EP2154431A3 - Thermal machine - Google Patents

Thermal machine Download PDF

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Publication number
EP2154431A3
EP2154431A3 EP09167590A EP09167590A EP2154431A3 EP 2154431 A3 EP2154431 A3 EP 2154431A3 EP 09167590 A EP09167590 A EP 09167590A EP 09167590 A EP09167590 A EP 09167590A EP 2154431 A3 EP2154431 A3 EP 2154431A3
Authority
EP
European Patent Office
Prior art keywords
cooling
combustion chamber
cooling channel
hot gas
inner shell
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.)
Granted
Application number
EP09167590A
Other languages
German (de)
French (fr)
Other versions
EP2154431A2 (en
EP2154431B1 (en
Inventor
Remigi Tschuor
Hartmut Hähnle
Uwe Rüdel
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 Technology GmbH
Original Assignee
Alstom Technology AG
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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2154431A2 publication Critical patent/EP2154431A2/en
Publication of EP2154431A3 publication Critical patent/EP2154431A3/en
Application granted granted Critical
Publication of EP2154431B1 publication Critical patent/EP2154431B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F23R3/54—Reverse-flow combustion chambers
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Eine thermische Maschine, insbesondere Gasturbine, umfasst eine durch eine Aussenschale und eine Innenschale (33) nach aussen begrenzte, ringförmige Brennkammer, durch welche in axialer Richtung ein Heissgasstrom strömt, wobei die Aussenschale und Innenschale (33) auf ihrer Aussenseite jeweils unter Ausbildung eines Kühlkanals (32) mit einem in einem Abstand angebrachten, konzentrischen Kühlhemd (31) versehen sind, durch welchen Kühlkanal (32) Kühlluft in einer zum Heissgasstrom entgegengesetzten Richtung strömt.A thermal engine, in particular a gas turbine, comprises an annular combustion chamber bounded outwards by an outer shell and an inner shell (33) through which a hot gas stream flows in the axial direction, the outer shell and inner shell (33) each forming a cooling channel on its outer side (32) are provided with a spaced, concentric cooling jacket (31), through which cooling channel (32) cooling air flows in a direction opposite to the hot gas flow direction.

Bei einer solchen Maschine wird die Kühlung der Brennkammer dadurch verbessert, dass zumindest eines der Kühlhemden (31) auf der Seite, auf welcher die Kühlluft in den Kühlkanal (32) eintritt, zur Verbesserung der Einströmbedingungen eine nach aussen gebogene, abgerundete Eintrittskante (37) aufweist.

Figure imgaf001
In such a machine, the cooling of the combustion chamber is improved in that at least one of the cooling shirts (31) on the side, on which the cooling air enters the cooling channel (32), to improve the Einströmbedingungen an outwardly curved, rounded leading edge (37). having.
Figure imgaf001
EP09167590.0A 2008-08-14 2009-08-11 Thermal machine Active EP2154431B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH01277/08A CH699309A1 (en) 2008-08-14 2008-08-14 Thermal machine with air cooled, annular combustion chamber.

Publications (3)

Publication Number Publication Date
EP2154431A2 EP2154431A2 (en) 2010-02-17
EP2154431A3 true EP2154431A3 (en) 2010-08-04
EP2154431B1 EP2154431B1 (en) 2017-07-26

Family

ID=40342516

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09167590.0A Active EP2154431B1 (en) 2008-08-14 2009-08-11 Thermal machine

Country Status (4)

