EP0724116A2 - Garniture céramique - Google Patents

Garniture céramique Download PDF

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Publication number
EP0724116A2
EP0724116A2 EP96810022A EP96810022A EP0724116A2 EP 0724116 A2 EP0724116 A2 EP 0724116A2 EP 96810022 A EP96810022 A EP 96810022A EP 96810022 A EP96810022 A EP 96810022A EP 0724116 A2 EP0724116 A2 EP 0724116A2
Authority
EP
European Patent Office
Prior art keywords
fastening element
ceramic
wall
ceramic lining
lining according
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Withdrawn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
EP96810022A
Other languages
German (de)
English (en)
Other versions
EP0724116A3 (fr
Inventor
Andreas Dr. Pfeiffer
Hugo Wetter
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.)
ABB AG Germany
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0724116A2 publication Critical patent/EP0724116A2/fr
Publication of EP0724116A3 publication Critical patent/EP0724116A3/fr
Withdrawn legal-status Critical Current

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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
    • F23M5/04—Supports for linings
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • 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
    • F23M2900/05004—Special materials for walls or lining

Definitions

  • the invention relates to a ceramic lining for thermally highly stressed walls of combustion chambers, in particular combustion chambers for gas turbines, the lining consisting of individual elements which are fastened to the metallic wall by means of holding devices.
  • the lining with refractory elements based on oxidic materials can be regarded as state of the art.
  • these bricks In addition to the low mechanical stability and the thick-walled, heavy construction, these bricks have the disadvantage that the individual elements cannot be dismantled without being destroyed.
  • the material properties of the oxidic materials used for these linings are not up to the increasing mechanical and thermal loads, for example in gas turbine combustion chambers.
  • the high-temperature-resistant structural ceramics available today such as silicon carbide SiC and silicon nitride Si 3 N 4 , are not suitable for use in industrial combustion chambers as linings with a form-fitting structure made up of individual elements without a fixed connection of the parts.
  • the invention tries to avoid all these disadvantages. It is based on the task of creating an uncooled, releasable lining of a combustion chamber with ceramic elements, which can withstand the high mechanical and thermal stresses in a commercial, highly stressed combustion chamber.
  • a ceramic lining for combustion chambers consisting of at least one wall plate made of high-temperature-resistant structural ceramic with at least one through opening and of one fastening element per opening, the fastening element being fastened with its foot in a metallic holding device fastened to the metallic supporting wall is and the head of the fastening element rests in the opening of the wall plate, and wherein an insulation layer is arranged between the metallic wall and the ceramic wall plate, the fastening element made of high-temperature-resistant structural ceramics is resiliently connected to the holding device.
  • the advantages of the invention can be seen, inter alia, in the fact that the lining can withstand very high mechanical and thermal stresses due to its homogeneity and the material used, that the lining can be disassembled without destruction and can therefore be used repeatedly and that due to the spring-elastic connection of the ceramic structure to the metal holding structure, the thermal expansions between metallic and ceramic components or deformations of the insulation layer are absorbed by mechanical stresses.
  • the fastening element has a shape which is optimized from a thermal point of view, preferably an arch in the middle of the head, one rounded head and rounded cross-sectional transitions with large radii from head to shaft and from shaft to foot. This ensures that the mechanical and thermal stresses cause only low stresses.
  • the shaft of the fastening element is surrounded by a divided sleeve made of solidified, preformed insulation material and the contact surfaces to the metal in the region of the foot of the fastening element are also provided with an insulating layer. This leads to a minimization of the temperature gradient within the ceramic fastening element, so that the thermal stresses can be kept at a low level.
  • the wall plate is drawn in in the area of the opening in the direction of the metallic supporting wall, so that the head of the fastening element is completely received by the opening in the ceramic wall plate.
  • the insulation layer consists of ceramic fiber material, which can be applied in the form of prefabricated blocks.
  • the insulation layer is advantageously solidified at least in the region of the butt joint of the adjacent wall panels or is otherwise protected on the surface. This prevents the insulation from being flushed out in the case of parasitic hot air flows in the gap.
  • the insulation layer has a bore in the area of the fastening element to be received.
  • the metallic holding device consists of a longitudinally divided threaded sleeve, which comprises the foot of the fastening element, with one on the external thread the sleeve seated nut, and a guide ring embedded in the metallic wall, a guide sleeve and spring elements.
  • a reliable, removable and easily adjustable connection between the base of the ceramic fastening element and the metallic parts is thereby achieved.
  • a seal is advantageously arranged between the guide sleeve and the guide ring. This prevents possible leakage air flows that could occur due to the generally positive pressure drop between the outer, cooling air side and the inner, hot gas side of the lining.
  • FIG. 1 shows a partial longitudinal section of the lining according to the invention for a gas turbine combustion chamber.
  • An insulation layer 2 is applied to the metallic support wall 1 of the combustion chamber.
  • This preferably consists of ceramic fiber material.
  • the wall plates 3 and the insulation layer 2 are fastened to the metal supporting wall 1 with the aid of fastening elements 4, which are each arranged in a metallic holding device 5, which will be described in detail later.
