EP1390670A1 - Ensemble ecran thermique pour un composant conduisant un gaz chaud, et procede de fabrication dudit ensemble - Google Patents

Ensemble ecran thermique pour un composant conduisant un gaz chaud, et procede de fabrication dudit ensemble

Info

Publication number
EP1390670A1
EP1390670A1 EP02750960A EP02750960A EP1390670A1 EP 1390670 A1 EP1390670 A1 EP 1390670A1 EP 02750960 A EP02750960 A EP 02750960A EP 02750960 A EP02750960 A EP 02750960A EP 1390670 A1 EP1390670 A1 EP 1390670A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
sealing element
sealing
groove
arrangement
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.)
Withdrawn
Application number
EP02750960A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP02750960A priority Critical patent/EP1390670A1/fr
Publication of EP1390670A1 publication Critical patent/EP1390670A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/0003—Linings or walls
    • 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
    • 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
    • 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
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05005—Sealing means between wall tiles or panels
    • 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
    • F23R2900/00012—Details of sealing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/04—Casings; Linings; Walls; Roofs characterised by the form, e.g. shape of the bricks or blocks used
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/14—Supports for linings
    • F27D1/145—Assembling elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D99/00—Subject matter not provided for in other groups of this subclass
    • F27D99/0073—Seals

