EP1508761A1 - Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes - Google Patents

Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes Download PDF

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Publication number
EP1508761A1
EP1508761A1 EP03019093A EP03019093A EP1508761A1 EP 1508761 A1 EP1508761 A1 EP 1508761A1 EP 03019093 A EP03019093 A EP 03019093A EP 03019093 A EP03019093 A EP 03019093A EP 1508761 A1 EP1508761 A1 EP 1508761A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
combustion chamber
edge
wall
core
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Withdrawn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
EP03019093A
Other languages
German (de)
English (en)
Inventor
Holger Grote
Andreas Heilos
Marc Tertilt
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 EP03019093A priority Critical patent/EP1508761A1/fr
Priority to EP04763502A priority patent/EP1660833A2/fr
Priority to US10/569,349 priority patent/US7793503B2/en
Priority to PCT/EP2004/008357 priority patent/WO2005022061A2/fr
Publication of EP1508761A1 publication Critical patent/EP1508761A1/fr
Withdrawn legal-status Critical Current

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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
    • F27D1/0006—Linings or walls formed from bricks or layers with a particular composition or specific characteristics
    • 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
    • F23R3/007—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
    • F27D1/0003—Linings or walls
    • F27D1/0033—Linings or walls comprising heat shields, e.g. heat shieldsd
    • 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 heat shield brick, in particular for Lining of a combustion chamber wall, with one of a hot Medium act on hot side and one of the hot side opposite Wall side and with one from the hot side to the wall side extending core area with a Core material.
  • the invention further relates to a combustion chamber with an inner combustion liner and a gas turbine.
  • a thermally and / or thermomechanically highly loaded combustion chamber such as a kiln, a hot gas duct or a combustion chamber in a gas turbine, in which a hot medium is generated and / or out, is too high for protection thermal stress with a corresponding lining Mistake.
  • the lining is usually made heat-resistant material and protects a wall of the combustion chamber before direct contact with the hot medium and the associated strong thermal load.
  • US Pat. No. 4,840,131 relates to an attachment of ceramic lining elements on a wall of a furnace.
  • a rail system which is attached to the wall is.
  • the lining elements have a rectangular shape with a planar surface and consist of a heat-insulating, refractory, ceramic fiber material.
  • U.S. Patent 4,835,831 also deals with application a refractory lining from a wall of a Furnace, in particular a vertically arranged wall.
  • a refractory lining from a wall of a Furnace, in particular a vertically arranged wall.
  • On the metallic wall of the furnace becomes one of glass, ceramic, or mineral fibers existing layer applied.
  • These Layer is attached by metallic clips or by adhesive attached to the wall.
  • On this layer is a wire mesh with .... applied meshes.
  • the mesh also serves securing the layer of ceramic fibers against Falling.
  • it is fastened by means of a bolt a uniform closed surface of refractory material applied.
  • a ceramic lining of the walls of thermally highly stressed combustion chambers for example of gas turbine combustion chambers, is described in EP 0 724 116 A2.
  • the lining consists of wall elements made of high temperature resistant structural ceramic, such. As silicon carbide (SeC) or silicon nitrite (Si 3 N 4 ).
  • the wall elements are mechanically fixed by means of a central fastening bolt to a metallic support structure (wall) of the combustion chamber.
  • a thick thermal insulation layer is provided, so that the wall element is spaced correspondingly from the wall of the combustion chamber.
  • About three times as thick in relation to the wall element insulation layer consists of ceramic fiber material, which is prefabricated in blocks.
  • the dimensions and the external shape of the wall elements are adaptable to the geometry of the space to be lined.
  • Another type of lining of a thermally highly loaded combustion chamber is given in EP 0 419 787 B1.
  • the lining consists of heat shield elements, which are mechanically supported on a metallic wall of the combustion chamber.
  • the heat shield elements touch the metallic wall directly.
  • the so-called sealing air is applied.
  • the blocking air prevents the penetration of hot medium up to the wall and at the same time cools the wall and the heat shield element.
  • WO 99/47874 relates to a wall segment for a combustion chamber and a combustion chamber of a gas turbine.
  • This is a Wall segment for a combustion chamber, which with a hot Fluid, e.g. As a hot gas, can be acted upon, with a metallic Support structure and one on the metallic support structure attached heat shield element specified.
  • a hot Fluid e.g. As a hot gas
  • the possible relative movements receive the heat shield element and the support structure and compensate.
  • Such relative movements can for example, in the combustion chamber of a gas turbine, in particular an annular combustion chamber, by different thermal expansion behavior the materials used and pulsations in the combustion chamber, during an irregular combustion for generating the hot working medium under the resonance effects may arise.
  • the separation layer can thus production-related bumps on the support structure and / or the heat shield element that is local to one unfavorable punctual force entry, balance.
  • WO 02/25173 A1 is a heat shield brick, in particular for lining a combustion chamber wall, with a hot one Medium exposable hot side, one of the hot side opposite Wall side and one to the hot side and the wall side adjacent peripheral side having a peripheral side surface has disclosed.
  • On the peripheral side is a circumferential direction provided Buchelement provided, wherein a Compressive stress is generated normal to the peripheral side surface.
