EP1064510A1 - Wall segment for a combustion chamber and combustion chamber - Google Patents

Wall segment for a combustion chamber and combustion chamber

Info

Publication number
EP1064510A1
EP1064510A1 EP99916770A EP99916770A EP1064510A1 EP 1064510 A1 EP1064510 A1 EP 1064510A1 EP 99916770 A EP99916770 A EP 99916770A EP 99916770 A EP99916770 A EP 99916770A EP 1064510 A1 EP1064510 A1 EP 1064510A1
Authority
EP
European Patent Office
Prior art keywords
support structure
heat
heat protection
protection element
separating layer
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP99916770A
Other languages
German (de)
French (fr)
Other versions
EP1064510B1 (en
Inventor
Bernard Becker
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
Publication of EP1064510A1 publication Critical patent/EP1064510A1/en
Application granted granted Critical
Publication of EP1064510B1 publication Critical patent/EP1064510B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F27D1/004—Linings or walls comprising means for securing bricks
    • 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
    • F23R3/002—Wall structures
    • 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
    • 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
    • F27D1/045—Bricks for lining cylindrical bodies, e.g. skids, tubes
    • F27D2001/047—Lining of cylindrical vessels

Definitions

  • the invention relates to a wall segment for a combustion chamber to which a hot fluid can be applied, in particular for a combustion chamber of a gas turbine.
  • the invention further relates to a combustion chamber.
  • a thermally highly loaded combustion chamber e.g. a furnace, a hot gas duct or a combustion chamber of a gas turbine, in which a hot fluid is generated and / or guided, is provided with a lining to protect it from excessive thermal stress.
  • the lining is made of heat-resistant material and protects a wall of the combustion chamber from direct contact with the hot fluid and the associated strong thermal stress.
  • US Pat. No. 4,840,131 relates to an improved fastening of ceramic lining elements to a wall of an oven.
  • a rail system which is fastened to the wall and has a plurality of ceramic rail elements, is provided therein, by means of which the lining elements are held.
  • Additional ceramic layers can be provided between a lining element and the wall of the furnace, including a layer of loose, partially compressed ceramic fibers, which layer has at least the same thickness as the ceramic lining elements or a greater thickness.
  • the lining elements here have a rectangular shape with a planar surface and consist of a heat-insulating, refractory ceramic fiber material.
  • US Pat. No. 4,835,831 also relates to the application of a refractory lining to a wall of an oven, in particular a vertical wall.
  • a glass, ceramic or mineral fiber made of glass fiber is placed on the metal wall of the furnace. layer applied. This layer is fixed by metalli ⁇ specific brackets or by adhesive to the wall.
  • a wire mesh network with honeycomb-shaped meshes is applied to this layer. The mesh network also serves to secure the layer of ceramic fibers against falling.
  • a continuous closed surface made of refractory material is applied to the layer fastened in this way by means of a suitable spray process. The method described largely avoids that refractory particles striking during spraying are thrown back, as would be the case if the refractory particles were sprayed directly onto the metallic wall.
  • EP 0 724 116 A2 describes a lining for walls of highly stressed combustion chambers.
  • the lining consists of wall elements made of high-temperature-resistant structural ceramics, such as silicon carbide (SiC) or silicon nitride (Si 3 N 4 ), which are mechanically attached to a metal support structure (wall) of the combustion chamber by means of a fastening bolt.
  • a thick insulation layer is provided between the wall element and the wall of the combustion chamber, so that the wall element is spaced from the wall of the combustion chamber.
  • the insulation layer which is three times as thick as the wall element, consists of ceramic fiber material that is prefabricated in blocks. The dimensions and the external shape of the heat protection segments can be adapted to the geometry of the room to be lined.
  • the lining consists of heat protection segments that are mechanically held on a metallic wall of the combustion chamber.
  • the heat protection segments touch the metallic wall directly.
  • the space formed by the wall of the combustion chamber and the heat protection segment is acted upon by cooling air, the so-called sealing air.
  • the sealing air prevents the penetration of hot action fluid up to the wall and cools the wall and the heat protection segment at the same time.
  • the object of the invention is to provide a wall segment for a combustion chamber to which a hot fluid can be applied, in particular a combustion chamber of a gas turbine. Another task is to provide a heat-resistant combustion chamber.
  • a wall segment for a combustion chamber which can be acted upon by a hot fluid, with a metallic support structure and one on the metallic one
  • Heat protection element fastened to the support structure the metallic support structure being provided at least in regions with a thin, heat-resistant separating layer, the separating layer being attached between the metallic supporting structure and the heat protection element.
  • the object is achieved by a wall segment in which, according to the invention, a metallic, heat-resistant separating layer is attached, at least in regions, between the support structure and the heat protection element.
  • the metallic separating layer can be thin.
  • the invention is based on the consideration that the heat protection segment and the wall of a combustion chamber mainly consist of relatively inelastic materials such as structural ceramics and metal.
  • a disadvantage of such a lining of a combustion chamber is that the heat protection elements directly touch the wall of the combustion chamber.
  • the support of the heat protection element on the wall may not always be flat for manufacturing reasons and due to different thermal expansion of the wall and heat protection element. As a result, high local forces can be generated at the contact points.
  • the heat protection element and the Wall have different thermal expansion, it may be during a change of the operating state of the combustion chamber, for example during a load change in a Gasturbinenan ⁇ location, due to the high force input at the contact points, under unfavorable circumstances, damage to the heat shield segments and / or the wall join. This can result in gaps between the heat protection element and the wall between the contact points of the heat protection element and the wall where there is no contact. These gaps form hot fluid access channels. In this case, in order to prevent the hot fluid from penetrating, an increased amount of sealing air would be required between the wall and the heat protection element.
  • the configuration of a wall segment according to the invention has the advantage that a deformable separating layer inserted between the metallic support structure and the heat protection element can absorb and compensate for possible relative movements of the heat protection element and the support structure.
  • Such relative movements can be caused, for example, in the combustion chamber of a gas turbine, in particular an annular combustion chamber, by different thermal expansion behavior of the materials used or by pulsations in the combustion chamber, which can occur during irregular combustion to generate the hot action fluid or through resonance effects.
  • the separating layer causes the relatively inelastic heat protection element to lie flat on the separating layer and the metallic supporting structure, since the heat protection element partially penetrates into the separating layer.
  • the separating layer can also compensate for production-related unevenness on the support structure and / or the heat protection element, which can locally lead to an unfavorable selective force input.
  • the heat-resistant separating layer inserted between the heat protection element and the metallic support structure is advantageously elastically and / or plastically deformable by the heat protection element.
  • the heat protection element can do so partially penetrate the heat-resistant separating layer and deform it and compensate for unevenness in the contact surfaces of the heat protection element and / or the support structure caused by production and / or by the operation of the system.
  • the force can be applied to the largely inelastic heat protection element as a whole and the risk of damage to the heat protection element and / or the metallic support structure is lower than in the case of force input via the direct, at least partially selective, contact of the heat protection element and support structure.
  • the partial deformation of the separation layer by the heat protection element also leads to a reduction in the gap openings between the heat protection element and the separation layer, which reduces the flow of heat through the hot fluid.
  • sealing air can be applied to a cavity formed by the heat protection element and the metallic support structure. The sealing air requirement is reduced by reducing the stomata and reducing the cavity volume through the separating layer.
  • the separating layer preferably has a thickness which is less than the height of the heat protection element.
  • the height of the heat protection element is understood here to mean the expansion of the heat protection element in the direction perpendicular to the surface of the metallic support structure.
  • the height can correspond directly to the layer thickness of the heat protection element. In the case of a curved or curved or hat-shaped heat protection element, on the other hand, the height is greater than the wall thickness of the heat protection element.
  • the separating layer can have a layer thickness of up to a few millimeters.
  • the layer thickness is preferably less than one millimeter, in particular up to a few tenths of a millimeter.