  • these fastening elements 4 also consist of high-temperature-resistant structural ceramics.
  • the outer shape and the dimensions of the wall panels 3 can be easily adapted to the geometry of the room to be lined and are in no way predetermined.
  • the wall panels 3 shows a further possible shape of the wall panels 3.
  • they have a hexagonal outer contour.
  • symmetrical shapes are preferred.
  • the thickness d of the wall plate 3 results on the one hand from the required mechanical stability and on the other hand from minimizing the thermal stresses due to temperature gradients in the component.
  • a through opening 6 for receiving a fastening element 4, which here is a bolt consisting of head, shaft and foot.
  • a fastening element 4 which here is a bolt consisting of head, shaft and foot.
  • a plurality of openings 6 can also be present in each wall plate 3.
  • FIG. 4 which shows an enlarged section of the wall plate 3 according to FIG. 2 in the region of the opening 6 along the line IV-IV, the opening 6 is drawn in in the direction of the metallic supporting wall 1.
  • this increases the contact area between the fastening element 4 and the wall plate 3, and on the other hand the heat flows in the case of stationary and unsteady load gradients are influenced in such a way that only minimal thermal stresses arise.
  • the geometric design of this zone results from a coordination between the heat storage and heat conduction properties of the materials used.
  • a ratio of the thickness d of the wall plate 3 to the depth t of the drawn-in part of the wall plate 3 in the region of the opening 6 of approximately 5 to 3 has proven to be advantageous.
  • the contact surface between the head of the fastening element 4 (not shown in FIG. 4) arranged in the opening 6 and the wall plate 3 is optimally spherical in order to ensure a flat contact even with small angular positions of the bolt (ball head principle).
  • the head of the fastening element 4 is also spherical, as can be seen in FIGS. 5a and 5b, which each show a longitudinal section of two differently designed fastening elements 4.
  • the foot of the fastening element 4 is also spherical, which is then received by a correspondingly designed threaded sleeve 7 of the metal holding device 5. Since the metal / ceramic contact surface at the foot of the fastening element 4 is also spherical, a flat contact is also ensured here even at small angular positions.
  • fastening element 4 which is optimized in terms of thermal technology, is that the head of the fastening element 4 has a bulge 8 in its center.
  • large radii and moderate cross-section transitions are used, so that basic rules for designing with brittle ceramic materials are observed.
  • the cavity between the shaft of the fastening element 4 and the insulation layer 2 is filled by a split sleeve 15 made of solidified, preformed insulation material. Since the contact surfaces to the metal in the area of the foot of the fastening element 4 are also provided with an insulating intermediate layer, the temperature gradients within the fastening element 4 are minimized and the thermal stresses are kept at a low level.
  • the thickness of the insulation layer 2 is selected in accordance with the thermal load on the overall composite of the lining. It is to be determined in such a way that the maximum permissible temperatures of the metal supporting wall 1 are not exceeded.
  • the insulation material can be applied, for example, in the form of prefabricated blocks, a corresponding hole having to be provided in the area of the fastening bolt 4 for the assembly of the lining. Since the mounting distance between two wall plates 3 is determined by the thermal expansions of the wall plates 3, it is at least in the range underneath the butt joints of two adjacent plate elements, the surface of the insulation material is suitably solidified or otherwise protected, so that the insulation layer 2 is avoided in the gap in the case of parasitic hot air flows.
  • a central point of the invention is the stretch-tolerant elastic clamping of the ceramic fastening element 4 on the outside of the metal supporting wall 1.
  • the metallic holding device 5 consists of a longitudinally divided threaded sleeve 7, which comprises the foot of the fastening element.
  • a threaded nut 9 is arranged, via which, as will be explained further below, the clamping force can be adjusted.
  • the nut 9 holds the two halves of the threaded sleeve 7 together.
  • the mutual positioning of the two threaded sleeve halves can be achieved by additional construction elements, e.g. the bolts.
  • a square 10 serves to hold the split sleeve when tightening the threaded nut 9. Positions 7 and 10 are part of the split sleeve.
  • the metallic holding device 5 consists of a guide ring 11 embedded in the metallic supporting wall 1, a one-piece guide sleeve 12 for the fastening element 4 and spring elements 13 arranged between the guide sleeve 12 and the guide ring 11.
  • the spring 13 is, for example, as in FIG. 1 shown a disc spring.
  • the spring-elastic connection of the ceramic structure to the metallic holding device ensures that thermal relative expansions between the metallic and ceramic components or deformations of the insulation layer 2 ("setting") are absorbed by mechanical stresses, for example pulsations in the combustion chamber, without the contact surfaces impermissibly high voltages in the ceramic component can be induced. Almost constant clamping forces are ensured via a certain spring travel of the clamping (adjustable via the threaded nut 9 screwed onto the external thread of the sleeve 7).
  • a seal 14 is arranged against possible leakage air flows.
  • This seal 14 is located between the guide sleeve 12 and the guide ring 11 embedded in the metallic support wall 1. The play in the guide also allows a certain angular position of the bolt without additional forces being introduced into the bolt.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ceramic Engineering (AREA)
  • Connection Of Plates (AREA)
  • Furnace Housings, Linings, Walls, And Ceilings (AREA)
EP96810022A 1995-01-28 1996-01-10 Garniture céramique Withdrawn EP0724116A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19502730A DE19502730A1 (de) 1995-01-28 1995-01-28 Keramische Auskleidung
DE19502730 1995-01-28

