EP2049841B1 - Chambre de combustion d'une installation d'incinération - Google Patents

Chambre de combustion d'une installation d'incinération Download PDF

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Publication number
EP2049841B1
EP2049841B1 EP07787170.5A EP07787170A EP2049841B1 EP 2049841 B1 EP2049841 B1 EP 2049841B1 EP 07787170 A EP07787170 A EP 07787170A EP 2049841 B1 EP2049841 B1 EP 2049841B1
Authority
EP
European Patent Office
Prior art keywords
gap
combustion chamber
liner
region
cooling
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.)
Active
Application number
EP07787170.5A
Other languages
German (de)
English (en)
Other versions
EP2049841A2 (fr
Inventor
Stefan Tschirren
Daniel Burri
Andreas Dr. Abdon
Christian Dr. Steinbach
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
General Electric Technology GmbH
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Publication date
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Publication of EP2049841A2 publication Critical patent/EP2049841A2/fr
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Publication of EP2049841B1 publication Critical patent/EP2049841B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • 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

Definitions

  • the invention relates to a combustion chamber of a combustion plant, in particular a gas turbine, with a heat shield having at least two segments.
  • combustion chambers of a combustion system such as a gas turbine, equipped with a so-called heat shield, which protects an underlying support structure from direct contact with a hot gas stream.
  • a heat shield which protects an underlying support structure from direct contact with a hot gas stream.
  • the longevity of the incinerator is crucial, so that the proper functioning of the heat shield must be guaranteed.
  • modern heat shields usually consist of several segments, With several liner elements, gaps form between two adjacent liner elements into which a stream of hot gas can enter.
  • a support element is often arranged which on the one hand carries at least one liner element and on the other hand is not protected in the worst case by the liner element from direct access contact with the hot gas stream and this is thus exposed unprotected.
  • Such gaps thus constitute potential weak points.
  • the gaps between the liner elements are to be protected from too high a temperature load.
  • DE19727407 relates to a heat shield, in particular for a flame tube of a gas turbine combustion chamber
  • EP1507116 relates to a heat shield assembly for a hot gas leading component
  • DE8618859 relates to a heat shield for protecting a support structure from a hot fluid.
  • the invention deals with the problem of providing for a combustion chamber of the type mentioned in an improved embodiment, which is characterized in particular by a locally adapted cooling of a heat shield.
  • the invention is based on the general idea of locally cooling a gap which is arranged between two liner elements of a heat shield and open towards a combustion chamber and thereby effectively protecting a support element arranged in the region of a split bottom from direct hot gas exposure.
  • the thermal protection shield provided for heat protection has at least two segments, each of which comprises a, a combustion chamber facing the liner element and a holding device which defines the liner element via a support member to a support structure.
  • each liner element has an edge region which simultaneously forms a wall of a gap located between two liner elements and open towards the combustion chamber. In the area of a floor while a support member is arranged, which closes the gap on its side facing away from the combustion chamber.
  • At least one through opening is provided in at least one edge region of a liner element and / or in the bottom, ie, in the support element, through which cooling gas flows into the gap, thereby cooling the film from the two edge regions adjoining liner elements formed gap walls.
  • an effective cooling of the gap can be achieved without substantially increasing the oxygen content in the combustion chamber and thereby the NO x emissions of the incinerator.
  • a passage opening are provided in only one of the two edge regions of the liner elements, in both edge regions, only in the bottom or at least one edge region and the bottom, so adapted depending on locally required cooling demand cooling by different arrangement of the through holes can be.
  • the edge region of the liner element expediently engages behind a flange region formed by the holding device. This allows reliable retention of the liner element via the holding device on the support element or on the support structure, wherein compared to a direct screwing temperature expansions are easily absorbed. Such a holder of the liner elements thus reduces the risk of excessive voltages due to thermal expansion and thereby contributes to the longevity of the incinerator.