  • the heat-resistant separating layer preferably comprises a metal grid with honeycomb-shaped cells which can be deformed by the heat protection element.
  • the advantage of the honeycomb cells of the metal grid are filled with a deformable full material.
  • the honeycomb-shaped cells can be made from thin metal sheets that are only a few tenths of a millimeter thick, for example from a nickel-based alloy.
  • the full material is preferably in powder form and has a metal and / or a ceramic.
  • the ceramic powders can be heated and transported in a plasma jet (atmospheric plasma spraying). Depending on the type of powder and spraying conditions, a layer produced by the powder can be made with more or fewer pores.
  • the honeycomb cells are preferably filled with a porous and thus easily deformable and well insulating layer.
  • a metallic full material preferably has a heat-resistant alloy, as is also used, for example, in the coating of gas turbine blades.
  • a metallic full material has, in particular, a base alloy of the type MCrAlY, where M can stand for nickel, cobalt or iron, Cr for chromium, Al for aluminum and Y for Yt ⁇ um or another reactive element of the rare earths.
  • the sealing air requirement is further reduced.
  • the action fluid can also be cooled appropriately when the sealing air enters the combustion chamber from the cooler sealing air, which can lead to a reduction in the overall efficiency of a gas turbine system operated with the hot action fluid.
  • the reduced sealing air requirement also leads to a lower overall efficiency drop than would be the case with a gas turbine system with heat protection elements without a separating layer. 7
  • the heat-resistant separating layer can advantageously also comprise a felt made of thin metal wires.
  • a metal felt can also be laid on contours with very small radii of curvature and is therefore particularly suitable as a separating layer for an irregularly shaped support structure in a combustion chamber, e.g. a metallic support structure for receiving heat protection elements in the combustion chamber of a gas turbine.
  • the thickness of the metal felt is chosen so that even larger gap openings between two contact surfaces of a heat protection element and the
  • the heat-resistant separating layer is preferably applied as a thin coating on the metallic support structure.
  • the heat-resistant separating layer installed between the support structure and the heat protection element is designed to be scale-resistant at a temperature of over 500 ° C., in particular up to approx. 800 ° C.
  • the heat protection element is advantageously mechanically connected to the metallic support structure of the combustion chamber. With the help of a mechanical connection, the contact pressure which the mechanical holder exerts on the heat protection element in the direction of the supporting structure and thus the depth of penetration of the heat protection element and the deformation of the heat-resistant separating layer can be adjusted. The remaining stomata and the resulting barrier air requirements can be adapted to the operating conditions and the amount of sealing air available at the respective location.
  • the heat protection element is advantageously held on the support structure by a bolt.
  • the pin engages approximately in the middle of the heat protection element in order to introduce the contact pressure as centrally as possible into the heat protection element.
  • the heat-resistant separating layer comprises in the region in which the bolt is fastened the associated thermal protection element to the metalli ⁇ 's support structure, a recess. Further recesses and openings in the separating layer, in particular in the case of a gas turbine, are likewise provided where the support structure has channels for supplying sealing air into the cavity formed by the heat protection element and the support structure. In this way sealing air can flow into the cavity and the backflow of the heat protection elements and / or the separating layer can be prevented by hot action fluid.
  • the heat protection element can preferably also be mechanically held on the metallic support structure with the aid of a tongue and groove connection.
  • the object directed to a combustion chamber is achieved according to the invention by a combustion chamber forming a combustion chamber, in particular a combustion chamber of a gas turbine, which is formed from the wall segments described above.
  • heat protection elements are attached to a metal support structure of the wall segment.
  • the heat protection elements have, for example, the shape of flat or curved polygons with straight or curved edges or of flat, regular polygons. They completely cover the metallic support structure that forms the outer wall of the combustion chamber, except for expansion gaps provided between the heat protection elements. Hot fluid can only penetrate into the expansion gaps up to a heat-resistant separating layer of the wall segment and the heat protection elements not currents. As a result, mechanical holders of the heat protection elements and the metallic support structure are largely protected from damage by hot fluid.
  • FIG. 1 wall segment with a separating layer made of a metal grid with filled, honeycomb-shaped cells on a curved supporting structure,
  • FIG. 2 enlarged section from FIG. 1,
  • FIG. 3 wall segment with a separating layer made of a metal felt on a supporting structure provided with m t webs,
  • Figure 4 wall segment with a thin coating applied to a support structure as a separating layer.
  • FIG. 1 shows a wall segment 1 of a combustion chamber of a gas tower that forms a combustion chamber 2 and is not shown in detail.
  • the wall segment 1 comprises a metallic one
  • the heat-resistant separating layer 7 consists of a metal grid with honeycomb-shaped cells (not shown in more detail).
  • the metal strips of the metal grid forming the honeycomb cells have a height which corresponds to the thickness of the separating layer 7.
  • the honeycomb cells of the metal grid are filled with a deformable full material.
  • a ceramic heat protection element 9 is attached on the combustion chamber side of the separating layer 7, a ceramic heat protection element 9 is attached.
  • the ceramic heat protection element 9 is attached to the metal 10 support structure 3 held.
  • the bolt 11 is guided in a bore 10 of the ceramic heat protection element 9, which runs essentially parallel to a normal of a hot gas side 21 of the heat protection element 9, through the region of the center of the heat protection element 9.
  • a contact pressure F generated by the bolt 11 is introduced essentially centrally into the heat protection element 9.
  • the end of the bolt 11 projects through a bore 12 in the support structure 3. This end of the bolt 11 is closed by a nut 13 to which a spring 15 is assigned.
  • the contact pressure F with which the heat protection element 9 is acted on by the bolt 11 can be set by nut 13.
  • the embossing depth of the heat protection element 9 m, the separating layer 7 and thus its deformation can also be adjusted at the same time.
  • FIG. 2 shows how the heat protection element 9 deforms the separating layer 7 through the contact pressure F and partially penetrates it.
  • channels 17 are provided, through which a cavity 19 formed by the heat protection element 9 and the support structure 3 with a separating layer 7 can be acted upon with sealing air S.
  • the separating layer 7 is provided at the points of the support structure 3 where channels 17 are provided with corresponding openings, not shown, through which the sealing air S m can enter the cavity 19.
  • the separating layer 7 has an opening, not shown, in which the bolt 11 is guided.
  • the hot action fluid A When the gas turbine is in operation, the hot action fluid A is generated in the combustion chamber 2.
  • the action fluid A is formed by the wall segment 1 on the hot gas side 21 facing the combustion chamber, which is formed by the heat protection elements 9 11 is led.
  • the heat protection elements 9 prevent the di ⁇ rect contact of the hot working fluid A with the metallic supporting structure 3.
  • Between adjacent heat shield elements 9 of a wall segment 3 22 are provided interface gaps to offset by Lange changes of the heat protection elements 9 due to thermal expansion. Hot action fluid A can penetrate these expansion gaps 22 to the separating layer 7.
  • the deformable full material of the heat-resistant separating layer 7 prevents the direct contact of action fluid A with the metallic support structure 3, seals the cavity 19 against the penetration of hot action fluid A, and thus prevents the heat protection elements 9 from flowing through the core the heat protection elements 9 slightly arched and thus additionally seals the cavity 19 against penetrating action fluid A.
  • the cavity 19 is acted upon by sealing air S through the channels 17.
  • the sealing air S exits the expansion gaps 22 at the points that are not completely sealed off from the hot action fluid A by the separating layer 7, as shown schematically in FIG. Due to the pressure drop generated by the sealing air S from the cavity 19 hm to the combustion chamber, the penetration of action fluid A m prevents the cavity 19.
  • the different thermal expansion of the heat protection element 9 and the metallic support structure 3 can lead to relative movements between the heat protection element 9 and the support structure 3 when the gas turbine changes load.
  • relative movements can also occur due to pulsations in the combustion chamber, caused by irregular combustion or resonances.
  • Such relative movements occurring during operation can also be compensated for by the partially elastically deformable separating layer 7.
