |
FR2826052B1 (en) * | 2001-06-19 | 2003-12-19 | Snecma Moteurs | RELIEF DEVICE FOR THE IGNITION OF A SELF-ROTATING TURBO-JET |
WO2006059996A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Balanced turbine rotor fan blade for a tip turbine engine |
WO2006059992A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Inducer for a fan blade of a tip turbine engine |
US7927075B2 (en) | 2004-12-01 | 2011-04-19 | United Technologies Corporation | Fan-turbine rotor assembly for a tip turbine engine |
US7726113B2 (en) * | 2005-10-19 | 2010-06-01 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7716914B2 (en) * | 2006-12-21 | 2010-05-18 | General Electric Company | Turbofan engine assembly and method of assembling same |
US9957918B2 (en) | 2007-08-28 | 2018-05-01 | United Technologies Corporation | Gas turbine engine front architecture |
US8887485B2 (en) | 2008-10-20 | 2014-11-18 | Rolls-Royce North American Technologies, Inc. | Three spool gas turbine engine having a clutch and compressor bypass |
US8375695B2 (en) * | 2009-06-30 | 2013-02-19 | General Electric Company | Aircraft gas turbine engine counter-rotatable generator |
US20110167791A1 (en) | 2009-09-25 | 2011-07-14 | James Edward Johnson | Convertible fan engine |
US9103227B2 (en) | 2012-02-28 | 2015-08-11 | United Technologies Corporation | Gas turbine engine with fan-tied inducer section |
-
2012
- 2012-02-29 US US13/407,899 patent/US8915700B2/en active Active
-
2013
- 2013-02-14 SG SG11201405143XA patent/SG11201405143XA/en unknown
- 2013-02-14 EP EP13784211.8A patent/EP2820249B1/en active Active
- 2013-02-14 WO PCT/US2013/026075 patent/WO2013165521A2/en active Application Filing
Also Published As
Publication number | Publication date |
---|---|
WO2013165521A2 (en) | 2013-11-07 |
WO2013165521A3 (en) | 2013-12-27 |
EP2820249A2 (en) | 2015-01-07 |
US20130223986A1 (en) | 2013-08-29 |
US8915700B2 (en) | 2014-12-23 |
EP2820249B1 (en) | 2019-10-23 |
EP2820249A4 (en) | 2015-12-23 |
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