IN2015DN00897A - - Google Patents

Info

Publication number
IN2015DN00897A
IN2015DN00897A IN897DEN2015A IN2015DN00897A IN 2015DN00897 A IN2015DN00897 A IN 2015DN00897A IN 897DEN2015 A IN897DEN2015 A IN 897DEN2015A IN 2015DN00897 A IN2015DN00897 A IN 2015DN00897A
Authority
IN
India
Prior art keywords
compressed air
receive
combustion gas
axial flow
flow
Prior art date
Application number
Inventor
Richard C Charron
Matthew D Montgomery
Original Assignee
Siemens Energy Inc
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 Siemens Energy Inc filed Critical Siemens Energy Inc
Publication of IN2015DN00897A publication Critical patent/IN2015DN00897A/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • 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

Abstract

An industrial gas turbine engine (10) including: a can annular combustion assembly (80) having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward
IN897DEN2015 2012-09-04 2013-08-20 IN2015DN00897A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/602,422 US9127554B2 (en) 2012-09-04 2012-09-04 Gas turbine engine with radial diffuser and shortened mid section
PCT/US2013/055792 WO2014039247A1 (en) 2012-09-04 2013-08-20 Gas turbine engine with radial diffuser and shortened mid section

Publications (1)

Publication Number Publication Date
IN2015DN00897A true IN2015DN00897A (en) 2015-06-12

Family

ID=49083791

Family Applications (1)

Application Number Title Priority Date Filing Date
IN897DEN2015 IN2015DN00897A (en) 2012-09-04 2013-08-20

Country Status (8)

Country Link
US (1) US9127554B2 (en)
EP (1) EP2893152A1 (en)
JP (1) JP6258325B2 (en)
CN (1) CN104619956B (en)
IN (1) IN2015DN00897A (en)
RU (1) RU2631181C2 (en)
SA (1) SA515360106B1 (en)
WO (1) WO2014039247A1 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130081407A1 (en) * 2011-10-04 2013-04-04 David J. Wiebe Aero-derivative gas turbine engine with an advanced transition duct combustion assembly
US20140060001A1 (en) * 2012-09-04 2014-03-06 Alexander R. Beeck Gas turbine engine with shortened mid section
JP6625427B2 (en) * 2015-12-25 2019-12-25 川崎重工業株式会社 Gas turbine engine
US10227883B2 (en) 2016-03-24 2019-03-12 General Electric Company Transition duct assembly
US10145251B2 (en) 2016-03-24 2018-12-04 General Electric Company Transition duct assembly
US10260752B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US10260360B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly
US10260424B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US11021977B2 (en) * 2018-11-02 2021-06-01 Chromalloy Gas Turbine Llc Diffuser guide vane with deflector panel having curved profile
US20210396175A1 (en) * 2018-11-30 2021-12-23 Siemens Energy Global GmbH & Co. KG Mid-frame section of a gas turbine engine and corresponding method of adjusting radial rotor clearance

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3088279A (en) * 1960-08-26 1963-05-07 Gen Electric Radial flow gas turbine power plant
US3631674A (en) * 1970-01-19 1972-01-04 Gen Electric Folded flow combustion chamber for a gas turbine engine
US4896499A (en) * 1978-10-26 1990-01-30 Rice Ivan G Compression intercooled gas turbine combined cycle
SU1311332A1 (en) * 1984-03-01 1995-11-20 В.Е. Беляев Axial-radial compressor diffuser
US5252860A (en) * 1989-12-11 1993-10-12 Westinghouse Electric Corp. Gas turbine control system having maximum instantaneous load-pickup limiter
KR940011861A (en) * 1992-11-09 1994-06-22 한스 요트. 헤쩨르, 하아. 카이저 Gas turbine combustion chamber
JP2904701B2 (en) * 1993-12-15 1999-06-14 株式会社日立製作所 Gas turbine and gas turbine combustion device
US5737915A (en) 1996-02-09 1998-04-14 General Electric Co. Tri-passage diffuser for a gas turbine
DE50107283D1 (en) * 2001-06-18 2005-10-06 Siemens Ag Gas turbine with a compressor for air
US6796130B2 (en) * 2002-11-07 2004-09-28 Siemens Westinghouse Power Corporation Integrated combustor and nozzle for a gas turbine combustion system
RU2235921C1 (en) * 2002-12-30 2004-09-10 Журавлев Юрий Иванович Axial-flow compressor pressure diffuser
JP2005042973A (en) * 2003-07-22 2005-02-17 Kawasaki Heavy Ind Ltd Gas turbine with swirl type combustor
US7721547B2 (en) * 2005-06-27 2010-05-25 Siemens Energy, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
US7870739B2 (en) * 2006-02-02 2011-01-18 Siemens Energy, Inc. Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions
US7600370B2 (en) * 2006-05-25 2009-10-13 Siemens Energy, Inc. Fluid flow distributor apparatus for gas turbine engine mid-frame section
JP5072278B2 (en) * 2006-07-18 2012-11-14 三菱重工業株式会社 Hydraulic removable coupling
US7631499B2 (en) * 2006-08-03 2009-12-15 Siemens Energy, Inc. Axially staged combustion system for a gas turbine engine
US20090139199A1 (en) 2007-11-15 2009-06-04 General Electric Company Pulse detonation combustor valve for high temperature and high pressure operation
CN101275750B (en) * 2008-04-25 2010-12-08 北京航空航天大学 Radial swirler turning zone direct injection premixing and prevapourising low pollution burning chamber
US8276389B2 (en) 2008-09-29 2012-10-02 Siemens Energy, Inc. Assembly for directing combustion gas
US8230688B2 (en) 2008-09-29 2012-07-31 Siemens Energy, Inc. Modular transvane assembly
US9822649B2 (en) * 2008-11-12 2017-11-21 General Electric Company Integrated combustor and stage 1 nozzle in a gas turbine and method
US8616007B2 (en) * 2009-01-22 2013-12-31 Siemens Energy, Inc. Structural attachment system for transition duct outlet
US20140060001A1 (en) * 2012-09-04 2014-03-06 Alexander R. Beeck Gas turbine engine with shortened mid section

Also Published As

Publication number Publication date
EP2893152A1 (en) 2015-07-15
SA515360106B1 (en) 2016-06-16
JP2015532699A (en) 2015-11-12
CN104619956A (en) 2015-05-13
US20140060000A1 (en) 2014-03-06
RU2015107382A (en) 2016-10-27
CN104619956B (en) 2017-06-09
JP6258325B2 (en) 2018-01-10
US9127554B2 (en) 2015-09-08
WO2014039247A1 (en) 2014-03-13
RU2631181C2 (en) 2017-09-19

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