Publications (2)

Publication Number Publication Date
EP0724116A2 true EP0724116A2 (fr) 1996-07-31
EP0724116A3 EP0724116A3 (fr) 1997-12-03

Family

ID=7752579

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810022A Withdrawn EP0724116A3 (fr) 1995-01-28 1996-01-10 Garniture céramique

Country Status (4)

Country Link
US (1) US5624256A (fr)
EP (1) EP0724116A3 (fr)
JP (1) JPH08296976A (fr)
DE (1) DE19502730A1 (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0895028A1 (fr) * 1997-07-28 1999-02-03 Abb Research Ltd. Garniture céramique
EP0895027A1 (fr) * 1997-07-28 1999-02-03 Abb Research Ltd. Garniture céramique
DE19825546C1 (de) * 1998-06-08 1999-08-26 Didier Werke Ag Einrichtung zum Befestigen von Auskleidungsplatten
WO1999047874A1 (fr) * 1998-03-19 1999-09-23 Siemens Aktiengesellschaft Segment de paroi pour une chambre de combustion, et chambre de combustion
EP1072573A1 (fr) 1999-07-30 2001-01-31 Siemens Aktiengesellschaft Procédé de fabrication d'une pièce réfractaire et brique céramique de chambre de combustion
EP1126221A1 (fr) 2000-02-17 2001-08-22 Siemens Aktiengesellschaft Tuile réfractaire rembourrée pour révêtement d'une chambre de combustion de turbies à gaz
EP1191285A1 (fr) 2000-09-22 2002-03-27 Siemens Aktiengesellschaft Bouclier thérmique , chambre de combustion avec garnissage interne et turbine à gaz
DE10046094A1 (de) * 2000-09-18 2002-05-02 Siemens Ag Hitzeschildstein zur Auskleidung einer Brennkammerwand, Brennkammer sowie Gasturbine
EP1712840A1 (fr) * 2005-04-13 2006-10-18 Siemens Aktiengesellschaft Bouclier thermique avec boulon de fixation
EP1862740A1 (fr) * 2006-05-31 2007-12-05 Siemens Aktiengesellschaft Paroi de chambre de combustion
EP1710501A3 (fr) * 1999-11-06 2008-01-23 Rolls-Royce plc Eléments de paroi pour turbomachine
US7540710B2 (en) 2003-10-27 2009-06-02 Siemens Aktiengesellschaft Turbine blade for use in a gas turbine
US7793503B2 (en) 2003-08-22 2010-09-14 Siemens Aktiengesellschaft Heat shield block for lining a combustion chamber wall, combustion chamber and gas turbine
WO2010105709A2 (fr) 2009-03-17 2010-09-23 Siemens Aktiengesellschaft Élément de protection thermique d'un bouclier thermique
US7942007B2 (en) 2005-04-19 2011-05-17 Siemens Aktiengesellschaft Heat shield element for lining a combustion chamber wall, combustion chamber and gas turbine
CH703656A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Von Heissgasen durchströmbarer Gehäusekörper mit innerem Hitzeschild.