  • Em increased force input into the heat protection element 9 on the contact surfaces, for example caused by a sudden increase in pressure, can be caused by the 12
  • FIG. 3 shows a further embodiment of a wall segment 1 for a combustion chamber of a gas turbine, not shown, forming a combustion chamber 2.
  • the wall segment 1 comprises a metallic support structure 23, a heat-resistant separating layer 25 and a metallic heat protection element 27.
  • the metallic support structure 3 has webs 29 which form a respective contact surface for the heat protection element 27.
  • the webs 29 are arranged such that the associated heat protection element 27 rests on the webs 29 in the region of the edge of its surface on the supporting structure side.
  • the heat protection element 27 thus closes the depression formed by the webs 29 and parts of the support structure 23 in a cover-like manner. At least that channel 31 for supplying sealing air S is provided between two webs 29.
  • the metallic heat protection element 27 is spring-mounted on the metallic support structure 23 by means of a bolt 29 (analogous to the bolt described in FIG. 1).
  • the separating layer 25 is embodied as a felt made of thin, heat-resistant metal wires (not shown in more detail), which lines the inside of the support structure 23 facing the combustion chamber 2.
  • the separating layer 25 has openings in the area of a through-opening 26 of the bolt 29 through the support structure 23 and in the area of the mouth 32 of the channel 31.
  • the bolt 29 is guided in the passage opening 26, while sealing air S can flow through the other opening from the channel 31 m through the cavity 33 formed by the heat protection element 27 and the support structure 23.
  • the heat protection element 27 deforms the separating layer 25.
  • Hot action fluid A cannot penetrate as far as the metallic support structure 23 or the heat protection elements 27 can flow.
  • FIG. 4 shows a further embodiment of a wall segment 1.
  • the wall segment 1 comprises a metallic support structure 41 with a heat protection element 47.
  • the heat protection element 47 is resiliently attached to the inside 43 of the support structure 41 by means of a bolt 49, analogous to the bolt described in FIG this tied up.
  • a heat-resistant separating layer 45 is applied to the support structure 41.
  • the heat-resistant separating layer is designed as a thin, heat-resistant coating 45 on the metallic support structure 41.
  • the thin, deformable coating 45 fills the entire space between the heat protection element 47 and the support structure 41, so that unevenness in the support structure 41 and / or the heat protection element 47 caused during production or during operation of the system is compensated for.
  • the heat protection element 47 cannot be flowed through by the hot action fluid A.
  • the action fluid A can penetrate through the expansion gaps 22 formed by adjacent heat protection elements 47 to the heat-resistant coating 45.
  • the coating 45 prevents direct contact of the action fluid A with the metallic support structure 41. Relative movements of the heat protection element 47 and the support structure 41 can be compensated for by the elastic and / or plastic deformation of the coating 45. Damage to the heat protection element and / or the support structure 41 is thus avoided.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Furnace Housings, Linings, Walls, And Ceilings (AREA)

Abstract

The invention relates to a wall segment (1) for a combustion chamber (2) which can be impinged upon by a hot fluid (A). The wall segment (1) has a metal support structure (3) and a heat protection element (9) secured thereon. The metal support structure (3) is provided, at least partially, with a thin and/or metal, heat resistant separating layer (7). The separating layer (7) is arranged between the metal support structure (3) and the heat protection element (9).

Description

Beschreibungdescription
Wandsegment für einen Brennraum sowie BrennraumWall segment for a combustion chamber and combustion chamber
Die Erfindung betrifft ein Wandsegment für einen mit einem heißen Fluid beaufschlagbaren Brennraum, insbesondere für eine Brennkammer einer Gasturbine. Die Erfindung betrifft weiterhin einen Brennraum.The invention relates to a wall segment for a combustion chamber to which a hot fluid can be applied, in particular for a combustion chamber of a gas turbine. The invention further relates to a combustion chamber.
Ein thermisch hochbelasteter Brennraum, wie z.B. ein Brennofen, ein Heißgaskanal oder eine Brennkammer einer Gasturbine, in dem ein heißes Fluid erzeugt und/oder geführt wird, ist zum Schutz vor zu hoher thermischer Beanspruchung mit einer Auskleidung versehen. Die Auskleidung besteht aus hitze- resistentem Material und schützt eine Wandung des Brennraumes vor dem direkten Kontakt mit dem heißen Fluid und der damit verbundenen starken thermischen Beanspruchung.A thermally highly loaded combustion chamber, e.g. a furnace, a hot gas duct or a combustion chamber of a gas turbine, in which a hot fluid is generated and / or guided, is provided with a lining to protect it from excessive thermal stress. The lining is made of heat-resistant material and protects a wall of the combustion chamber from direct contact with the hot fluid and the associated strong thermal stress.
Die US-PS 4,840,131 betrifft eine verbesserte Befestigung von keramischen Auskleidungselementen an einer Wand eines Ofens. Hierin ist ein Schienensystem, welches an der Wand befestigt ist und eine Mehrzahl von keramischen Schienenelementen aufweist, vorgesehen, durch die die Auskleidungselemente gehaltert werden. Zwischen einem Auskleidungselement und der Wand des Ofens können weitere keramische Schichten vorgesehen sein, unter anderem eine Schicht aus losen, teilweise komprimierten Keramikfasern, welche Schicht zumindest dieselbe Dicke wie die keramischen Auskleidungselemente oder eine größere Dicke aufweist. Die Auskleidungselemente weisen hierbei eine rechteckige Form mit planarer Oberfläche auf und bestehen aus einem wärmeisolierenden feuerfesten keramischen Fasermaterial .US Pat. No. 4,840,131 relates to an improved fastening of ceramic lining elements to a wall of an oven. A rail system, which is fastened to the wall and has a plurality of ceramic rail elements, is provided therein, by means of which the lining elements are held. Additional ceramic layers can be provided between a lining element and the wall of the furnace, including a layer of loose, partially compressed ceramic fibers, which layer has at least the same thickness as the ceramic lining elements or a greater thickness. The lining elements here have a rectangular shape with a planar surface and consist of a heat-insulating, refractory ceramic fiber material.
Die US-PS 4,835,831 betrifft ebenfalls das Aufbringen einer feuerfesten Aufkleidung auf einer Wand eines Ofens, insbesondere einer vertikalen Wand. Auf die metallische Wand des Ofens wird eine aus Glas-, Keramik- oder Mineralfasern beste- hende Schicht aufgebracht. Diese Schicht wird durch metalli¬ sche Klammern oder durch Kleber an der Wand befestigt. Auf dieser Schicht wird ein Drahtmaschennetz mit wabenförmigen Maschen aufgebracht. Das Maschennetz dient ebenfalls der Si- cherung der Schicht aus Keramikfasern gegen ein Herabfallen. Auf die so befestigte Schicht wird mittels eines geeigneten Sprühverfahrens eine kontinuierliche geschlossene Oberfläche aus feuerfestem Material aufgebracht. Mit dem beschriebenen Verfahren wird weitgehend vermieden, daß während des Aufsprü- hens auftreffende feuerfeste Partikel zurückgeworfen werden, wie dies bei einem direkten Aufsprühen der feuerfesten Partikeln auf die metallische Wand der Fall wäre.US Pat. No. 4,835,831 also relates to the application of a refractory lining to a wall of an oven, in particular a vertical wall. A glass, ceramic or mineral fiber made of glass fiber is placed on the metal wall of the furnace. layer applied. This layer is fixed by metalli ¬ specific brackets or by adhesive to the wall. A wire mesh network with honeycomb-shaped meshes is applied to this layer. The mesh network also serves to secure the layer of ceramic fibers against falling. A continuous closed surface made of refractory material is applied to the layer fastened in this way by means of a suitable spray process. The method described largely avoids that refractory particles striking during spraying are thrown back, as would be the case if the refractory particles were sprayed directly onto the metallic wall.