  • At least the edge regions of the liner elements and / or the support element have a temperature protection layer in the region of the split bottom.
  • a temperature protection layer improves the resistance of the liner elements or of the support element to a temperature load resulting from the hot gas flow and thereby increases the service life of the liner elements.
  • the resistance of the liner elements or of the support element to a temperature load which is improved by the temperature protection layer, also reduces maintenance requirements since the temperature protection layers prolong the service life of the liner elements or the support elements. Prolonged life extend the maintenance intervals, which can significantly reduce the downtime of the incinerator and thus the incinerator itself can be operated more cost effective.
  • FIG. 1 is a sectional view through a combustion chamber wall of a combustion system shown, in particular a gas turbine, with a heat shield 1, which has at least two juxtaposed segments 2, 2 '.
  • the two segments 2, 2 'each have a combustion element 3 facing a liner element 4 or 4' and a holding device 5, 5 '.
  • the liner element 4 is, like the liner element 4 ', formed of a material which is insensitive to heat, so that it readily resists direct contact with hot gases present in the combustion chamber 3.
  • the two liner elements 4, 4 ' are fixed via at least one support element 6 to a support structure 7, wherein the support device 5 both the liner element 4th as well as the at least one support element 6 defines on the support structure 7.
  • the gap 10 is closed by a gap bottom, which is formed, for example, by one or more support elements 6, 6 '.
  • hot gas flowing into the gap 10 acts on a gap bottom almost directly on the support element 6 or 6' and adversely affect this with respect to its function, provided that the gap bottom is not opposed to it Flange portions 11, 11 'of the two liner elements 4, 4' is protected from direct contact with the hot gas stream.
  • At least one through-opening 12 is provided in the edge region 8 of at least one liner element 4 or 4 'and / or in the bottom, ie in the support element 6, through which cooling gas can flow into the gap 10.
  • the reaching into the gap cooling gas is previously used to cool the two liner elements 4, 4 'or flows directly from a cooling gas duct 13 through the support member 6 and between two adjacent support members 6, 6' into the gap 10.
  • Both liner elements 4, 4 ' have these on their side facing away from the combustion chamber 3 side cooling fins 14, 14' on.
  • the passage opening 12 between the cooling gas channel 13 and the gap bottom of the gap 10 can be either a through hole or Through opening 12 may be formed by a one-piece support member 6 or as a gap channel between two adjacent support members 6, 6 ', whereby a uniform cooling of the gap 10 along the gap 10 is achieved.
  • at least the edge regions 8, 8 'of the liner elements 4, 4' and / or the support element 6 or 6 ' have a temperature protection layer in the region of the split bottom on. This lowers the sensitivity to temperature stress and increases the resistance of the components coated with the temperature layer.
  • 10 through holes 12 are provided through both which can flow into the gap 10 through both cooling gas in both edge regions 8, 8 'and in the region of the gap bottom of the gap.
  • 10 through holes 12 are provided through both which can flow into the gap 10 through both cooling gas in both edge regions 8, 8 'and in the region of the gap bottom of the gap.
  • the edge region 8 or 8 'of the liner element 4 or 4' and / or the support element 6 can also be made to have at least one row of passage openings 12 running essentially parallel to the gap 10 in the region of the split bottom (cf. , Fig. 2 ).
  • a reduced cooling requirement only a row with several, but widely spaced, and formed with a small diameter through holes 12 are seen, while at a high cooling demand several rows with close together lying and each having a large diameter through holes 12 are provided.
  • the solution according to the invention with an arrangement of passage openings 12 in the gap 10 which is adapted to a respective required cooling requirement makes it possible to achieve cooling adapted to the respective cooling requirement, in particular film cooling, which on one hand achieves the gap 10 with the adjacent liner elements 4, 4 'and the support member 6 sufficiently cool and on the other hand only just enough refrigerant gas in the gap 10 and in the combustion chamber 3 enters, as is essential for cooling. Too high a cooling gas flow, which is associated with a concomitant reduced efficiency of the incinerator, can be prevented as well as excessive NO x emissions of the incinerator.

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)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Claims (7)