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JP2942254B2 (ja) * 1997-10-27 1999-08-30 タキ産業株式会社 高温炉内張り用セラミックファイバブロック
DE19748259A1 (de) * 1997-10-31 1999-05-06 Bosch Gmbh Robert Brennkammer für Warmwasserbereiter, insbesondere Gasheizgeräte
DE59806717D1 (de) 1998-03-17 2003-01-30 Alstom Switzerland Ltd Keramische Auskleidung einer Brennkammer
EP1006315B1 (fr) 1998-11-30 2004-01-21 ALSTOM (Switzerland) Ltd Garnissage céramique d'une chambre de combustion
DE19927491A1 (de) * 1999-06-16 2000-12-21 Kalenborn Kalprotect Dr Maurit Auskleidungsplattenbefestigung
JP4747443B2 (ja) * 2001-06-21 2011-08-17 Ｊｆｅスチール株式会社 ベンチュリ・スクラバー
EP1288601B1 (fr) * 2001-08-28 2006-10-25 Siemens Aktiengesellschaft Brique de protection thermique ainsi que son utilisation dans une chambre de combustion
DE10154285A1 (de) * 2001-11-05 2003-05-15 Rolls Royce Deutschland Hitzeschildanordnung mit kragenförmigem Befestigungsbereich
EP1389714A1 (fr) * 2002-08-16 2004-02-18 Siemens Aktiengesellschaft Chambre à combustion de turbine à gaz
EP1533572A1 (fr) * 2003-11-24 2005-05-25 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz et turbine à gaz
DE102006060857B4 (de) 2006-12-22 2014-02-13 Deutsches Zentrum für Luft- und Raumfahrt e.V. CMC-Brennkammerauskleidung in Doppelschichtbauweise
US8771604B2 (en) * 2007-02-06 2014-07-08 Aerojet Rocketdyne Of De, Inc. Gasifier liner
DE102007062699A1 (de) 2007-12-27 2009-07-02 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerauskleidung
EP2270395B1 (fr) * 2009-06-09 2015-01-14 Siemens Aktiengesellschaft Agencement d'élément de bouclier thermique et procédé de montage d'un élément de bouclier thermique
DE102011075865A1 (de) * 2011-05-16 2012-11-22 Siemens Aktiengesellschaft Brennkammerseitig verschraubte Brennereinsatzplatte
US9422865B2 (en) * 2013-03-14 2016-08-23 Rolls-Royce Corporation Bi-metal fastener for thermal growth compensation
WO2015009384A1 (fr) * 2013-07-16 2015-01-22 United Technologies Corporation Turbine à gaz pourvue d'un panneau en céramique
US10451280B2 (en) * 2015-02-16 2019-10-22 United Technologies Corporation Combustor panel having material transition region
EP3104079B1 (fr) * 2015-06-08 2018-10-31 ANSALDO ENERGIA S.p.A. Chambres de combustion de turbines à gaz ayant un dispositif d'ancrage de boucliers thermiques
US10767863B2 (en) * 2015-07-22 2020-09-08 Rolls-Royce North American Technologies, Inc. Combustor tile with monolithic inserts
GB2540769A (en) * 2015-07-27 2017-02-01 Rolls Royce Plc Combustor for a gas turbine engine
DE102015217161A1 (de) * 2015-09-04 2017-03-09 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe mit einer Brennkammerschindel für eine Gasturbine
DE102016211613A1 (de) 2016-06-28 2017-12-28 Siemens Aktiengesellschaft Hitzeschildanordnung einer Brennkammer mit Tellerfederpaket
US10969106B2 (en) * 2019-08-13 2021-04-06 General Electric Company Axial retention assembly for combustor components of a gas turbine engine
US20240230234A9 (en) * 2022-10-24 2024-07-11 HarbisonWalker International Holdings, Inc. Apparatus and method for preventing lining disruptions exposed to elevated temperature