In der EP 0 724 116 A2 ist eine Auskleidung für Wandungen von hoch beanspruchten Brennräume beschrieben. Die Auskleidung besteht aus Wandelementen aus hochtemperaturbeständiger Strukturkeramik, wie z.B. Siliciumcarbid (SiC) oder Silicium- nitrid (Si3N4) , die mechanisch mittels eines Befestigungsbolzens an einer metallischen Tragstruktur (Wandung) der Brenn- kammer befestigt sind. Zwischen dem Wandelement und der Wandung des Brennraumes ist eine dicke Isolationsschicht vorgesehen, so daß das Wandelement von der Wandung der Brennkammer beabstandet ist. Die im Verhältnis zum Wandelement drei mal so dicke Isolationsschicht besteht aus keramischem Fasermate- rial, das in Blöcken vorgefertigt ist. Die Abmessungen und die äußere Form der Hitzeschutzsegmente ist an die Geometrie des auszukleidenden Raumes anpaßbar.EP 0 724 116 A2 describes a lining for walls of highly stressed combustion chambers. The lining consists of wall elements made of high-temperature-resistant structural ceramics, such as silicon carbide (SiC) or silicon nitride (Si 3 N 4 ), which are mechanically attached to a metal support structure (wall) of the combustion chamber by means of a fastening bolt. A thick insulation layer is provided between the wall element and the wall of the combustion chamber, so that the wall element is spaced from the wall of the combustion chamber. The insulation layer, which is three times as thick as the wall element, consists of ceramic fiber material that is prefabricated in blocks. The dimensions and the external shape of the heat protection segments can be adapted to the geometry of the room to be lined.
Eine andere Art der Auskleidung eines thermisch hoch bean- spruchten Brennraumes ist in der EP 0 419 487 Bl angegeben. Die Auskleidung besteht aus Hitzeschutzsegmenten, die mechanisch an einer metallischen Wandung des Brennraumes gehaltert sind. Die Hitzeschutzsegmente berühren die metallische Wandung direkt. Um eine zu starke Erwärmung der Wandung zu ver- meiden, z.B. durch direkten Wärmeübergang vom Hitzeschutzsegment oder durch Eindringen von heißem Aktionsfluid in die von aneinandergrenzenden Hitzeschutzsegmenten gebildeten Spalte, wird der von der Wandung des Brennraumes und dem Hitzeschutzsegment gebildete Raum mit Kühlluft, der sogenannten Sperrluft, beaufschlagt. Die Sperrluft verhindert das Vordringen von heißem Aktionsfluid bis zur Wandung und kühlt gleichzei- tig Wandung und Hitzeschutzsegment.Another type of lining for a thermally highly stressed combustion chamber is specified in EP 0 419 487 B1. The lining consists of heat protection segments that are mechanically held on a metallic wall of the combustion chamber. The heat protection segments touch the metallic wall directly. In order to avoid excessive heating of the wall, for example by direct heat transfer from the heat protection segment or by penetration of hot action fluid into the gaps formed by adjoining heat protection segments, the space formed by the wall of the combustion chamber and the heat protection segment is acted upon by cooling air, the so-called sealing air. The sealing air prevents the penetration of hot action fluid up to the wall and cools the wall and the heat protection segment at the same time.
Aufgabe der Erfindung ist es ein Wandsegment für einen mit einem heißen Fluid beaufschlagbaren Brennraum, insbesondere eine Brennkammer einer Gasturbine, anzugeben. Eine weitere Aufgabe ist es einen hitzebeständigen Brennraum anzugeben.The object of the invention is to provide a wall segment for a combustion chamber to which a hot fluid can be applied, in particular a combustion chamber of a gas turbine. Another task is to provide a heat-resistant combustion chamber.
Die auf ein Wandsegment gerichtete Aufgabe wird erfindungsgemäß gelöst durch ein Wandsegment für einen Brennraum, welcher mit einem heißen Fluid beaufschlagbar ist, mit einer me- tallische Tragstruktur und einem auf der metallischenThe object directed to a wall segment is achieved according to the invention by a wall segment for a combustion chamber which can be acted upon by a hot fluid, with a metallic support structure and one on the metallic one
Tragstruktur befestigten Hitzeschutzelement, wobei die metallische Tragstruktur zumindest bereichsweise mit einer dünnen, hitzebeständigen Trennschicht versehen ist, wobei die Trennschicht zwischen der metallischen Tragstruktur und dem Hitze- schutzelement angebracht ist. Alternativ oder zusätzlich wird die Aufgabe gelöst durch ein Wandsegment bei dem erfindungsgemäß zwischen der Tragstruktur und dem Hitzeschutzelement, zumindest bereichsweise, eine metallische, hitzebeständige Trennschicht angebracht ist. Die metallische Trennschicht kann dünn sein.Heat protection element fastened to the support structure, the metallic support structure being provided at least in regions with a thin, heat-resistant separating layer, the separating layer being attached between the metallic supporting structure and the heat protection element. Alternatively or additionally, the object is achieved by a wall segment in which, according to the invention, a metallic, heat-resistant separating layer is attached, at least in regions, between the support structure and the heat protection element. The metallic separating layer can be thin.
Die Erfindung geht von der Überlegung aus, daß das Hitzeschutzsegment und die Wandung eines Brennraumes vorwiegend aus relativ unelastischen Materialien wie z.B. Strukturkera- mik und Metall bestehen. Ein Nachteil einer so ausgestalteten Auskleidung eines Brennraumes liegt darin, daß die Hitzeschutzelemente die Wandung des Brennraumes direkt berühren. Die Auflage des Hitzeschutzelementes auf der Wandung kann aus fertigungstechnischen Gründen und aufgrund unterschiedlicher Wärmedehnung von Wandung und Hitzeschutzelement nicht immer flächig sein. Dadurch können an den Anlagepunkten lokal hohe Kräfte erzeugt werden. Wenn das Hitzeschutzelement und die Wandung unterschiedliches Wärmedehnverhalten aufweisen, kann es bei einem Wechsel des Betriebszustandes des Brennraumes, beispielsweise bei einem Lastwechsel in einer Gasturbinenan¬ lage, durch den hohen Krafteintrag an den Anlagepunkten unter ungünstigen Umständen zu Beschädigungen der Hitzeschutzsegmente und/oder der Wandung kommen. Hierdurch können Spalte zwischen dem Hitzeschutzelement und der Wandung zwischen den Anlagepunkten von Hitzeschutzelement und Wandung entstehen, wo keine Anlage stattfindet. Diese Spalte bilden Zugangska- näle für heißes Fluid. Um ein Eindringen des heißen Fluids zu verhindern wäre in diesem Fall ein erhöhter Sperrluftbedarf zwischen Wandung und Hitzeschutzelement notwendig.The invention is based on the consideration that the heat protection segment and the wall of a combustion chamber mainly consist of relatively inelastic materials such as structural ceramics and metal. A disadvantage of such a lining of a combustion chamber is that the heat protection elements directly touch the wall of the combustion chamber. The support of the heat protection element on the wall may not always be flat for manufacturing reasons and due to different thermal expansion of the wall and heat protection element. As a result, high local forces can be generated at the contact points. If the heat protection element and the Wall have different thermal expansion, it may be during a change of the operating state of the combustion chamber, for example during a load change in a Gasturbinenan ¬ location, due to the high force input at the contact points, under unfavorable circumstances, damage to the heat shield segments and / or the wall join. This can result in gaps between the heat protection element and the wall between the contact points of the heat protection element and the wall where there is no contact. These gaps form hot fluid access channels. In this case, in order to prevent the hot fluid from penetrating, an increased amount of sealing air would be required between the wall and the heat protection element.
