WO2013081714A3 - Guide vane assembly for a gas turbine engine - Google Patents

Guide vane assembly for a gas turbine engine Download PDF

Info

Publication number
WO2013081714A3
WO2013081714A3 PCT/US2012/055312 US2012055312W WO2013081714A3 WO 2013081714 A3 WO2013081714 A3 WO 2013081714A3 US 2012055312 W US2012055312 W US 2012055312W WO 2013081714 A3 WO2013081714 A3 WO 2013081714A3
Authority
WO
WIPO (PCT)
Prior art keywords
flap
trailing edge
leading edge
gas turbine
turbine engine
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/US2012/055312
Other languages
French (fr)
Other versions
WO2013081714A2 (en
Inventor
Thurmond Douglas SENTER
Mark Joseph MIELKE
Alan Glen TURNER
Thomas Becker
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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
Application filed by General Electric Co filed Critical General Electric Co
Priority to CA2847566A priority Critical patent/CA2847566A1/en
Priority to EP12837618.3A priority patent/EP2756182A2/en
Publication of WO2013081714A2 publication Critical patent/WO2013081714A2/en
Publication of WO2013081714A3 publication Critical patent/WO2013081714A3/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A guide vane assembly (62, 64) for a flade duct of a gas turbine engine (10) includes: a strut (62) having: a root (95), a tip (70), a leading edge, a trailing edge wall (78), and opposed sidewalls extending between the leading edge and the trailing edge wall; and a pair of spaced-apart prongs (80) extending axially aft from the trailing edge wall, each prong having an outer wall that is flush with a respective one of the sidewalls (72,74); and a flap positioned axially aft of the strut (64), the flap having a root, a tip, a leading edge, a trailing edge, and opposed sides extending between the leading and trailing edge, wherein a portion of the leading edge (92) is disposed between the prongs, and wherein a disk-like flap button (102) is disposed at the tip of the flap adjacent its leading edge (92), the flap button including a pair of spaced-apart notches formed therein (104).
PCT/US2012/055312 2011-09-14 2012-09-14 Guide vane assembly for a gas turbine engine Ceased WO2013081714A2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CA2847566A CA2847566A1 (en) 2011-09-14 2012-09-14 Guide vane assembly for a gas turbine engine
EP12837618.3A EP2756182A2 (en) 2011-09-14 2012-09-14 Guide vane assembly for a gas turbine engine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US201161534826P 2011-09-14 2011-09-14
US61/534,826 2011-09-14
US13/607,147 US20140064955A1 (en) 2011-09-14 2012-09-07 Guide vane assembly for a gas turbine engine
US13/607,147 2012-09-07

Publications (2)

Publication Number Publication Date
WO2013081714A2 WO2013081714A2 (en) 2013-06-06
WO2013081714A3 true WO2013081714A3 (en) 2013-08-15

Family

ID=47997770

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2012/055312 Ceased WO2013081714A2 (en) 2011-09-14 2012-09-14 Guide vane assembly for a gas turbine engine

Country Status (4)

Country Link
US (1) US20140064955A1 (en)
EP (1) EP2756182A2 (en)
CA (1) CA2847566A1 (en)
WO (1) WO2013081714A2 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9494053B2 (en) * 2013-09-23 2016-11-15 Siemens Aktiengesellschaft Diffuser with strut-induced vortex mixing
US9957823B2 (en) * 2014-01-24 2018-05-01 United Technologies Corporation Virtual multi-stream gas turbine engine
US10107196B2 (en) * 2014-08-08 2018-10-23 Thomas International, Inc. Adjustable size inlet system
US10151325B2 (en) * 2015-04-08 2018-12-11 General Electric Company Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same
US10563513B2 (en) * 2017-12-19 2020-02-18 United Technologies Corporation Variable inlet guide vane
US10781707B2 (en) * 2018-09-14 2020-09-22 United Technologies Corporation Integral half vane, ringcase, and id shroud
US10794200B2 (en) * 2018-09-14 2020-10-06 United Technologies Corporation Integral half vane, ringcase, and id shroud
BE1027876B1 (en) * 2019-12-18 2021-07-26 Safran Aero Boosters Sa TURBOMACHINE MODULE
US12398655B2 (en) * 2023-03-17 2025-08-26 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with segment interface components
US12480422B2 (en) * 2023-03-17 2025-11-25 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with pass through actuation mechanisms

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1491725A2 (en) * 2003-06-26 2004-12-29 Snecma Moteurs Bearing device for an adjustable vane
EP1780378A2 (en) * 2005-10-25 2007-05-02 United Technologies Corporation Variable geometry inlet guide vane
FR2908828A1 (en) * 2006-11-16 2008-05-23 Snecma Sa Mobile flap shutter sealing device for e.g. turbojet engine, of aircraft, has seal fixed to downstream end of fixed radial arm of vanes by sticking, and including lip supported on upstream end, during pivotable displacements of shutter
EP2031193A2 (en) * 2007-08-31 2009-03-04 General Electric Company Slipring bushing assembly for moveable turbine vane
GB2466214A (en) * 2008-12-12 2010-06-16 Gen Electric A bushing and clock spring assembly for a movable turbine vane
US20120163960A1 (en) * 2010-12-27 2012-06-28 Ress Jr Robert A Gas turbine engine and variable camber vane system

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3059902A (en) * 1961-07-03 1962-10-23 Chrysler Corp Adjustable nozzle and intermediate inner shroud support
US6435821B1 (en) * 2000-12-20 2002-08-20 United Technologies Corporation Variable vane for use in turbo machines
US6619916B1 (en) * 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow
US6843638B2 (en) * 2002-12-10 2005-01-18 Honeywell International Inc. Vane radial mounting apparatus
US7594794B2 (en) * 2006-08-24 2009-09-29 United Technologies Corporation Leaned high pressure compressor inlet guide vane
FR2916815B1 (en) * 2007-05-30 2017-02-24 Snecma AIR REINJECTION COMPRESSOR
US8123471B2 (en) * 2009-03-11 2012-02-28 General Electric Company Variable stator vane contoured button

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1491725A2 (en) * 2003-06-26 2004-12-29 Snecma Moteurs Bearing device for an adjustable vane
EP1780378A2 (en) * 2005-10-25 2007-05-02 United Technologies Corporation Variable geometry inlet guide vane
FR2908828A1 (en) * 2006-11-16 2008-05-23 Snecma Sa Mobile flap shutter sealing device for e.g. turbojet engine, of aircraft, has seal fixed to downstream end of fixed radial arm of vanes by sticking, and including lip supported on upstream end, during pivotable displacements of shutter
EP2031193A2 (en) * 2007-08-31 2009-03-04 General Electric Company Slipring bushing assembly for moveable turbine vane
GB2466214A (en) * 2008-12-12 2010-06-16 Gen Electric A bushing and clock spring assembly for a movable turbine vane
US20120163960A1 (en) * 2010-12-27 2012-06-28 Ress Jr Robert A Gas turbine engine and variable camber vane system

Also Published As

Publication number Publication date
EP2756182A2 (en) 2014-07-23
WO2013081714A2 (en) 2013-06-06
CA2847566A1 (en) 2013-06-06
US20140064955A1 (en) 2014-03-06

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