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Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0895027A1 (fr) * 1997-07-28 1999-02-03 Abb Research Ltd. Garniture céramique
US5957067A (en) * 1997-07-28 1999-09-28 Abb Research Ltd. Ceramic liner
US6145452A (en) * 1997-07-28 2000-11-14 Abb Research Ltd. Ceramic lining
EP0895028A1 (fr) * 1997-07-28 1999-02-03 Abb Research Ltd. Garniture céramique
US6612248B2 (en) 1998-03-19 2003-09-02 Siemens Aktiengesellschaft Wall segment for a combustion area, and a combustion area
WO1999047874A1 (fr) * 1998-03-19 1999-09-23 Siemens Aktiengesellschaft Segment de paroi pour une chambre de combustion, et chambre de combustion
US6397765B1 (en) 1998-03-19 2002-06-04 Siemens Aktiengesellschaft Wall segment for a combustion chamber and a combustion chamber
DE19825546C1 (de) * 1998-06-08 1999-08-26 Didier Werke Ag Einrichtung zum Befestigen von Auskleidungsplatten
EP1072573A1 (fr) 1999-07-30 2001-01-31 Siemens Aktiengesellschaft Procédé de fabrication d'une pièce réfractaire et brique céramique de chambre de combustion
EP1710501A3 (fr) * 1999-11-06 2008-01-23 Rolls-Royce plc Eléments de paroi pour turbomachine
EP1126221A1 (fr) 2000-02-17 2001-08-22 Siemens Aktiengesellschaft Tuile réfractaire rembourrée pour révêtement d'une chambre de combustion de turbies à gaz
WO2001061250A1 (fr) 2000-02-17 2001-08-23 Siemens Aktiengesellschaft Pierre de protection thermique et dispositif de garniture d'une paroi de chambre de combustion et turbine a gaz
DE10046094A1 (de) * 2000-09-18 2002-05-02 Siemens Ag Hitzeschildstein zur Auskleidung einer Brennkammerwand, Brennkammer sowie Gasturbine
DE10046094C2 (de) * 2000-09-18 2002-09-19 Siemens Ag Hitzeschildstein zur Auskleidung einer Brennkammerwand
US6832484B2 (en) 2000-09-22 2004-12-21 Siemens Aktiengesellschaft Heat-shield brick, combustion chamber comprising an internal, combustion chamber lining and a gas turbine
EP1191285A1 (fr) 2000-09-22 2002-03-27 Siemens Aktiengesellschaft Bouclier thérmique , chambre de combustion avec garnissage interne et turbine à gaz
US7793503B2 (en) 2003-08-22 2010-09-14 Siemens Aktiengesellschaft Heat shield block for lining a combustion chamber wall, combustion chamber and gas turbine
US8857190B2 (en) 2003-10-27 2014-10-14 Siemens Aktiengesellschaft Heat shield element, in particular for lining a combustion chamber wall
US7805945B2 (en) 2003-10-27 2010-10-05 Siemens Aktiengesellschaft Thermal shield, especially for lining the wall of a combustion chamber
US7540710B2 (en) 2003-10-27 2009-06-02 Siemens Aktiengesellschaft Turbine blade for use in a gas turbine
EP1712840A1 (fr) * 2005-04-13 2006-10-18 Siemens Aktiengesellschaft Bouclier thermique avec boulon de fixation
US7942007B2 (en) 2005-04-19 2011-05-17 Siemens Aktiengesellschaft Heat shield element for lining a combustion chamber wall, combustion chamber and gas turbine
WO2007137883A1 (fr) * 2006-05-31 2007-12-06 Siemens Aktiengesellschaft Paroi de chambre de combustion
US8069670B2 (en) 2006-05-31 2011-12-06 Siemens Aktiengesellschaft Combustion chamber wall
RU2437034C2 (ru) * 2006-05-31 2011-12-20 Сименс Акциенгезелльшафт Стенка камеры сгорания и газовая турбина
EP1862740A1 (fr) * 2006-05-31 2007-12-05 Siemens Aktiengesellschaft Paroi de chambre de combustion
WO2010105709A2 (fr) 2009-03-17 2010-09-23 Siemens Aktiengesellschaft Élément de protection thermique d'un bouclier thermique
WO2010105709A3 (fr) * 2009-03-17 2011-04-14 Siemens Aktiengesellschaft Élément de protection thermique d'un bouclier thermique
CN102356277A (zh) * 2009-03-17 2012-02-15 西门子公司 热屏装置的热屏元件
RU2515692C2 (ru) * 2009-03-17 2014-05-20 Сименс Акциенгезелльшафт Элемент теплозащитного экрана
CN102356277B (zh) * 2009-03-17 2014-10-22 西门子公司 热屏元件和热屏以及组装热屏元件的方法和热屏的应用
CH703656A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Von Heissgasen durchströmbarer Gehäusekörper mit innerem Hitzeschild.
DE102011110660A1 (de) 2010-08-27 2012-03-15 Alstom Technology Ltd. Von Heissgasen durchströmbarer Gehäusekörper mit innerem Hitzeschild
US9810154B2 (en) 2010-08-27 2017-11-07 Ansaldo Energia Ip Uk Limited Casing body through which hot gases can flow and comprising an inner heat shield

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JPH08296976A (ja) 1996-11-12
US5624256A (en) 1997-04-29
EP0724116A3 (fr) 1997-12-03
DE19502730A1 (de) 1996-08-01

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