Die erfindungsgemäße Ausgestaltung eines Wandsegmentes hat den Vorteil, daß eine zwischen die metallische Tragstruktur und das Hitzeschutzelement eingefügte, verformbare Trennschicht mögliche Relativbewegungen des Hitzeschutzelementes und der Tragstruktur aufnehmen und ausgleichen kann. Solche Relativbewegungen können beispielsweise in der Brennkammer einer Gasturbine, insbesondere einer Ringbrennkammer, durch unterschiedliches Wärmedehnverhalten der verwendeten Materialien oder durch Pulsationen im Brennraum, die bei einer unregelmäßigen Verbrennung zur Erzeugung des heißen Aktions fluid oder durch Resonanzeffekte entstehen können, hervorgerufen werden. Gleichzeitig bewirkt die Trennschicht, daß das relativ unelastische Hitzeschutzelement insgesamt flächiger auf der Trennschicht und der metallischen Tragstruktur aufliegt, da das Hitzeschutzelement teilweise in die Trennschicht eindringt. Die Trennschicht kann so auch fertigungsbedingte Un- ebenheiten an der Tragstruktur und/oder dem Hitzeschutzelement, die lokal zu einem ungünstigen punktuellen Krafteintrag führen können, ausgleichen.The configuration of a wall segment according to the invention has the advantage that a deformable separating layer inserted between the metallic support structure and the heat protection element can absorb and compensate for possible relative movements of the heat protection element and the support structure. Such relative movements can be caused, for example, in the combustion chamber of a gas turbine, in particular an annular combustion chamber, by different thermal expansion behavior of the materials used or by pulsations in the combustion chamber, which can occur during irregular combustion to generate the hot action fluid or through resonance effects. At the same time, the separating layer causes the relatively inelastic heat protection element to lie flat on the separating layer and the metallic supporting structure, since the heat protection element partially penetrates into the separating layer. The separating layer can also compensate for production-related unevenness on the support structure and / or the heat protection element, which can locally lead to an unfavorable selective force input.
Die zwischen dem Hitzeschutzelement und der metallischen Tragstruktur eingefügte, hitzebeständige Trennschicht ist vorteilhafterweise durch das Hitzeschutzelement elastisch und/oder plastisch verformbar. Das Hitzeschutzelement kann so teilweise m die hitzebestandige Trennschicht eindringen und diese deformieren und fertigungsbedingte und/oder durch den Betrieb der Anlage entstandene Unebenheiten der Auflageflachen des Hitzeschutzelementes und/oder der Tragstruktur aus- gleichen. Dadurch kann der Krafteintrag auf das weitgehend unelastische Hitzeschutzelement insgesamt flächiger erfolgen und die Gefahr von Beschädigungen des Hitzeschutzelementes und/oder der metallischen Tragstruktur ist geringer als bei beim Krafteintrag über den direkten, zumindest teilweise punktuellen, Kontakt von Hitzeschutzelement und Tragstruktur. Die teilweise Deformation der Trennschicht durch das Hitze- schutzelement fuhrt außerdem zu einer Verringerung der Spaltöffnungen zwischen Hitzeschutzelement und Trennschicht, was die Hmterstromung durch das heiße Fluid verringert. Um die Hmterstromung der Hitzeschutzelemente zu vermeiden oder zumindest zu verringern, kann ein vom Hitzeschutzelement und der metallischen Tragstruktur gebildeter Hohlraum mit Sperrluft beaufschlagt werden. Durch die Verringerung der Spaltöffnungen und eine Verkleinerung des Hohlraumvolumens durch die Trennschicht wird der Sperrluftbedarf vermindert.The heat-resistant separating layer inserted between the heat protection element and the metallic support structure is advantageously elastically and / or plastically deformable by the heat protection element. The heat protection element can do so partially penetrate the heat-resistant separating layer and deform it and compensate for unevenness in the contact surfaces of the heat protection element and / or the support structure caused by production and / or by the operation of the system. As a result, the force can be applied to the largely inelastic heat protection element as a whole and the risk of damage to the heat protection element and / or the metallic support structure is lower than in the case of force input via the direct, at least partially selective, contact of the heat protection element and support structure. The partial deformation of the separation layer by the heat protection element also leads to a reduction in the gap openings between the heat protection element and the separation layer, which reduces the flow of heat through the hot fluid. To prevent or at least reduce the flow of heat through the heat protection elements, sealing air can be applied to a cavity formed by the heat protection element and the metallic support structure. The sealing air requirement is reduced by reducing the stomata and reducing the cavity volume through the separating layer.
Vorzugsweise weist die Trennschicht eine Dicke auf, die geringer als die Hohe des Hitzeschutzelements ist. Unter Hohe des Hitzeschutzelements wird hierbei die Ausdehnung des Hit- zeschutzelements m Richtung senkrecht zur Oberflache der metallischen Tragstruktur verstanden. Die Hohe kann hierbei unmittelbar der Schichtdicke des Hitzeschutzelements entsprechen. Bei einem gewölbten oder gebogenen oder hutformigen Hitzeschutzelement ist die Hohe hingegen großer als die Wand- starke des Hitzeschutzelements. Die Trennschicht kann eine Schichtdicke bis zu einigen Millimetern aufweisen. Vorzugsweise betragt die Schichtdicke unter einem Millimeter, insbesondere bis zu einigen zehntel Millimetern.The separating layer preferably has a thickness which is less than the height of the heat protection element. The height of the heat protection element is understood here to mean the expansion of the heat protection element in the direction perpendicular to the surface of the metallic support structure. The height can correspond directly to the layer thickness of the heat protection element. In the case of a curved or curved or hat-shaped heat protection element, on the other hand, the height is greater than the wall thickness of the heat protection element. The separating layer can have a layer thickness of up to a few millimeters. The layer thickness is preferably less than one millimeter, in particular up to a few tenths of a millimeter.
Bevorzugt umfaßt die hitzebestandige Trennschicht em Metall- gitter mit wabenfor igen Zellen, das durch das Hitzeschutzelement verformbar ist. Vorteil afterweise sind die wabenfor- migen Zellen des Metallgitters mit einem deformierbaren Fullmater al gefüllt. Die wabenformigen Zellen können aus dünnen, nur wenige Zehntel Millimeter dicken Blechen, beispielsweise aus einer Nickelbasis-Legierung, hergestellt sein. Das Fullmaterial ist vorzugsweise pulverformig und weist em Metall und/oder eine Keramik auf. Die Keramikpulver können in einem Plasmastrahl erhitzt und transportiert werden (atmosphärisches Plasmaspritzen) . Je nach Pulverart und Spritzbedingung kann eine durch das Pulver hergestellte Schicht mit mehr oder weniger Poren ausgeführt werden. Die wabenformigen Zellen werden bevorzugt mit einer porösen und somit leicht verformbaren und gut isolierenden Schicht ausgefüllt. Em metallisches Fullmaterial weist vorzugsweise eine hitzebestandige Legierung auf, wie sie beispielsweise auch bei der Beschichtung von Gasturbmenschaufeln Verwendung findet. Em metallisches Fullmaterial weist insbesondere eine Basislegierung der Art MCrAlY auf, wobei M für Nickel, Kobalt oder Eisen, Cr für Chrom, AI für Aluminium und Y für Ytπum oder em anderes reaktives Element der seltenen Erden stehen kann. Das deformierbare Fullmaterial verschließt beim Verfor- men und Eindringen des Hitzeschutzelementes m die Trennschicht, die zwischen den Auflageflachen bestehenden Spaltöffnungen, bzw. verkleinert diese, was zur Verringerung des Sperrluftbedarfs fuhrt. Weiterhin verkleinert die Trenn- Schicht das Volumen des vom Hitzeschutzelement und derThe heat-resistant separating layer preferably comprises a metal grid with honeycomb-shaped cells which can be deformed by the heat protection element. The advantage of the honeycomb cells of the metal grid are filled with a deformable full material. The honeycomb-shaped cells can be made from thin metal sheets that are only a few tenths of a millimeter thick, for example from a nickel-based alloy. The full material is preferably in powder form and has a metal and / or a ceramic. The ceramic powders can be heated and transported in a plasma jet (atmospheric plasma spraying). Depending on the type of powder and spraying conditions, a layer produced by the powder can be made with more or fewer pores. The honeycomb cells are preferably filled with a porous and thus easily deformable and well insulating layer. A metallic full material preferably has a heat-resistant alloy, as is also used, for example, in the coating of gas turbine blades. A metallic full material has, in particular, a base alloy of the type MCrAlY, where M can stand for nickel, cobalt or iron, Cr for chromium, Al for aluminum and Y for Ytπum or another reactive element of the rare earths. When the heat protection element m is deformed and penetrated, the deformable full material closes or reduces the separating layer, the gap openings existing between the contact surfaces, which leads to a reduction in the need for sealing air. Furthermore, the separating layer reduces the volume of the heat protection element and the