  1. Chambre de combustion d'une installation d'incinération, plus particulièrement d'une turbine à gaz, avec un bouclier thermique (1) comprenant au moins deux segments (2, 2'),
    - chaque segment (2, 2') comprenant un élément de liner (4, 4') orienté vers un espace de combustion (3) et un dispositif de maintien (5) qui fixe l'élément de liner (4, 4') à une structure porteuse (7) par l'intermédiaire d'un élément porteur (6, 6'),
    - l'élément de liner (4, 4') comprenant une zone de bord (8, 8'),
    - entre les zones de bord (8, 8') de deux éléments de liner (4, 4') adjacents, un interstice (10) ouvert en direction de l'espace de combustion (3) subsistant,
    - l'élément porteur (6, 6') étant disposé au niveau d'un fond de l'interstice (10),
    - pour le refroidissement des zones de bord (8, 8') orientées vers l'interstice (10) des éléments de liner (4, 4'), dans la zone de bord (8, 8') d'au moins un élément de liner (4, 4') et/ou dans le fond, au moins une ouverture de passage (12) étant prévue, à travers laquelle un gaz de refroidissement s'écoule dans l'interstice (10),
    caractérisée en ce que
    la zone de bord (8, 8') de l'élément de liner (4, 4') vient en prise à l'arrière d'une zone de bride (9) constitué par le dispositif de maintien (5).
  2. Chambre de combustion selon la revendication 1,
    caractérisée en ce que
    au moins les zones de bords (8, 8') des éléments de liner (4, 4') et/ou l'élément porteur (6, 6') comprennent, au niveau du fond de l'interstice, une couche de protection thermique.
  3. Chambre de combustion selon l'une des revendications 1 à 2,
    caractérisée en ce que
    la zone de bord (8, 8') de l'élément de liner (4, 4') et/ou l'élément porteur (6, 6') comprennent, au niveau du fond de l'interstice, au moins une série d'ouvertures de passage s'étendant globalement parallèlement à l'interstice (10).
  4. Chambre de combustion selon l'une des revendications 1 à 3,
    caractérisée en ce que
    l'élément de liner (4, 4') comprend, sur son côté opposé à la chambre de combustion (3), des nervures de refroidissement (14).
  5. Chambre de combustion selon l'une des revendications 1 à 4,
    caractérisée en ce que
    l'au moins une ouverture de passage (12) s'étend dans la zone de bord (8, 8') de l'élément de liner (4, 4') et/ou dans l'élément porteur (6, 6') en oblique par rapport à l'interstice (10) et forment ainsi un écoulement de gaz de refroidissement prédéfini.
  6. Chambre de combustion selon l'une des revendications 1 à 5,
    caractérisée en ce que
    une zone de transition (15) de l'élément de liner (4, 4') entre l'interstice (10) et l'espace de combustion (3) est arrondie.
  7. installation d'incinération, plus particulièrement une turbine à gaz, avec une chambre combustion selon au moins l'une des revendications 1 à 6.
EP07787170.5A 2006-08-07 2007-07-06 Chambre de combustion d'une installation d'incinération Active EP2049841B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH12602006 2006-08-07
PCT/EP2007/056887 WO2008017551A2 (fr) 2006-08-07 2007-07-06 Chambre de combustion d'une installation d'incinération

Publications (2)

Publication Number Publication Date
EP2049841A2 EP2049841A2 (fr) 2009-04-22
EP2049841B1 true EP2049841B1 (fr) 2016-12-28

Family

ID=37400851

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07787170.5A Active EP2049841B1 (fr) 2006-08-07 2007-07-06 Chambre de combustion d'une installation d'incinération

Country Status (3)

Country Link
US (1) US8006498B2 (fr)
EP (1) EP2049841B1 (fr)
WO (1) WO2008017551A2 (fr)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8495881B2 (en) * 2009-06-02 2013-07-30 General Electric Company System and method for thermal control in a cap of a gas turbine combustor
US8359865B2 (en) * 2010-02-04 2013-01-29 United Technologies Corporation Combustor liner segment seal member
US9534783B2 (en) * 2011-07-21 2017-01-03 United Technologies Corporation Insert adjacent to a heat shield element for a gas turbine engine combustor
US9021812B2 (en) 2012-07-27 2015-05-05 Honeywell International Inc. Combustor dome and heat-shield assembly
EP2711634A1 (fr) * 2012-09-21 2014-03-26 Siemens Aktiengesellschaft Bouclier thermique avec une structure porteuse et procédé de refroidissement de la structure porteuse
US9651258B2 (en) 2013-03-15 2017-05-16 Rolls-Royce Corporation Shell and tiled liner arrangement for a combustor
EP2984317B1 (fr) * 2013-04-12 2019-03-13 United Technologies Corporation Refroidissement de jonction en t de panneau de chambre de combustion
EP2952812B1 (fr) * 2014-06-05 2018-08-08 General Electric Technology GmbH Chambre de combustion annulaire d'une turbine á gaz et segment de manchon
US10655853B2 (en) 2016-11-10 2020-05-19 United Technologies Corporation Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor
US10935236B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10830433B2 (en) 2016-11-10 2020-11-10 Raytheon Technologies Corporation Axial non-linear interface for combustor liner panels in a gas turbine combustor
US10935235B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10619854B2 (en) * 2016-11-30 2020-04-14 United Technologies Corporation Systems and methods for combustor panel
US10739001B2 (en) * 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface for a gas turbine engine combustor
US10718521B2 (en) 2017-02-23 2020-07-21 Raytheon Technologies Corporation Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor
US10823411B2 (en) 2017-02-23 2020-11-03 Raytheon Technologies Corporation Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor
US10677462B2 (en) 2017-02-23 2020-06-09 Raytheon Technologies Corporation Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor
US10830434B2 (en) 2017-02-23 2020-11-10 Raytheon Technologies Corporation Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine
US11098899B2 (en) 2018-01-18 2021-08-24 Raytheon Technologies Corporation Panel burn through tolerant shell design
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
US10830435B2 (en) 2018-02-06 2020-11-10 Raytheon Technologies Corporation Diffusing hole for rail effusion
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel
US11022307B2 (en) * 2018-02-22 2021-06-01 Raytheon Technology Corporation Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling
US10995955B2 (en) * 2018-08-01 2021-05-04 Raytheon Technologies Corporation Combustor panel

