WO2015069334A3 - Variable area turbine arrangement for a gas turbine engine - Google Patents

Variable area turbine arrangement for a gas turbine engine Download PDF

Info

Publication number
WO2015069334A3
WO2015069334A3 PCT/US2014/049536 US2014049536W WO2015069334A3 WO 2015069334 A3 WO2015069334 A3 WO 2015069334A3 US 2014049536 W US2014049536 W US 2014049536W WO 2015069334 A3 WO2015069334 A3 WO 2015069334A3
Authority
WO
WIPO (PCT)
Prior art keywords
variable area
turbine section
turbine
arrangement
gas turbine
Prior art date
Application number
PCT/US2014/049536
Other languages
French (fr)
Other versions
WO2015069334A2 (en
Inventor
Raymond Surace
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
Application filed by United Technologies Corporation filed Critical United Technologies Corporation
Priority to EP14860068.7A priority Critical patent/EP3030756B1/en
Priority to US14/909,209 priority patent/US10240479B2/en
Publication of WO2015069334A2 publication Critical patent/WO2015069334A2/en
Publication of WO2015069334A3 publication Critical patent/WO2015069334A3/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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • 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
    • F05D2220/32—Application in turbines in gas turbines

Abstract

A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a first turbine section having at least a first variable vane row and a second turbine section downstream from the first turbine section and having at least a second variable vane row. A transition duct is disposed between the first turbine section and the second turbine section.
PCT/US2014/049536 2013-08-07 2014-08-04 Variable area turbine arrangement for a gas turbine engine WO2015069334A2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14860068.7A EP3030756B1 (en) 2013-08-07 2014-08-04 Variable area turbine arrangement for a gas turbine engine
US14/909,209 US10240479B2 (en) 2013-08-07 2014-08-04 Variable area turbine arrangement for a gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361863000P 2013-08-07 2013-08-07
US61/863,000 2013-08-07

Publications (2)

Publication Number Publication Date
WO2015069334A2 WO2015069334A2 (en) 2015-05-14
WO2015069334A3 true WO2015069334A3 (en) 2015-07-23

Family

ID=53042285

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2014/049536 WO2015069334A2 (en) 2013-08-07 2014-08-04 Variable area turbine arrangement for a gas turbine engine

Country Status (3)

Country Link
US (1) US10240479B2 (en)
EP (1) EP3030756B1 (en)
WO (1) WO2015069334A2 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180149114A1 (en) * 2016-11-30 2018-05-31 Sikorsky Aircraft Corporation Low infrared signature exhaust through active film cooling active mixing and acitve vane rotation
US11167858B2 (en) * 2018-09-10 2021-11-09 Raytheon Technologies Corporation Variable cycle compensation in a gas turbine engine
US11692491B1 (en) 2022-05-05 2023-07-04 Raytheon Technologies Corporation Transmission and method for control of boost spool
US11976598B2 (en) 2022-05-05 2024-05-07 Rtx Corporation Transmission and method for control of boost spool
US11692493B1 (en) 2022-05-05 2023-07-04 Raytheon Technologies Corporation Fluidic valve configuration for boost spool engine
US11898490B2 (en) * 2022-05-05 2024-02-13 Rtx Corporation Transmission and method for control of boost spool
US11639690B1 (en) 2022-05-05 2023-05-02 Raytheon Technologies Corporation Boost spool flow control and generator load matching via load compressor

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
US20060275111A1 (en) * 2005-06-06 2006-12-07 General Electric Company Forward tilted turbine nozzle
US20070119150A1 (en) * 2005-11-29 2007-05-31 Wood Peter J Turbofan gas turbine engine with variable fan outlet guide vanes
US20100202873A1 (en) * 2009-02-06 2010-08-12 General Electric Company Ceramic Matrix Composite Turbine Engine
US20130104521A1 (en) * 2011-11-01 2013-05-02 Daniel B. Kupratis Gas turbine engine with two-spool fan and variable vane turbine

Family Cites Families (16)

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Publication number Priority date Publication date Assignee Title
US3449914A (en) * 1967-12-21 1969-06-17 United Aircraft Corp Variable flow turbofan engine
CA1020365A (en) * 1974-02-25 1977-11-08 James E. Johnson Modulating bypass variable cycle turbofan engine
US3861822A (en) 1974-02-27 1975-01-21 Gen Electric Duct with vanes having selectively variable pitch
US4043121A (en) * 1975-01-02 1977-08-23 General Electric Company Two-spool variable cycle engine
CH582823A5 (en) * 1975-03-06 1976-12-15 Bbc Brown Boveri & Cie
US4013377A (en) 1975-10-08 1977-03-22 Westinghouse Electric Corporation Intermediate transition annulus for a two shaft gas turbine engine
US5397215A (en) * 1993-06-14 1995-03-14 United Technologies Corporation Flow directing assembly for the compression section of a rotary machine
US5911679A (en) * 1996-12-31 1999-06-15 General Electric Company Variable pitch rotor assembly for a gas turbine engine inlet
US5931636A (en) * 1997-08-28 1999-08-03 General Electric Company Variable area turbine nozzle
WO2006110123A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Vectoring transition duct for turbine engine
GB2436130B (en) * 2005-12-15 2008-01-30 Rolls Royce Plc A vane arrangement and a method of making vane arrangement
US20070214795A1 (en) * 2006-03-15 2007-09-20 Paul Cooker Continuous real time EGT margin control
US7877980B2 (en) * 2006-12-28 2011-02-01 General Electric Company Convertible gas turbine engine
US8161728B2 (en) * 2007-06-28 2012-04-24 United Technologies Corp. Gas turbines with multiple gas flow paths
US8622687B2 (en) * 2009-09-25 2014-01-07 General Electric Company Method of operating adaptive core engines
US20110167784A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Method of operating a convertible fan engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
US20060275111A1 (en) * 2005-06-06 2006-12-07 General Electric Company Forward tilted turbine nozzle
US20070119150A1 (en) * 2005-11-29 2007-05-31 Wood Peter J Turbofan gas turbine engine with variable fan outlet guide vanes
US20100202873A1 (en) * 2009-02-06 2010-08-12 General Electric Company Ceramic Matrix Composite Turbine Engine
US20130104521A1 (en) * 2011-11-01 2013-05-02 Daniel B. Kupratis Gas turbine engine with two-spool fan and variable vane turbine

Also Published As

Publication number Publication date
EP3030756A2 (en) 2016-06-15
US20160186600A1 (en) 2016-06-30
EP3030756A4 (en) 2017-03-22
EP3030756B1 (en) 2020-04-29
US10240479B2 (en) 2019-03-26
WO2015069334A2 (en) 2015-05-14

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