  • the tension element is biased in the circumferential direction, with a certain Compressive stress is generated normal to the peripheral side surface. By this normal force, pointing towards the inside of the heat shield stone in the center of which is directed becomes the heat shield stone already secured at very low normal forces.
  • a material tear for example in Consequence of a shock load, effectively counteracted.
  • Existing material cracks can occur with appropriate arrangement and embodiment of the tension element not or only limited continue education or expand.
  • the tension element stops The heat shield brick, so to speak together and secures him on the one hand against Materialanrissen and on the other hand especially against a complete material tear. additionally becomes the danger of detachment or falling out of smaller or larger fragments in case of a possible Material tear effectively countered.
  • the object of the invention is to specify a heat shield block, which both in terms of unlimited thermal Expansion as well as in terms of its resistance a hot gas attack high reliability and long service life guaranteed.
  • Another object of the invention is the specification of a combustion chamber with an inner Combustion lining and the specification of a gas turbine with a combustion chamber.
  • the object directed to a heat shield brick is achieved according to the invention solved by a heat shield stone, in particular for lining a combustion chamber wall, with one of a hot medium acted upon hot side and one of the hot side opposite wall side, and with one of the hot side to the wall side extending core area with a core material, wherein the core portion of a peripheral region surrounded by a marginal material whose thermal conductivity lower than that of the core material.
  • the invention already starts from the knowledge, that in case of use in consequence of the edges of the heat shield stone cooling air flow through the gap between the Heat shields and the heat input to the hot side of the Heat shield block as a result of the application of hot gas, a three-dimensional temperature distribution within the Heat shield stone sets. This is marked by a Temperature drop from the hot side to the wall side and in Consequence of the sealing air cooling of the edges ("edge cooling") of central points in the ceramic heat shield stone towards the cooled edges.
  • edge cooling Consequence of the sealing air cooling of the edges
  • At typically parallel to the hot side or to the wall side flat heat shields leads the temperature gradient perpendicular to the wall surface for comparison only low thermal stresses, so long for the heat shield brick in the installed state no obstruction the thermally-induced bulge exists.
  • the invention provides a heat shield brick, whose thermal conductivity is set locally targeted to To avoid cracking and crack growth.
  • the Core area surrounded by a marginal area with a marginal material, whose thermal conductivity is lower than that of Core material. So it's going to be a two-material heat shield stone indicated with a thermal insulation in the edge area, due to the specific choice of material for the edge material, with towards the core material reduced thermal conductivity.
  • the core area and the edge area are integral components of the heat shield stone, leaving a heat shield stone with over its volume of variable thermal conductivity is provided. Due to the greater thermal conductivity in the Core area is achieved that in the core area a parallel to the hot side approximately balanced temperature profile established. The core area thus remains largely heat stress. Temperature gradients and associated therewith Thermal stresses occur only in the edge area.
  • the edge region advantageously also includes the outer edges of the heat shield stone, so this due the opposite to the core area lower thermal conductivity act as a thermal insulation or as an isolation area.
  • the length of thermo-voltage induced Cracks is shortened because these on the Edge area are limited, whereby the heat shield brick respect a cracking is stabilized.
  • the thermal conductivity of the edge material is less than 60%, in particular less than 50% of the thermal conductivity of the core material.
  • the heat shield stone is thus designed that a significant reduction in the thermal conductivity at the transition from the core area to the edge area.
  • the edge area acts as a thermal insulation, the surrounds the core area.
  • Advantageously encloses the Edge region of the core area directly, with a cohesive Composite of the core material and the edge material is realized.
  • the edge material is porous, wherein the porosity of the edge material is set specifically so that As a result, the thermal conductivity of the edge material opposite the thermal conductivity of the core material is lowered.
  • the density distribution and size distribution of the pore structure of the edge material can in the edge region the thermal conductivity depending on the requirements in case of load targeted become. It may also be possible within the Edge region a variation of local thermal conductivity via a corresponding variation of the pore size and pore diameter distribution be achieved.
  • the core material and the edge material of the same ceramic base material in particular a refractory ceramic, formed.
  • the so-called meddling Pore formers be provided in the base material.
  • the pore builder is advantageously in the near-edge region, that is pressed in the edge area of Dröhnlings or poured. During the Sinther process volatilized itself the pore builder and leaves the pores that the effective Thermal conductivity of the base material accordingly Lower. In the core area, this pore-forming agent is preferred not applied, so that the desired reduction in thermal conductivity in the transition from core area to the edge area results.
  • the axial extent of the edge region less than 20%, in particular between about 5 and 10%, the axial total extension of the heat shield stone.
