SG11201402895RA - Gas turbine engine with low fan pressure ratio - Google Patents

Gas turbine engine with low fan pressure ratio

Info

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
Application number
SG11201402895RA
Other languages
English (en)
Inventor
Peter G Smith
Stuart S Ochs
Frederick M Schwarz
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
Priority claimed from US13/340,761 external-priority patent/US8459035B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of SG11201402895RA publication Critical patent/SG11201402895RA/en

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)
SG11201402895RA 2011-12-30 2012-12-28 Gas turbine engine with low fan pressure ratio SG11201402895RA (en)

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 (fr) 2011-12-30 2012-12-28 Turbomoteur à faible rapport de pression de soufflante

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 (fr)
CN (1) CN104011358B (fr)
SG (1) SG11201402895RA (fr)
WO (1) WO2013141930A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013154639A2 (fr) * 2012-01-31 2013-10-17 United Technologies Corporation Turbine à gaz dotée d'une efficience énergétique améliorée
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 (zh) * 2015-12-29 2020-07-31 中国航发商用航空发动机有限责任公司 全局最优涡扇发动机进气道减噪设计方法
CN105673251A (zh) * 2016-01-13 2016-06-15 中国航空动力机械研究所 风扇增压级以及涡扇发动机
US20180208297A1 (en) * 2017-01-20 2018-07-26 General Electric Company Nacelle for an aircraft aft fan
CN108626023B (zh) * 2017-03-23 2019-12-10 中国航发商用航空发动机有限责任公司 大涵道比涡扇发动机及其可变外涵排气面积的排气装置
FR3083260B1 (fr) * 2018-06-28 2020-06-19 Safran Aircraft Engines Module d’un moteur d’aeronef a double flux dont un bras integre une aube de stator

Family Cites Families (12)

* Cited by examiner, † Cited by third party
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 (zh) * 2002-04-23 2003-11-05 闵瑜 智能锁具系统
GB2420157B (en) * 2003-05-14 2006-06-28 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
WO2008045058A1 (fr) * 2006-10-12 2008-04-17 United Technologies Corporation Gestion de la ligne de fonctionnement d'un compresseur basse pression dans un moteur de turboréacteur à double flux
US7877980B2 (en) * 2006-12-28 2011-02-01 General Electric Company Convertible gas turbine engine
FR2910937B1 (fr) * 2007-01-02 2009-04-03 Airbus France Sas Nacelle de reacteur d'aeronef et aeronef comportant une telle 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

Also Published As

Publication number Publication date
EP2798183A4 (fr) 2015-08-05
EP3812570B1 (fr) 2024-02-21
EP3812570A1 (fr) 2021-04-28
EP2798183A1 (fr) 2014-11-05
WO2013141930A1 (fr) 2013-09-26
CN104011358A (zh) 2014-08-27
EP2798183B1 (fr) 2020-12-02
EP2798183B8 (fr) 2021-01-20
CN104011358B (zh) 2017-05-03

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