Definitions

  • Heat shield arrangement for a component carrying hot gas in particular for structural parts of gas turbines, and method for producing such an arrangement
  • the invention relates to a heat shield arrangement for a component carrying hot gas, in particular for structural parts of gas turbines. It also relates to a method for producing such an arrangement.
  • the arrangement contains a plurality of heat shield elements, which are arranged side by side on a support structure and are anchored to it.
  • EP 0 224 817 B1 describes a heat shield arrangement, in particular for structural parts of gas turbine plants, which is formed from a number of triangular heat shield elements.
  • the heat shield elements are arranged side by side, each leaving a gap on a support structure and screwed to the support structure.
  • Support structure can come into contact, so that the material of the support structure can be damaged due to the resulting massive heat.
  • a disadvantage of such an arrangement is that, for example, the insertion or removal of a heat shield element of such an arrangement cannot take place independently of its adjacent heat shield elements.
  • the heat shield elements cannot simply be anchored independently of one another to the supporting structure, but rather a larger gap must first be formed between the heat shield elements, the sealing element being used
  • Gap are reduced and the heat shield elements are finally anchored to the support structure.
  • the invention is therefore based on the object of specifying a heat shield arrangement for a hot gas-carrying structure, in particular a metallic component of a gas turbine system or combustion chamber, with heat shield elements anchored alongside one another on a support structure, and a method for producing such a heat shield arrangement, which in particular overcome the disadvantages described , flexible in use and particularly easy and quick to manufacture.
  • the object is achieved according to the invention by a heat shield arrangement with area-wide heat shield elements anchored side by side on a support structure, in which at least two adjacent heat shield elements each have at least one lateral groove, which is provided in the region of the edge of their surface facing the hot gas, these heat shield elements by means of at least of a sealing element introduced into the groove and in which the sealing element is designed as a sealing flap,
  • -Which-. can be moved from a first to a second position and vice versa, the first position being an open position without a sealing effect and the second position being a closed position with a sealing effect.
  • a heat shield arrangement according to the invention on the one hand, the support structure is protected from contact with hot gas emerging from the combustion chamber by the sealing element, which closes gaps between the heat shield elements of the heat shield arrangement.
  • a heat shield arrangement according to the invention is easy to produce and detach because of the special design of the sealing element as a sealing flap, because the sealing element can be moved from a first position into a second position or vice versa when it is inserted or detached, so that the sealing element automatically moves when the arrangement according to the invention is produced its first position (open position) is moved into its second position (closed position) and is automatically moved from its second to its first position when the arrangement according to the invention is released.
  • the sealing element can be moved from the first to the second position and vice versa by means of a movement of a heat shield element.
  • Sealing elements are not introduced into the arrangement according to the invention in a separate working step, but rather the sealing elements automatically move into their second (closed) position as a result of the movement of a heat shield element to be used, without the anchoring of adjacent heat shield elements having to be released from the support structure.
  • the sealing element advantageously has a substantially C-shaped cross section. Such a cross section of the
  • Sealing element is particularly suitable since the (longitudinal) slot formed in this way can be used particularly easily to hold the sealing element in the first position, for example by plugging the slot of the sealing element onto the wall of a groove and thus holding it in the first position ,
  • the sealing element is designed as a curved plate.
  • the sealing element is particularly easy to manufacture if it is produced by bending a plate, since a large number of raw materials are available in the form of plates.
  • the plate is advantageously made of sheet metal.
  • Sheet metal is characterized by a high resistance to heat, so that sheet metal is particularly suitable as a sealing element in the heat shield arrangement according to the invention. Furthermore, sheet metal is easily available, inexpensive and particularly easy to process.
  • the invention furthermore leads to a method for producing a heat shield arrangement according to the invention with the following steps:
  • a first and a second heat shield element are anchored on the support structure, leaving a space for a third heat shield element, so that the groove 'of the first heat shield element lies opposite the groove of the second heat shield element.
  • a sealing element is introduced into the groove of the first and the second heat shield element in such a way that the sealing element is held in the first position.
  • the third heat shield element which has a groove on opposite sides in each case, is moved into the intermediate space in the direction of the support structure, a sealing element in each case projecting into one of these grooves.
  • the third heat shield element is anchored on the support structure.
  • the seal between the heat shield elements is formed automatically without manual work being carried out.
  • ⁇ step is necessary:
  • the sealing element designed as a sealing flap is automatically moved from its first (open) to its second (closed) position, for example being compressed and inserted into the groove, advantageously in the form of a rotary movement.
  • the compression of the sealing element improves the sealing effect when the "prestressed” sealing element is finally introduced into the groove in close contact with the walls of the groove and also secures the second position (closed position) of the sealing flap against falling out of the groove.
  • FIG 3 shows an embodiment of a sealing element for a heat shield arrangement according to the invention.
  • FIG. 1 A heat shield arrangement 5 according to the invention is shown in FIG.
  • the heat shield arrangement 5 protects a support structure 15 from the destructive influence of hot gas, which is formed in a combustion chamber 10.
  • the heat shield arrangement 5 comprises heat shield elements 20, which are arranged side by side on the support structure 15 and are anchored thereon by means of fastening elements 35, for example screw connections.
  • sealing elements 30 In order to prevent the support structure 15 from being damaged or destroyed, the gaps between the heat shield elements 20 described above are sealed by means of sealing elements 30.
  • the heat shield elements 20 each have at least one lateral groove 25, which is provided in the region of the edge of their surface facing the hot gas.
  • a sealing element 30 is introduced into the grooves 25 of adjacent heat shield elements 20.
  • the sealing element 30 is a sealing flap designed in such a way that it can be moved from a first to a second position, the first position being an open position without a sealing effect and the second position being a closed position with a sealing effect. 1 shows the sealing elements 30 in the second position.
  • the sealing elements 30 advantageously have a substantially C-shaped cross section.
  • the sealing elements 30 can be produced, for example, from a flat plate, which preferably consists of sheet metal, and which is processed by bending in such a way that it has a C-shaped cross section.
  • Such a C-shaped sealing flap has an elasticity that enables a resilient contact with the heat shield elements and a good seal.
  • the first position of the sealing element 30, which is not shown in FIG. 1, can be formed, for example, in that a sealing element 30 with its (longitudinal) slot formed on account of the C-shaped cross section on the side of the combustion O 02/097332
  • Chamber 10 closer edge of the groove 25 is held, in which said wall protrudes into the slot (see FIG. 2b and 2c).
  • FIG. 2 shows steps a) to e) of the method according to the invention.
  • step a a first and a second heat shield element 51, 52 are anchored to the support structure, leaving a space for a third heat shield element 53, for example by means of a scraper joint 65, so that the groove of the first heat shield element 51 is opposite the groove of the second heat shield element 52.
  • step b) is in the groove 55 of the first and the second
  • Heat shield elements 51, 52 each introduced a sealing element 60 such that the sealing element 60 is held in the first position (open position without a sealing effect).
  • the first position is that an edge 56 of a groove 55, which is closer to the combustion chamber 40, is inserted into a (longitudinal) slot 61 of the sealing element 60. , .. ... -
  • step c) the third heat shield element 53, which in each case has a groove 55 on opposite sides, is moved into the intermediate space in direction B, a sealing element 60 projecting into one of the previously described grooves of the third heat shield element 53.
  • step d) the movement B of the third heat shield element 53 moves the sealing element 60 into the second position (closed position with a sealing effect).
  • the sealing element 60 can be compressed to achieve an improved sealing effect and can be inserted into the groove 55, for example, by means of a rotary movement.
  • step e) the third heat shield element 53 is finally anchored on the support structure 45, for example by means of a screw connection 65.
  • the sealing element 60 can be moved by means of the movement B of the third heat shield element 53 both into the second position and by a movement of the third heat shield element 53 in the opposite direction to B into the first position, so that the arrangement according to the invention can also be easily released, without e.g. having to remove the sealing element in a separate, manual work step.
  • FIG. 3 shows an exemplary embodiment of a sealing element 80 for use in a heat shield arrangement according to the invention and / or in the method according to the invention.
  • the sealing element 80 is designed as a hollow tube, for example made of sheet metal, which has an oval, essentially C-shaped O 02/097332
  • This hollow tube has a slot 85 which extends essentially over the entire length of the sealing element 80.
  • the slot 85 is particularly suitable for holding the sealing element 80 in its first position (open position without a sealing effect), for example by inserting one of the boundary walls of a groove of a heat shield element into the slot 85 and in this way the sealing element 80 in the first position is held (see, for example, also FIG. 2, step “b); The part of the sealing element 80 which projects beyond the 'groove ' can then be reached by the movement of a heat shield element and the sealing element 80 can thereby be moved into the second position.
  • the sealing element 80 preferably consists of sheet metal, which has been brought into the shape according to FIG. 3, for example by bending.