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4321311A (en) * 1980-01-07 1982-03-23 United Technologies Corporation Columnar grain ceramic thermal barrier coatings
DE8618859U1 (de) * 1986-07-14 1988-01-28 Siemens AG, 1000 Berlin und 8000 München Hitzeschild
EP0419487B1 (fr) * 1988-06-13 1994-11-23 Siemens Aktiengesellschaft Bouclier thermique n'exigeant que peu de fluide de refroidissement
US5431020A (en) * 1990-11-29 1995-07-11 Siemens Aktiengesellschaft Ceramic heat shield on a load-bearing structure
GB9112324D0 (en) * 1991-06-07 1991-07-24 Rolls Royce Plc Gas turbine engine combustor
GB2298267B (en) 1995-02-23 1999-01-13 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
EP0928396B1 (fr) 1996-09-26 2001-11-21 Siemens Aktiengesellschaft Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds
DE19727407A1 (de) * 1997-06-27 1999-01-07 Siemens Ag Hitzeschild
DE29714742U1 (de) * 1997-08-18 1998-12-17 Siemens AG, 80333 München Hitzeschildkomponente mit Kühlfluidrückführung und Hitzeschildanordnung für eine heißgasführende Komponente
EP1022437A1 (fr) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Elément de construction à l'usage d'une machine thermique
US6331096B1 (en) 2000-04-05 2001-12-18 General Electric Company Apparatus and methods for impingement cooling of an undercut region adjacent a side wall of a turbine nozzle segment
EP1199520A1 (fr) * 2000-10-16 2002-04-24 Siemens Aktiengesellschaft Bouclier thermique pour parois de chambre de combustion, chambre de combustion et turbine à gaz
EP1284390A1 (fr) * 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz
DE50111316D1 (de) * 2001-08-28 2006-12-07 Siemens Ag Hitzeschildstein sowie Verwendung eines Hitzeschildsteins in einer Brennkammer
DE50212581D1 (de) * 2002-12-10 2008-09-11 Siemens Ag Gasturbine
ES2307834T3 (es) * 2003-01-29 2008-12-01 Siemens Aktiengesellschaft Camara de combustion.
US6931855B2 (en) 2003-05-12 2005-08-23 Siemens Westinghouse Power Corporation Attachment system for coupling combustor liners to a carrier of a turbine combustor
EP1507116A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
EP1650503A1 (fr) * 2004-10-25 2006-04-26 Siemens Aktiengesellschaft Méthode de refroidissement d'un bouclier thermique et bouclier thermique
EP1715248A1 (fr) * 2005-04-19 2006-10-25 Siemens Aktiengesellschaft Élément de fixation et portion correspondante d'un bouclier thermique ainsi que chambre de combustion munie d'un tel bouclier

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
WO2008017551A3 (fr) 2008-04-17
WO2008017551A2 (fr) 2008-02-14
US20090199837A1 (en) 2009-08-13
US8006498B2 (en) 2011-08-30
EP2049841A2 (fr) 2009-04-22

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