  • the heat shield stone is covered at all of the edge area Edges with deviating from the core material low thermal conductivity at a distance of less than 10% of the respective Total extension (carrying length) with a lowering of the thermal conductivity opposite the thermal conductivity of the core area provided on less than 50% of the core material.
  • the edge region extends from the hot side the wall side.
  • the core area Completely enclosed by the peripheral area, so that a full-scale thermal insulation of the core area under realization of a material bond between nuclear material and edge material is reached.
  • the heat shield brick on the hot side and the wall side adjacent peripheral side having a peripheral side surface on, at least partially from the edge material is formed.
  • the gaps between the heat shield stones thereby at least partially from the edge material on the peripheral side surface limited.
  • the peripheral side surface completely formed by the core material, so that the best possible thermal insulation of Core material is given.
  • the heat shield brick consists of a ceramic Base material, in particular of a refractory ceramic.
  • a ceramic as a base material for the heat shield stone is the use of heat shield stone up to very high Temperatures safely ensured while being oxidative and / or corrosive attacks, as in the event of an attack the hot side of the heat shield brick with a hot medium, z. B. a hot gas, largely harmless for are the heat shield stone.
  • the combustion chamber can, at least with the usual maintenance cycles be operated, but also an extension of the Service life due to the lower tendency to crack propagation is achievable.
  • the task directed to a combustion chamber is according to the invention dissolved by a combustion chamber with an inner combustion liner, the heat shield stones according to the above Executions has.
  • the object directed to a gas turbine is achieved according to the invention solved by a gas turbine with such a combustion chamber.
  • the gas turbine 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive of the compressor 2 and a generator, not shown or a work machine. These are the turbine 6 and the compressor 2 on a common, as a turbine rotor designated turbine shaft 8 is arranged, with the also the generator or the work machine is connected, and which is rotatably mounted about its central axis 9.
  • a turbine rotor designated turbine shaft 8 is arranged, with the also the generator or the work machine is connected, and which is rotatably mounted about its central axis 9.
  • the type of an annular combustion chamber running combustion chamber 4 is with a number of burners 10 for burning a liquid or gaseous fuel.
  • the turbine 6 has a number of with the turbine shaft. 8 connected rotatable blades 12.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 includes a number of stationary vanes 14, which is also coronal under the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine. 6 flowing through hot medium, the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between each two in the flow direction of the Working medium M seen, consecutive blade rows or blade wreaths.
  • a successive one Pair of a ring of vanes 14 or a row of vanes and from a wreath of blades 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a so-called blade root Platform 18 on, which fixes the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparatively heavily loaded component, which is the outer boundary a hot gas channel for the turbine 6 flowing through Working medium M forms.
  • Each blade 12 is analogous via a platform 20, also referred to as a blade root attached to the turbine shaft 8.
  • each guide ring 21 is arranged between the spaced apart platforms 18 of the vanes 14 of two adjacent rows of vanes.
  • the outer one Surface of each guide ring 21 is also the hot, the turbine 6 flowing through working medium M exposed and in the radial direction from the outer end 22 of it opposed blade 12 spaced by a gap.
  • the arranged between adjacent vane rows Guide rings 21 serve in particular as cover elements, the inner wall 16 or other housing-mounting parts before a thermal overload by the the turbine 6 through flowing hot working medium M protects.
  • the combustion chamber 4 is bounded by a combustion chamber housing 29, wherein combustion chamber side a combustion chamber wall 24 is formed is.
  • the combustion chamber 4 as so-called annular combustion chamber designed in which a variety arranged circumferentially about the turbine shaft 8 around Burners open in a common combustion chamber space.
  • the combustion chamber 4 in its entirety as an annular Structure designed around the turbine shaft. 8 is positioned around.
  • the combustion chamber 4 for a comparatively high temperature the working medium M of about 1200 ° C to 1500 ° C designed. Even with these, for the materials unfavorable operating parameters to allow a comparatively long service life is the combustion chamber wall 24 on the working medium M facing side with a heat shield bricks 26th provided combustion chamber lining provided.
  • a hot gas resistant Structure of designed as an annular combustion chamber Combustion chamber 4 is the combustion chamber lining with a plurality provided by high temperature resistant heat shield stones 26, so that in this way a full-surface, largely leak-free Combustor lining is formed in the annulus.
  • FIG. 2 shows a heat shield block 26 in a perspective view, as he especially for lining a combustion chamber wall 24 is designed according to the invention.
  • the combustion chamber stone 26 has a cuboid or parallelepiped-like geometry and extends along a longitudinal axis 43 and a substantially perpendicular to the longitudinal axis 43 extending Transverse axis 45.
  • the heat shield block 26 has one of the hot medium M acted upon hot side 35 and one of Hot side 35 opposite wall 33 on. Of the Hot side 35 to the wall side 33 extends through the interior of the heat shield block 26, a core portion 31 with a Core material 39.
  • the core region 31 is from a peripheral region 37 surrounded with a border material 41, wherein the thermal conductivity of the edge material 41 is lower than the thermal conductivity of the core material 39.