Landscapes

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

Abstract

Ensemble écran thermique pour un composant conduisant un gaz chaud, en particulier pour parties structurales de turbines à gaz, et procédé de fabrication dudit ensemble. Selon la présente invention, l'ensemble écran thermique (5) pour une structure conduisant du gaz chaud, en particulier pour une partie structurale métallique d'un ensemble turbine à gaz ou d'une chambre de combustion (10), possède des éléments écrans thermiques (20) fixés les uns à côté des autres sur une structure de support (15) de manière à couvrir une surface. Lesdits éléments (20) possèdent chacun au moins une rainure (25) latérale située dans la zone du bord de leur face orientée vers le gaz chaud. Au moins deux éléments (20) voisins sont reliés à l'aide d'au moins un élément d'étanchéité (30) introduit dans la rainure (25) et l'élément d'étanchéité (30) est conçu sous forme de clapet étanche qui peut être déplacé entre une première et une seconde position et inversement. La première position correspond à une position ouverte sans effet d'étanchéité et la seconde position correspond à une position fermée avec effet d'étanchéité. Selon ledit procédé, le clapet d'étanchéité est déplacé de la première dans la seconde position grâce au mouvement d'un élément écran thermique (53).
EP02750960A 2001-05-25 2002-05-21 Ensemble ecran thermique pour un composant conduisant un gaz chaud, et procede de fabrication dudit ensemble Withdrawn EP1390670A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02750960A EP1390670A1 (fr) 2001-05-25 2002-05-21 Ensemble ecran thermique pour un composant conduisant un gaz chaud, et procede de fabrication dudit ensemble

