WO2013154639A3 - Gas turbine engine with improved fuel efficiency - Google Patents

Gas turbine engine with improved fuel efficiency Download PDF

Info

Publication number
WO2013154639A3
WO2013154639A3 PCT/US2013/021831 US2013021831W WO2013154639A3 WO 2013154639 A3 WO2013154639 A3 WO 2013154639A3 US 2013021831 W US2013021831 W US 2013021831W WO 2013154639 A3 WO2013154639 A3 WO 2013154639A3
Authority
WO
WIPO (PCT)
Prior art keywords
fan
equal
exit guide
gas turbine
turbine engine
Prior art date
Application number
PCT/US2013/021831
Other languages
French (fr)
Other versions
WO2013154639A2 (en
Inventor
Karl L. Hasel
Peter G. Smith
Stuart S. Ochs
Original Assignee
United Technologies Corporation
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 US13/361,987 external-priority patent/US20120124964A1/en
Application filed by United Technologies Corporation filed Critical United Technologies Corporation
Priority to EP13775841.3A priority Critical patent/EP2809936B1/en
Publication of WO2013154639A2 publication Critical patent/WO2013154639A2/en
Publication of WO2013154639A3 publication Critical patent/WO2013154639A3/en

Links

Classifications

    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has an expansion ratio greater than or equal to about 5. The fan has a bypass ratio greater than or equal to about 8. In other features, a turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.
PCT/US2013/021831 2012-01-31 2013-01-17 Gas turbine engine with improved fuel efficiency WO2013154639A2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13775841.3A EP2809936B1 (en) 2012-01-31 2013-01-17 Gas turbine engine with improved fuel efficiency

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/361,987 US20120124964A1 (en) 2007-07-27 2012-01-31 Gas turbine engine with improved fuel efficiency
US13/361,987 2012-01-31

Publications (2)

Publication Number Publication Date
WO2013154639A2 WO2013154639A2 (en) 2013-10-17
WO2013154639A3 true WO2013154639A3 (en) 2014-01-03

Family

ID=49328269

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2013/021831 WO2013154639A2 (en) 2012-01-31 2013-01-17 Gas turbine engine with improved fuel efficiency

Country Status (2)

Country Link
EP (1) EP2809936B1 (en)
WO (1) WO2013154639A2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20230027726A1 (en) * 2021-07-19 2023-01-26 Raytheon Technologies Corporation High and low spool configuration for a gas turbine engine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020098082A1 (en) * 2001-01-25 2002-07-25 Mitsubishi Heavy Industries, Ltd. Gas turbine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5259187A (en) * 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes
US20110120078A1 (en) * 2009-11-24 2011-05-26 Schwark Jr Fred W Variable area fan nozzle track
CN104011358B (en) * 2011-12-30 2017-05-03 联合工艺公司 Gas turbine engine with low fan pressure ratio

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020098082A1 (en) * 2001-01-25 2002-07-25 Mitsubishi Heavy Industries, Ltd. Gas turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
"GEARS PUT A NEW SPIN ON TURBOFAN PERFORMANCE", MACHINE DESIGN MAGAZINE, 5 November 1998 (1998-11-05), XP055129882 *

Also Published As

Publication number Publication date
EP2809936A4 (en) 2015-09-02
EP2809936B1 (en) 2019-08-14
EP2809936A2 (en) 2014-12-10
WO2013154639A2 (en) 2013-10-17

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