  • the edge region 37 encloses the core region 31 completely along the edges of the cuboid or cuboid heat shield element 26.
  • the Material transition from the core material 39 in the core region 31 to the edge material 41 in the edge region 37 is effected by a Adhesive bond.
  • the thermal conductivity of the edge material 41 is less than 50% of the thermal conductivity of the core material 39. This ensures that when using the heat shield stone 26 in the combustion chamber 4 of a gas turbine 1 (see. Figure 1) in the core area parallel to the hot side 35th sets approximately balanced temperature profile.
  • FIG. 3 shows a sectional view along the section line III-III of the heat shield block 26 shown in FIG.
  • the core area 31 is cuboid or parallelepiped-like.
  • the border area 37 completely surrounds the core region 31 with itself the edge portion 31 from the hot side 35 to the wall side 33 extends.
  • the edge region 37 consists of a border material 41, wherein the peripheral side surface 49, the edge material 41st having.
  • the peripheral side surface 49 is the outermost Boundary surface of the peripheral side 47, which on the hot side 35 and adjacent to the wall 33.
  • the edge material 41 As a porous Material configured with a variety of pores, wherein the Porosity of the edge material 41 is set specifically, that thereby the thermal conductivity of the edge material 41st to the thermal conductivity of the core material 39 on a desired level is lowered.
  • the thermal conductivity of the Edge material 41 is for example less than 60%, in particular less than 50% of the thermal conductivity of the core material 39.
  • the core material 39 and the edge material 41 for example, from the same ceramic base material, in particular a refractory ceramic, be formed.
  • identity of the base material for the core material 39 and the edge material 41 is a particularly solid and durable material composite realized.
  • the setting of a desired porosity for lowering the thermal conductivity in the edge region 37 takes place, for example, by mixing suitable pore formers into the ceramic mass, the pore formers being pressed or cast into the edge region 37 of the drone being defined by the edge region 37.
  • the pore-forming agent volatilizes and leaves behind pores having a predetermined pore diameter distribution and pore density distribution within the edge region 37.
  • the heat-shielded brick 26 thus becomes in edge region 37 with lower thermal conductivity deviating from the core material 39, for example with a reduction in the thermal conductivity to less than 50% of the core material 39 provided.
  • the axial extent d R of the edge portion 37 is less than 20%, in particular between about 5% and 10% of the total axial extent L of the heat shield block 26. Consequently, in this embodiment, the axial extent d K of the core portion 31 with the Core material 39 significantly larger than the axial extent d R of the edge region 37.
  • FIGS. 4 to 7 show further embodiments of the heat shield block 26 with modification of the geometry of the heat shield stone 26 (see Figures 6 and 7) or with variation of Geometry of core area 31 and edge area 37.
  • FIG. 4 shows a sectional view of a heat shield element 26 with a extending from the hot side 35 to the wall 33 side Edge region 37, wherein the cross section of the edge region 37 imposed on the wall 33 side. Corresponding the cross section of the core region 31 decreases from the hot side 35 to the cold side 33 to continuously.
  • Figure 5 shows an embodiment of the heat shield stone 26, in which the edge region 37 with the edge material 41 a Partial surface of the peripheral side surface 49 forms.
  • the border area 37 faces the hot side 35 and is at the same time a component the hot side 35.
  • the peripheral side surface 49 has both the core material 39 and the edge material 41, wherein the edge material 41 faces the hot side 35 and the core material 39 faces the wall side 33.
  • both the geometry of the edge region 37 and the Core area 31 as well as the local heat conduction properties in the edge area 37 by setting a corresponding Porosity of the edge material 41 in the edge region 37 modified and adapted.
  • FIGS. 6 and 7 show different geometries of the Heat shield stone 26 in a plan view of the hot side 35.
  • the geometry of the Core portion 31 is substantially cylindrical and extends from the hot side 35 to the cold side 33.
  • the outer boundary edge of the heat shield element 26 is shown in FIG square geometry and in Figure 7 of hexagonal geometry.
  • the edge region 37 results essentially as Complementary volume to the cylindrical core portion 31.
  • the edge material 41 has a porosity on, so that in the edge region 37 a against the Core area 31 significantly reduced thermal conductivity achieved is.
  • the core material 39 and the edge material 41 are of identical base material or substantially the same Base material built so that the transition from the core area 31 to the edge region 37 in the form of a cohesive, is achieved largely homogeneous composite material, the Although chemically identical or similar, but due to the physical Effect of the specifically set porosity of the Edge material 41, the desired reduction in thermal conductivity caused from the core portion 31 to the edge portion 37.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03019093A 2003-08-22 2003-08-22 Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes Withdrawn EP1508761A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP03019093A EP1508761A1 (fr) 2003-08-22 2003-08-22 Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes
EP04763502A EP1660833A2 (fr) 2003-08-22 2004-07-26 Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes
US10/569,349 US7793503B2 (en) 2003-08-22 2004-07-26 Heat shield block for lining a combustion chamber wall, combustion chamber and gas turbine
PCT/EP2004/008357 WO2005022061A2 (fr) 2003-08-22 2004-07-26 Pierre de bouclier thermique pour habiller une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03019093A EP1508761A1 (fr) 2003-08-22 2003-08-22 Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes