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP01112710A EP1260767A1 (fr) 2001-05-25 2001-05-25 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz, ainsi que le procédé de fabrication d'un tel ensemble
EP01112710 2001-05-25
EP02750960A EP1390670A1 (fr) 2001-05-25 2002-05-21 Ensemble ecran thermique pour un composant conduisant un gaz chaud, et procede de fabrication dudit ensemble
PCT/EP2002/005578 WO2002097332A1 (fr) 2001-05-25 2002-05-21 Ensemble ecran thermique pour un composant conduisant un gaz chaud, et procede de fabrication dudit ensemble

Publications (1)

Publication Number Publication Date
EP1390670A1 true EP1390670A1 (fr) 2004-02-25

Family

ID=8177545

Family Applications (2)

Application Number Title Priority Date Filing Date
EP01112710A Withdrawn EP1260767A1 (fr) 2001-05-25 2001-05-25 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz, ainsi que le procédé de fabrication d'un tel ensemble
EP02750960A Withdrawn EP1390670A1 (fr) 2001-05-25 2002-05-21 Ensemble ecran thermique pour un composant conduisant un gaz chaud, et procede de fabrication dudit ensemble

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP01112710A Withdrawn EP1260767A1 (fr) 2001-05-25 2001-05-25 Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz, ainsi que le procédé de fabrication d'un tel ensemble

Country Status (5)

Country Link
US (1) US7021061B2 (fr)
EP (2) EP1260767A1 (fr)
JP (1) JP2004526936A (fr)
CN (1) CN1250908C (fr)
WO (1) WO2002097332A1 (fr)

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ES2528177T3 (es) * 2004-01-21 2015-02-05 Siemens Aktiengesellschaft Barrera de flujo, revestimiento y cámara de combustión
ATE514905T1 (de) 2004-04-30 2011-07-15 Siemens Ag Spaltdichtelement für einen hitzeschild
US8695989B2 (en) 2004-04-30 2014-04-15 Siemens Aktiengesellschaft Hot gas seal
LU91455B1 (en) * 2008-06-06 2009-12-07 Wurth Paul Sa Gap-filler insert for use with cooling plates for a metallurgical furnace
US9945484B2 (en) * 2011-05-20 2018-04-17 Siemens Energy, Inc. Turbine seals
US10378775B2 (en) 2012-03-23 2019-08-13 Pratt & Whitney Canada Corp. Combustor heat shield
EP2657455A1 (fr) * 2012-04-27 2013-10-30 Siemens Aktiengesellschaft Écran thermique et procédé de construction associé
EP2685052A1 (fr) * 2012-07-10 2014-01-15 Siemens Aktiengesellschaft Écran thermique et procédé de construction associé
US9771818B2 (en) 2012-12-29 2017-09-26 United Technologies Corporation Seals for a circumferential stop ring in a turbine exhaust case
EP3025030B1 (fr) * 2013-07-24 2021-04-21 Raytheon Technologies Corporation Joint à rainure destiné à un moteur à turbine à gaz
US8984896B2 (en) 2013-08-23 2015-03-24 Pratt & Whitney Canada Corp. Interlocking combustor heat shield panels
US9534784B2 (en) 2013-08-23 2017-01-03 Pratt & Whitney Canada Corp. Asymmetric combustor heat shield panels
US10816201B2 (en) * 2013-09-13 2020-10-27 Raytheon Technologies Corporation Sealed combustor liner panel for a gas turbine engine
JP6366180B2 (ja) * 2014-09-26 2018-08-01 三菱日立パワーシステムズ株式会社 シール構造
DE102016114177B4 (de) * 2016-04-15 2023-11-23 Jünger+Gräter GmbH Feuerfestschutzsegment
US10739001B2 (en) 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface 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
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
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
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
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine

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Also Published As

Publication number Publication date
WO2002097332A1 (fr) 2002-12-05
CN1511242A (zh) 2004-07-07
US20040206087A1 (en) 2004-10-21
US7021061B2 (en) 2006-04-04
JP2004526936A (ja) 2004-09-02
CN1250908C (zh) 2006-04-12
EP1260767A1 (fr) 2002-11-27

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