Tragstruktur gebildeten Hohlraumes, wodurch der Sperrluftbedarf weiter vermindert wird. Bei einer Gasturbine kann das Aktionsfluid außerdem beim Eintritt von Sperrluft m den Brennraum von der kuhleren Sperrluft entsprechend abgekühlt werden, was zu einem Gesamtwirkungsgradabfall einer mit dem heißen Aktionsfluid betriebenen Gasturbinenanlage fuhren kann. Der verminderte Sperrluftbedarf fuhrt m diesem Fall auch zu einem geringeren Gesamtwirkungsgradabfall, als das bei einer Gasturbinenanlage mit Hitzeschutzelementen ohne Trennschicht der Fall wäre. 7Support structure formed cavity, whereby the sealing air requirement is further reduced. In the case of a gas turbine, the action fluid can also be cooled appropriately when the sealing air enters the combustion chamber from the cooler sealing air, which can lead to a reduction in the overall efficiency of a gas turbine system operated with the hot action fluid. In this case, the reduced sealing air requirement also leads to a lower overall efficiency drop than would be the case with a gas turbine system with heat protection elements without a separating layer. 7
Die hitzebeständige Trennschicht kann vorteilhafterweise auch einen Filz aus dünnen Metalldrähten umfassen. Ein solcher Metallfilz kann auch auf Konturen mit sehr kleinen Krümmungsradien verlegt werden und eignet sich daher besonders als Trennschicht für einen unregelmäßig ausgeformte Tragstruktur in einem Brennraum, wie z.B. einer metallischen Tragstruktur zur Aufnahme von sperrluftbeaufschlagten Hitzeschutzelementen in der Brennkammer einer Gasturbine. Die Dicke des Metallfilzes ist so gewählt, daß auch größere Spaltöffnungen zwischen zwei Auflageflächen eines Hitzeschutzelementes und derThe heat-resistant separating layer can advantageously also comprise a felt made of thin metal wires. Such a metal felt can also be laid on contours with very small radii of curvature and is therefore particularly suitable as a separating layer for an irregularly shaped support structure in a combustion chamber, e.g. a metallic support structure for receiving heat protection elements in the combustion chamber of a gas turbine. The thickness of the metal felt is chosen so that even larger gap openings between two contact surfaces of a heat protection element and the
Tragstruktur vom Metallfilz verschlossen oder zumindest stark verkleinert werden. Dadurch wird der Einsatz eines solchermaßen ausgestalteten Wandsegmentes auch in Anlagen möglich, bei denen die zur Verfügung stehende Sperrluftmenge begrenzt ist.Support structure closed by the metal felt or at least greatly reduced. As a result, the use of a wall segment designed in this way is also possible in systems in which the amount of sealing air available is limited.
Sind die zwischen der metallischen Tragstruktur und den zugehörigen Hitzeschutzelementen entstehenden Spaltöffnungen relativ klein und gleichförmig, so ist die hitzebeständige Trennschicht vorzugsweise als dünne Beschichtung auf der metallischen Tragstruktur aufgebracht.If the gap openings formed between the metallic support structure and the associated heat protection elements are relatively small and uniform, the heat-resistant separating layer is preferably applied as a thin coating on the metallic support structure.
Um den Belastungen durch eindringendes heißes Fluid widerstehen zu können und die metallischen Tragstruktur wirksam zu schützen ist die zwischen der Tragstruktur und dem Hitzeschutzelement installierte hitzebestandige Trennschicht bei einer Temperatur von über 500°C, insbesondere bis ca. 800°C zunderfest ausgebildet.In order to be able to withstand the loads caused by penetrating hot fluid and to effectively protect the metallic support structure, the heat-resistant separating layer installed between the support structure and the heat protection element is designed to be scale-resistant at a temperature of over 500 ° C., in particular up to approx. 800 ° C.
Das Hitzeschutzelement ist vorteilhafterweise mechanisch an die metallische Tragstruktur des Brennraumes angebunden. Mit Hilfe einer mechanischen Verbindung kann die Anpreßkraft, welche die mechanische Halterung auf das Hitzeschutzelement in Richtung Tragstruktur ausübt und damit die Eindringtiefe des Hitzeschutzelementes und die Deformation der hitzebeständigen Trennschicht, eingestellt werden. So können die verbleibenden Spaltöffnungen und der daraus resultierende Sperr- luftbedarf an die Betriebsbedingungen und die zur Verfügung stehende Sperrluftmenge des jeweiligen Einsatzortes angepaßt werden.The heat protection element is advantageously mechanically connected to the metallic support structure of the combustion chamber. With the help of a mechanical connection, the contact pressure which the mechanical holder exerts on the heat protection element in the direction of the supporting structure and thus the depth of penetration of the heat protection element and the deformation of the heat-resistant separating layer can be adjusted. The remaining stomata and the resulting barrier air requirements can be adapted to the operating conditions and the amount of sealing air available at the respective location.
Vorteilhaft ist das Hitzeschutzelement durch einen Bolzen an der Tragstruktur gehaltert. Der Bolzen greift etwa in der Mitte des Hitzeschutzelementes an, um die Anpreßkraft möglichst zentrisch in das Hitzeschutzelement einzuleiten. Die hitzebeständige Trennschicht weist in dem Bereich, in dem der Bolzen des zugehörigen Hitzeschutzelementes an der metalli¬ schen Tragstruktur befestigt wird, eine Ausnehmung auf. Weitere Ausnehmungen und Öffnungen in der Trennschicht, insbesondere bei einer Gasturbine, sind ebenfalls dort vorgesehen, wo die Tragstruktur Kanäle für eine Sperrluftzufuhr in den vom Hitzeschutzelement und der Tragstruktur gebildeten Hohlraum aufweist. So kann Sperrluft in den Hohlraum strömen und die Hinterströmung der Hitzeschutzelemente und/oder der Trennschicht durch heißes Aktionsfluid verhindert werden.The heat protection element is advantageously held on the support structure by a bolt. The pin engages approximately in the middle of the heat protection element in order to introduce the contact pressure as centrally as possible into the heat protection element. The heat-resistant separating layer comprises in the region in which the bolt is fastened the associated thermal protection element to the metalli ¬'s support structure, a recess. Further recesses and openings in the separating layer, in particular in the case of a gas turbine, are likewise provided where the support structure has channels for supplying sealing air into the cavity formed by the heat protection element and the support structure. In this way sealing air can flow into the cavity and the backflow of the heat protection elements and / or the separating layer can be prevented by hot action fluid.
Bevorzugt kann das Hitzeschutzelement auch mit Hilfe einer Feder-Nut-Verbindung mechanisch an der metallischen Tragstruktur gehaltert sein.The heat protection element can preferably also be mechanically held on the metallic support structure with the aid of a tongue and groove connection.
