SG11201402895RA - Gas turbine engine with low fan pressure ratio - Google Patents
Gas turbine engine with low fan pressure ratioInfo
- Publication number
- SG11201402895RA SG11201402895RA SG11201402895RA SG11201402895RA SG11201402895RA SG 11201402895R A SG11201402895R A SG 11201402895RA SG 11201402895R A SG11201402895R A SG 11201402895RA SG 11201402895R A SG11201402895R A SG 11201402895RA SG 11201402895R A SG11201402895R A SG 11201402895RA
- Authority
- SG
- Singapore
- Prior art keywords
- gas turbine
- turbine engine
- pressure ratio
- fan pressure
- low fan
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
- F02K1/16—Control or regulation conjointly with another control
-
- 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
- F02K3/075—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 controlling flow ratio between flows
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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
-
- 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
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
- F05D2270/3015—Pressure differential pressure
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/340,761 US8459035B2 (en) | 2007-07-27 | 2011-12-30 | Gas turbine engine with low fan pressure ratio |
PCT/US2012/071901 WO2013141930A1 (en) | 2011-12-30 | 2012-12-28 | Gas turbine engine with low fan pressure ratio |
Publications (1)
Publication Number | Publication Date |
---|---|
SG11201402895RA true SG11201402895RA (en) | 2014-10-30 |
Family
ID=49223143
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SG11201402895RA SG11201402895RA (en) | 2011-12-30 | 2012-12-28 | Gas turbine engine with low fan pressure ratio |
Country Status (4)
Country | Link |
---|---|
EP (2) | EP2798183B8 (en) |
CN (1) | CN104011358B (en) |
SG (1) | SG11201402895RA (en) |
WO (1) | WO2013141930A1 (en) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013154639A2 (en) * | 2012-01-31 | 2013-10-17 | United Technologies Corporation | Gas turbine engine with improved fuel efficiency |
US20160186657A1 (en) * | 2014-11-21 | 2016-06-30 | General Electric Company | Turbine engine assembly and method of manufacturing thereof |
US20160333729A1 (en) * | 2015-05-11 | 2016-11-17 | General Electric Company | Turbine engine having variable pitch outlet guide vanes |
CN106934074B (en) * | 2015-12-29 | 2020-07-31 | 中国航发商用航空发动机有限责任公司 | Global optimal turbofan engine air inlet channel noise reduction design method |
CN105673251A (en) * | 2016-01-13 | 2016-06-15 | 中国航空动力机械研究所 | Fan pressure boosting stage and turbofan engine |
US20180208297A1 (en) * | 2017-01-20 | 2018-07-26 | General Electric Company | Nacelle for an aircraft aft fan |
CN108626023B (en) * | 2017-03-23 | 2019-12-10 | 中国航发商用航空发动机有限责任公司 | turbofan engine with large bypass ratio and exhaust device with variable bypass exhaust area |
FR3083260B1 (en) | 2018-06-28 | 2020-06-19 | Safran Aircraft Engines | MODULE OF A DOUBLE FLOW AIRCRAFT ENGINE WITH AN INTEGRATED ARM OF A STATOR VANE |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5655360A (en) * | 1995-05-31 | 1997-08-12 | General Electric Company | Thrust reverser with variable nozzle |
CN1453446A (en) * | 2002-04-23 | 2003-11-05 | 闵瑜 | Intelligent lock system |
GB2401654B (en) * | 2003-05-14 | 2006-04-19 | Rolls Royce Plc | A stator vane assembly for a turbomachine |
US7845902B2 (en) * | 2005-02-15 | 2010-12-07 | Massachusetts Institute Of Technology | Jet engine inlet-fan system and design method |
US7374403B2 (en) * | 2005-04-07 | 2008-05-20 | General Electric Company | Low solidity turbofan |
US8601786B2 (en) * | 2006-10-12 | 2013-12-10 | United Technologies Corporation | Operational line management of low pressure compressor in a turbofan engine |
US7877980B2 (en) * | 2006-12-28 | 2011-02-01 | General Electric Company | Convertible gas turbine engine |
FR2910937B1 (en) | 2007-01-02 | 2009-04-03 | Airbus France Sas | AIRCRAFT REACTOR NACELLE AND AIRCRAFT COMPRISING SUCH A NACELLE |
US7721549B2 (en) * | 2007-02-08 | 2010-05-25 | United Technologies Corporation | Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system |
US7950237B2 (en) * | 2007-06-25 | 2011-05-31 | United Technologies Corporation | Managing spool bearing load using variable area flow nozzle |
US8347633B2 (en) * | 2007-07-27 | 2013-01-08 | United Technologies Corporation | Gas turbine engine with variable geometry fan exit guide vane system |
US20110120078A1 (en) * | 2009-11-24 | 2011-05-26 | Schwark Jr Fred W | Variable area fan nozzle track |
-
2012
- 2012-12-28 EP EP12872281.6A patent/EP2798183B8/en active Active
- 2012-12-28 EP EP20210919.5A patent/EP3812570B1/en active Active
- 2012-12-28 CN CN201280065386.3A patent/CN104011358B/en active Active
- 2012-12-28 WO PCT/US2012/071901 patent/WO2013141930A1/en active Application Filing
- 2012-12-28 SG SG11201402895RA patent/SG11201402895RA/en unknown
Also Published As
Publication number | Publication date |
---|---|
EP2798183A4 (en) | 2015-08-05 |
EP2798183A1 (en) | 2014-11-05 |
EP2798183B8 (en) | 2021-01-20 |
EP3812570B1 (en) | 2024-02-21 |
EP2798183B1 (en) | 2020-12-02 |
EP3812570A1 (en) | 2021-04-28 |
WO2013141930A1 (en) | 2013-09-26 |
CN104011358B (en) | 2017-05-03 |
CN104011358A (en) | 2014-08-27 |
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