Publications (1)

Publication Number Publication Date
EP1508761A1 true EP1508761A1 (fr) 2005-02-23

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EP03019093A Withdrawn EP1508761A1 (fr) 2003-08-22 2003-08-22 Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes
EP04763502A Withdrawn EP1660833A2 (fr) 2003-08-22 2004-07-26 Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes

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EP04763502A Withdrawn EP1660833A2 (fr) 2003-08-22 2004-07-26 Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes

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US (1) US7793503B2 (fr)
EP (2) EP1508761A1 (fr)
WO (1) WO2005022061A2 (fr)

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US8997495B2 (en) 2011-06-24 2015-04-07 United Technologies Corporation Strain tolerant combustor panel for gas turbine engine
US9115600B2 (en) 2011-08-30 2015-08-25 Siemens Energy, Inc. Insulated wall section
WO2014187659A1 (fr) * 2013-05-21 2014-11-27 Siemens Aktiengesellschaft Carreau en faïence pour bouclier thermique de chambre de combustion

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DE1904373A1 (de) * 1968-01-29 1969-09-25 Deketelaere Eugene Camille Feuerfeste oder nicht-feuerfeste Produkte sowie Verfahren zu ihrer Herstellung
EP1126221A1 (fr) * 2000-02-17 2001-08-22 Siemens Aktiengesellschaft Tuile réfractaire rembourrée pour révêtement d'une chambre de combustion de turbies à gaz
WO2002025197A1 (fr) * 2000-09-18 2002-03-28 Siemens Aktiengesellschaft Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1741531A1 (fr) 2005-07-07 2007-01-10 Siemens Aktiengesellschaft Moule pour la fabrication d'un écran thérmique en céramique
US7306194B2 (en) 2005-07-07 2007-12-11 Siemens Aktiengesellschaft Mold for producing a ceramic heat shield element

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US7793503B2 (en) 2010-09-14
US20070000252A1 (en) 2007-01-04
WO2005022061A2 (fr) 2005-03-10
WO2005022061A3 (fr) 2005-06-23
EP1660833A2 (fr) 2006-05-31

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