MXPA02012451A - Transition piece for non-annular gas turbine combustion chambers. - Google Patents

Transition piece for non-annular gas turbine combustion chambers.

Info

Publication number
MXPA02012451A
MXPA02012451A MXPA02012451A MXPA02012451A MXPA02012451A MX PA02012451 A MXPA02012451 A MX PA02012451A MX PA02012451 A MXPA02012451 A MX PA02012451A MX PA02012451 A MXPA02012451 A MX PA02012451A MX PA02012451 A MXPA02012451 A MX PA02012451A
Authority
MX
Mexico
Prior art keywords
gas turbine
transition piece
combustion chambers
annular gas
turbine combustion
Prior art date
Application number
MXPA02012451A
Other languages
Spanish (es)
Inventor
Alessandro Coppola
Original Assignee
Nuovo Pignone Spa
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 Nuovo Pignone Spa filed Critical Nuovo Pignone Spa
Publication of MXPA02012451A publication Critical patent/MXPA02012451A/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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Abstract

A transition piece (10) for non-annular gas turbine combustion chambers has a projecting connection arm (22) for support on the turbine stator, wherein the projecting connection arm (22) makes it possible to obtain a lead-in axis with an angle of between 5 and 7 relative to an axis, which is parallel to the axis of the machine, and is perpendicular to the plane on which there lies the frame for interfacing of the transition piece (10) with the ring of nozzles of the first stage of the gas turbine.
MXPA02012451A 2000-06-16 2001-06-08 Transition piece for non-annular gas turbine combustion chambers. MXPA02012451A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT2000MI001362A IT1317978B1 (en) 2000-06-16 2000-06-16 TRANSITION PIECE FOR COMBUSTION CHAMBERS OF NONANULAR GAS TURBINES.
PCT/EP2001/006484 WO2001096712A1 (en) 2000-06-16 2001-06-08 Transition piece for non-annular gas turbine combustion chambers

Publications (1)

Publication Number Publication Date
MXPA02012451A true MXPA02012451A (en) 2003-04-25

Family

ID=11445283

Family Applications (1)

Application Number Title Priority Date Filing Date
MXPA02012451A MXPA02012451A (en) 2000-06-16 2001-06-08 Transition piece for non-annular gas turbine combustion chambers.

Country Status (12)

Country Link
US (1) US20030167776A1 (en)
EP (1) EP1295014B1 (en)
AR (1) AR028133A1 (en)
AT (1) ATE310896T1 (en)
AU (1) AU7844301A (en)
BR (1) BR0111577A (en)
DE (1) DE60115236T2 (en)
IT (1) IT1317978B1 (en)
MX (1) MXPA02012451A (en)
NO (1) NO330416B1 (en)
RU (1) RU2275554C2 (en)
WO (1) WO2001096712A1 (en)

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7178341B2 (en) * 2004-06-17 2007-02-20 Siemens Power Generation, Inc. Multi-zone tubing assembly for a transition piece of a gas turbine
US7278254B2 (en) * 2005-01-27 2007-10-09 Siemens Power Generation, Inc. Cooling system for a transition bracket of a transition in a turbine engine
US8015818B2 (en) * 2005-02-22 2011-09-13 Siemens Energy, Inc. Cooled transition duct for a gas turbine engine
US7827801B2 (en) * 2006-02-09 2010-11-09 Siemens Energy, Inc. Gas turbine engine transitions comprising closed cooled transition cooling channels
US8151570B2 (en) * 2007-12-06 2012-04-10 Alstom Technology Ltd Transition duct cooling feed tubes
US8091365B2 (en) * 2008-08-12 2012-01-10 Siemens Energy, Inc. Canted outlet for transition in a gas turbine engine
US8113003B2 (en) * 2008-08-12 2012-02-14 Siemens Energy, Inc. Transition with a linear flow path for use in a gas turbine engine
US20120186269A1 (en) * 2011-01-25 2012-07-26 General Electric Company Support between transition piece and impingement sleeve in combustor
IN2014DN03773A (en) 2011-10-24 2015-07-10 Alstom Technology Ltd
US9593853B2 (en) * 2014-02-20 2017-03-14 Siemens Energy, Inc. Gas flow path for a gas turbine engine
WO2017039567A1 (en) * 2015-08-28 2017-03-09 Siemens Aktiengesellschaft Non-axially symmetric transition ducts for combustors
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10641491B2 (en) 2016-03-25 2020-05-05 General Electric Company Cooling of integrated combustor nozzle of segmented annular combustion system
US10584638B2 (en) 2016-03-25 2020-03-10 General Electric Company Turbine nozzle cooling with panel fuel injector
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
JP6650849B2 (en) * 2016-08-25 2020-02-19 三菱日立パワーシステムズ株式会社 gas turbine
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
US10837299B2 (en) 2017-03-07 2020-11-17 General Electric Company System and method for transition piece seal
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5964091A (en) * 1995-07-11 1999-10-12 Hitachi, Ltd. Gas turbine combustor and gas turbine
US6006523A (en) * 1997-04-30 1999-12-28 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor with angled tube section
US6393828B1 (en) * 1997-07-21 2002-05-28 General Electric Company Protective coatings for turbine combustion components

Also Published As

Publication number Publication date
IT1317978B1 (en) 2003-07-21
ITMI20001362A0 (en) 2000-06-16
DE60115236D1 (en) 2005-12-29
NO20025995D0 (en) 2002-12-13
AR028133A1 (en) 2003-04-23
NO20025995L (en) 2003-02-13
AU7844301A (en) 2001-12-24
ATE310896T1 (en) 2005-12-15
RU2275554C2 (en) 2006-04-27
WO2001096712A1 (en) 2001-12-20
DE60115236T2 (en) 2006-07-27
EP1295014A1 (en) 2003-03-26
ITMI20001362A1 (en) 2001-12-16
BR0111577A (en) 2003-03-18
US20030167776A1 (en) 2003-09-11
EP1295014B1 (en) 2005-11-23
NO330416B1 (en) 2011-04-11

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