Die auf einen Brennraum gerichtete Aufgabe wird erfindungsge- maß gelöst durch eine einen Brennraum bildende Brennkammer, insbesondere eine Brennkammer einer Gasturbine, die aus oben beschriebenen Wandsegmenten gebildet ist. Um eine, hitzebest ndige Auskleidung des Brennraumes zu erreichen sind Hitzeschutzelemente auf einer metallischen Tragstruktur des Wand- Segmentes angebracht. Die Hitzeschutzelemente haben z.B. die Form ebener oder gekrümmter Vielecke mit geraden oder gebogenen Kanten oder von ebenen, regelmäßigen Vielecken. Sie überdecken die metallische Tragstruktur, die die Außenwandung des Brennraumes bildet, bis auf zwischen den Hitzeschutzelementen vorgesehene Dehnungsspalte vollständig. Heißes Fluid kann in den Dehnungsspalten nur bis zur einer hitzebeständigen Trennschicht des Wandsegmentes vordringen und die Hitzeschutzele- mente nicht hmterstromen. Dadurch werden mechanische Halterungen der Hitzeschutzelemente und die metallische Tragstruktur vor der Beschädigung durch heißes Fluid weitgehend geschützt.The object directed to a combustion chamber is achieved according to the invention by a combustion chamber forming a combustion chamber, in particular a combustion chamber of a gas turbine, which is formed from the wall segments described above. In order to achieve a heat-resistant lining of the combustion chamber, heat protection elements are attached to a metal support structure of the wall segment. The heat protection elements have, for example, the shape of flat or curved polygons with straight or curved edges or of flat, regular polygons. They completely cover the metallic support structure that forms the outer wall of the combustion chamber, except for expansion gaps provided between the heat protection elements. Hot fluid can only penetrate into the expansion gaps up to a heat-resistant separating layer of the wall segment and the heat protection elements not currents. As a result, mechanical holders of the heat protection elements and the metallic support structure are largely protected from damage by hot fluid.
Anhand der m der Zeichnung dargestellten Ausfuhrungsbei- spiele werden das Wandsegment und em Brennraum naher erläu¬ tert. Es zeigen die Figuren m schematischer Darstellung:On the basis of the drawing shown m Ausfuhrungsbei- games are the wall segment and em combustion chamber near erläu ¬ tert. The figures show a schematic representation:
Figur 1 Wandsegment mit einer Trennschicht aus einem Metallgitter mit gefüllten, wabenformigen Zellen auf einer gekrümmten Tragstruktur,FIG. 1 wall segment with a separating layer made of a metal grid with filled, honeycomb-shaped cells on a curved supporting structure,
Figur 2 Vergrößerter Ausschnitt aus Figur 1,FIG. 2 enlarged section from FIG. 1,
Figur 3 Wandsegment mit einer Trennschicht aus einem Me- tallfilz auf einer m t Stegen versehenen Tragstruktur,FIG. 3 wall segment with a separating layer made of a metal felt on a supporting structure provided with m t webs,
Figur 4 Wandsegment mit einer auf einer Tragstruktur aufgebrachten, dünnen Beschichtung als Trennschicht.Figure 4 wall segment with a thin coating applied to a support structure as a separating layer.
In Figur 1 ist em Wandsegment 1 einer einen Brennraum 2 bildenden, nicht naher dargestellten Brennkammer einer Gastur- bme gezeigt. Das Wandsegment 1 umfaßt eine metallischeFIG. 1 shows a wall segment 1 of a combustion chamber of a gas tower that forms a combustion chamber 2 and is not shown in detail. The wall segment 1 comprises a metallic one
Tragstruktur 3, auf deren dem Brennraum 2 zugewandten Innenwandung 5 eine hitzebestandige Trennschicht 7 aufgebracht ist. Die hitzebestandige Trennschicht 7 besteht aus einem nicht naher dargestellten Metallgitter mit wabenformigen Zel- len. Die die wabenformigen Zellen bildenden Metallbander des Metaligitters weisen eine Hohe auf, die der Dicke der Trennschicht 7 entspricht. Die wabenformigen Zellen des Metallgit- ters sind mit einem deformierbaren Fullmaterial ausgefüllt.Support structure 3, on the inner wall 5 facing the combustion chamber 2, a heat-resistant separating layer 7 is applied. The heat-resistant separating layer 7 consists of a metal grid with honeycomb-shaped cells (not shown in more detail). The metal strips of the metal grid forming the honeycomb cells have a height which corresponds to the thickness of the separating layer 7. The honeycomb cells of the metal grid are filled with a deformable full material.
Auf der Brennraumseite der Trennschicht 7, ist e keramisches Hitzeschutzelement 9 angebracht. Das keramische Hitze- schutzelement 9 ist mit Hilfe eines Bolzens 11 an der metal- 10 lischen Tragstruktur 3 gehaltert. Der Bolzen 11 ist m einer Bohrung 10 des keramischen Hitzeschutzele entes 9 gefuhrt, die im wesentlichen parallel zu einer Normalen einer Heiß- gasseite 21 des Hitzeschutzelementes 9, durch den Bereich des Zentrums des Hitzeschutzelementes 9 verlauft. Hierdurch ist eine vom Bolzen 11 erzeugte Anpreßkraft F im wesentlichen zentrisch das Hitzeschutzelement 9 eingeleitet. Em Ende des Bolzens 11 ragt durch eine Bohrung 12 der Tragstruktur 3 hindurch. Dieses Ende des Bolzens 11 wird von einer Mutter 13 abgeschlossen, der eine Feder 15 zugeordnet ist. Über dieOn the combustion chamber side of the separating layer 7, a ceramic heat protection element 9 is attached. The ceramic heat protection element 9 is attached to the metal 10 support structure 3 held. The bolt 11 is guided in a bore 10 of the ceramic heat protection element 9, which runs essentially parallel to a normal of a hot gas side 21 of the heat protection element 9, through the region of the center of the heat protection element 9. As a result, a contact pressure F generated by the bolt 11 is introduced essentially centrally into the heat protection element 9. The end of the bolt 11 projects through a bore 12 in the support structure 3. This end of the bolt 11 is closed by a nut 13 to which a spring 15 is assigned. About the
Mutter 13 kann die Anpreßkraft F mit der das Hitzeschutzele- ment 9 über den Bolzen 11 beaufschlagt wird eingestellt werden. Damit kann gleichzeitig auch die Emdrmgtiefe des Hitzeschutzelementes 9 m die Trennschicht 7 und damit deren De- formation eingestellt werden. Je großer die Anpreßkraft F ist mit der das Hitzeschutzelement 9 auf die hitzebestandige Trennschicht 7 gepreßt wird, desto tiefer dringt das Hitze- schutzelement 9 m die Trennschicht 7 em. In Figur 2 ist gezeigt, wie das Hitzeschutzelement 9 durch die Anpreßkraft F die Trennschicht 7 deformiert und teilweise m diese eindringt .The contact pressure F with which the heat protection element 9 is acted on by the bolt 11 can be set by nut 13. The embossing depth of the heat protection element 9 m, the separating layer 7 and thus its deformation can also be adjusted at the same time. The greater the contact pressure F with which the heat protection element 9 is pressed onto the heat-resistant separation layer 7, the deeper the heat protection element 9 m penetrates the separation layer 7 em. FIG. 2 shows how the heat protection element 9 deforms the separating layer 7 through the contact pressure F and partially penetrates it.
In der metallischen Tragstruktur 3 sind Kanäle 17 vorgesehen, durch die em vom Hitzeschutzelement 9 und der Tragstruktur 3 mit Trennschicht 7 gebildeter Hohlraum 19 mit Sperrluft S beaufschlagt werden kann. Die Trennschicht 7 ist dazu an den Stellen der Tragstruktur 3 wo Kanäle 17 vorgesehen sind mit entsprechenden, nicht dargestellten Offnungen versehen, durch die die Sperrluft S m den Hohlraum 19 eintreten kann. In dem Bereich, m dem der Bolzen 11 an der metallischen Tragstruk- tur 3 gehaltert ist, weist die Trennschicht 7 eine nicht naher gezeigte Öffnung auf, m der der Bolzen 11 gefuhrt ist.In the metallic support structure 3, channels 17 are provided, through which a cavity 19 formed by the heat protection element 9 and the support structure 3 with a separating layer 7 can be acted upon with sealing air S. For this purpose, the separating layer 7 is provided at the points of the support structure 3 where channels 17 are provided with corresponding openings, not shown, through which the sealing air S m can enter the cavity 19. In the area in which the bolt 11 is held on the metallic supporting structure 3, the separating layer 7 has an opening, not shown, in which the bolt 11 is guided.