Country Link
US (1) US8434313B2 (en)
EP (1) EP2154431B1 (en)
AU (1) AU2009208110B2 (en)
CH (1) CH699309A1 (en)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
MY161317A (en) * 2008-02-20 2017-04-14 General Electric Technology Gmbh Gas turbine
US8899975B2 (en) * 2011-11-04 2014-12-02 General Electric Company Combustor having wake air injection
US9267687B2 (en) 2011-11-04 2016-02-23 General Electric Company Combustion system having a venturi for reducing wakes in an airflow
US9897317B2 (en) * 2012-10-01 2018-02-20 Ansaldo Energia Ip Uk Limited Thermally free liner retention mechanism
US20140208771A1 (en) * 2012-12-28 2014-07-31 United Technologies Corporation Gas turbine engine component cooling arrangement
US9739201B2 (en) 2013-05-08 2017-08-22 General Electric Company Wake reducing structure for a turbine system and method of reducing wake
US9322553B2 (en) 2013-05-08 2016-04-26 General Electric Company Wake manipulating structure for a turbine system
US9435221B2 (en) 2013-08-09 2016-09-06 General Electric Company Turbomachine airfoil positioning
EP2868898A1 (en) * 2013-10-30 2015-05-06 Siemens Aktiengesellschaft Improved partial load operation of a gas turbine with an adjustable bypass flow channel
GB201501817D0 (en) * 2015-02-04 2015-03-18 Rolls Royce Plc A combustion chamber and a combustion chamber segment
EP3236155B1 (en) * 2016-04-22 2020-05-06 Rolls-Royce plc Combustion chamber with segmented wall
US10641174B2 (en) 2017-01-18 2020-05-05 General Electric Company Rotor shaft cooling
US10801730B2 (en) * 2017-04-12 2020-10-13 Raytheon Technologies Corporation Combustor panel mounting systems and methods
US10697634B2 (en) * 2018-03-07 2020-06-30 General Electric Company Inner cooling shroud for transition zone of annular combustor liner
US11248797B2 (en) 2018-11-02 2022-02-15 Chromalloy Gas Turbine Llc Axial stop configuration for a combustion liner
WO2020092896A1 (en) * 2018-11-02 2020-05-07 Chromalloy Gas Turbine Llc System and method for providing compressed air to a gas turbine combustor
US11377970B2 (en) 2018-11-02 2022-07-05 Chromalloy Gas Turbine Llc System and method for providing compressed air to a gas turbine combustor
US11047575B2 (en) * 2019-04-15 2021-06-29 Raytheon Technologies Corporation Combustor heat shield panel
US11215367B2 (en) 2019-10-03 2022-01-04 Raytheon Technologies Corporation Mounting a ceramic component to a non-ceramic component in a gas turbine engine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0239020A2 (en) * 1986-03-20 1987-09-30 Hitachi, Ltd. Gas turbine combustion apparatus
EP0590338A1 (en) * 1992-09-28 1994-04-06 Asea Brown Boveri Ag Gas turbine combustion chamber
EP0599055A1 (en) * 1992-11-27 1994-06-01 Asea Brown Boveri Ag Gasturbine combustor
DE19751299A1 (en) * 1997-11-19 1999-06-02 Siemens Ag Combustion chamber and method for steam cooling a combustion chamber
US20010020364A1 (en) * 1998-11-12 2001-09-13 Yoshichika Sato Gas turbine combustor
EP1219900A2 (en) * 2000-12-26 2002-07-03 Mitsubishi Heavy Industries, Ltd. Gas turbine combustion device
US20050144953A1 (en) * 2003-12-24 2005-07-07 Martling Vincent C. Flow sleeve for a law NOx combustor
EP1662201A2 (en) * 2004-11-30 2006-05-31 Alstom Technology Ltd Tile and exo-skeleton tile structure
GB2434199A (en) * 2006-01-14 2007-07-18 Alstom Technology Ltd Combustor liners

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4896510A (en) * 1987-02-06 1990-01-30 General Electric Company Combustor liner cooling arrangement
DE59010740D1 (en) * 1990-12-05 1997-09-04 Asea Brown Boveri Gas turbine combustor
DE4242721A1 (en) * 1992-12-17 1994-06-23 Asea Brown Boveri Gas turbine combustion chamber
EP0985882B1 (en) * 1998-09-10 2003-12-03 ALSTOM (Switzerland) Ltd Vibration damping in combustors

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0239020A2 (en) * 1986-03-20 1987-09-30 Hitachi, Ltd. Gas turbine combustion apparatus
EP0590338A1 (en) * 1992-09-28 1994-04-06 Asea Brown Boveri Ag Gas turbine combustion chamber
EP0599055A1 (en) * 1992-11-27 1994-06-01 Asea Brown Boveri Ag Gasturbine combustor
DE19751299A1 (en) * 1997-11-19 1999-06-02 Siemens Ag Combustion chamber and method for steam cooling a combustion chamber
US20010020364A1 (en) * 1998-11-12 2001-09-13 Yoshichika Sato Gas turbine combustor
EP1219900A2 (en) * 2000-12-26 2002-07-03 Mitsubishi Heavy Industries, Ltd. Gas turbine combustion device
US20050144953A1 (en) * 2003-12-24 2005-07-07 Martling Vincent C. Flow sleeve for a law NOx combustor
EP1662201A2 (en) * 2004-11-30 2006-05-31 Alstom Technology Ltd Tile and exo-skeleton tile structure
GB2434199A (en) * 2006-01-14 2007-07-18 Alstom Technology Ltd Combustor liners

Also Published As

Publication number Publication date
EP2154431A2 (en) 2010-02-17
US8434313B2 (en) 2013-05-07
AU2009208110B2 (en) 2014-07-10
EP2154431B1 (en) 2017-07-26
US20100037621A1 (en) 2010-02-18
CH699309A1 (en) 2010-02-15
AU2009208110A1 (en) 2010-03-04

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