Bei Betrieb der Gasturbine wird im Brennraum 2 der Brennka - mer heißes Aktionsfluid A erzeugt. Das Aktionsfluid A wird von dem Wandsegment 1 auf der dem Brennraum zugewandten Heiß- gasseite 21, die von den Hitzeschutzelementen 9 gebildet 11 wird, gefuhrt. Die Hitzeschutzelemente 9 verhindern den di¬ rekten Kontakt von dem heißen Aktionsfluid A mit der metallischen Tragstruktur 3. Zwischen benachbarten Hitzeschutzelementen 9 eines Wandsegmentes 3 sind Dehnspalte 22 zum Aus- gleich von Langenanderungen der Hitzeschutzelemente 9 aufgrund von Wärmedehnung vorgesehen. Heißes Aktionsfluid A kann m diese Dehnspalte 22 bis zur Trennschicht 7 vordringen. Das deformierbare Fullmaterial der hitzebestandigen Trennschicht 7 verhindert den direkten Kontakt von Aktionsfluid A mit der metallischen Tragstruktur 3, dichtet den Hohlraum 19 gegen eindringendes heißes Aktionsfluid A und verhindert so eine Hmterstromung der Hitzeschutzelemente 9. Die Trennschicht 7 wird im Bereich des Dehnspaltes 21 durch die Langendehnung der Hitzeschutzelemente 9 leicht aufgewölbt und dichtet den Hohlraum 19 so zusätzlich gegen eindringendes Aktionsfluid A ab. Um die Sperrwirkung der Trennschicht 7 und der Hitze- schutzelemente 9 zu verstarken wird der Hohlraum 19 durch die Kanäle 17 mit Sperrluft S beaufschlagt. Die Sperrluft S tritt den Dehnspalten 22 an den Stellen aus, die nicht vollstan- dig durch die Trennschicht 7 vor dem heißen Aktionsfluid A abgedichtet sind, wie m Figur 2 schematisch gezeigt. Durch das von der Sperrluft S erzeugte Druckgefalle vom Hohlraum 19 hm zum Brennraum wird em Eindringen von Aktionsfluid A m den Hohlraum 19 verhindert.When the gas turbine is in operation, the hot action fluid A is generated in the combustion chamber 2. The action fluid A is formed by the wall segment 1 on the hot gas side 21 facing the combustion chamber, which is formed by the heat protection elements 9 11 is led. The heat protection elements 9 prevent the di ¬ rect contact of the hot working fluid A with the metallic supporting structure 3. Between adjacent heat shield elements 9 of a wall segment 3 22 are provided interface gaps to offset by Lange changes of the heat protection elements 9 due to thermal expansion. Hot action fluid A can penetrate these expansion gaps 22 to the separating layer 7. The deformable full material of the heat-resistant separating layer 7 prevents the direct contact of action fluid A with the metallic support structure 3, seals the cavity 19 against the penetration of hot action fluid A, and thus prevents the heat protection elements 9 from flowing through the core the heat protection elements 9 slightly arched and thus additionally seals the cavity 19 against penetrating action fluid A. In order to reinforce the barrier effect of the separating layer 7 and the heat protection elements 9, the cavity 19 is acted upon by sealing air S through the channels 17. The sealing air S exits the expansion gaps 22 at the points that are not completely sealed off from the hot action fluid A by the separating layer 7, as shown schematically in FIG. Due to the pressure drop generated by the sealing air S from the cavity 19 hm to the combustion chamber, the penetration of action fluid A m prevents the cavity 19.
Die unterschiedlichen Wärmedehnung des Hitzeschutzelementes 9 und der metallischen Tragstruktur 3 können bei Lastwechseln der Gasturbine zu Relativbewegungen zwischen Hitzeschutzele- ment 9 und der Tragstruktur 3 fuhren. Relativbewegungen kon- nen aber auch durch Pulsationen im Brennraum, verursacht durch unregelmäßige Verbrennungen oder Resonanzen, entstehen. Solche wahrend des Betriebes auftretenden Relativbewegungen können von der teilweise elastisch verformbaren Trennschicht 7 ebenfalls ausgeglichen werden. Em erhöhter Krafteintrag in das Hitzeschutzelement 9 an den Auflageflachen, z.B. verursacht durch einem plötzlichen Druckanstieg, kann durch das 12The different thermal expansion of the heat protection element 9 and the metallic support structure 3 can lead to relative movements between the heat protection element 9 and the support structure 3 when the gas turbine changes load. However, relative movements can also occur due to pulsations in the combustion chamber, caused by irregular combustion or resonances. Such relative movements occurring during operation can also be compensated for by the partially elastically deformable separating layer 7. Em increased force input into the heat protection element 9 on the contact surfaces, for example caused by a sudden increase in pressure, can be caused by the 12
Zusammenpressen der Trennschicht 7 und die damit entstehende, vergrößerte Auflageflache vermindert werden.Pressing the separating layer 7 together and the resulting enlarged contact surface can be reduced.
Figur 3 zeigt eine weitere Ausführungsform eines Wandsegmen- tes 1 für eine einen Brennraum 2 bildenden nicht naher dargestellte Brennkammer einer Gasturbine. Das Wandsegment 1 umfaßt eine metallischen Tragstruktur 23, eine hitzebestandige Trennschicht 25 und em metallisches Hitzeschutzelement 27. Die metallische Tragstruktur 3 weist Stege 29 auf, die eine jeweilige Auflageflache für das Hitzeschutzelement 27 bilden. Die Stege 29 sind so angeordnet, daß das zugeordnete Hitze- schutzelement 27 im Bereich des Randes seiner tragstruktur- seitigen Oberflache auf den Stegen 29 aufliegt. Das Hitze- schutzelement 27 verschließt so die von den Stegen 29 und von Teilen der Tragstruktur 23 gebildete Vertiefung deckelartig. Zwischen zwei Stegen 29 ist mindestens j e em Kanal 31 zur Zufuhr von Sperrluft S vorgesehen. Das metallische Hitze- schutzelement 27 ist mittels eines Bolzens 29 (analog zu dem m Figur 1 beschriebenen Bolzen) federnd an der metallischen Tragstruktur 23 gehaltert.FIG. 3 shows a further embodiment of a wall segment 1 for a combustion chamber of a gas turbine, not shown, forming a combustion chamber 2. The wall segment 1 comprises a metallic support structure 23, a heat-resistant separating layer 25 and a metallic heat protection element 27. The metallic support structure 3 has webs 29 which form a respective contact surface for the heat protection element 27. The webs 29 are arranged such that the associated heat protection element 27 rests on the webs 29 in the region of the edge of its surface on the supporting structure side. The heat protection element 27 thus closes the depression formed by the webs 29 and parts of the support structure 23 in a cover-like manner. At least that channel 31 for supplying sealing air S is provided between two webs 29. The metallic heat protection element 27 is spring-mounted on the metallic support structure 23 by means of a bolt 29 (analogous to the bolt described in FIG. 1).
Die Trennschicht 25 ist als em Filz aus dünnen, nicht naher gezeigten, hitzeresistenten Metalldrahten ausgeführt, welcher die dem Brennraum 2 zugewandte Innenseite der Tragstruktur 23 auskleidet. Die Trennschicht 25 weist im Bereich einer Durch- tπttsoffnung 26 des Bolzens 29 durch die Tragstruktur 23 sowie im Bereich der Mundung 32 des Kanals 31 Offnungen auf. In der Durchtrittsoffnung 26 ist der Bolzen 29 gefuhrt wahrend durch die andere Öffnung Sperrluft S aus dem Kanal 31 m den von dem Hitzeschutzelement 27 und der Tragstruktur 23 gebildeten Hohlraum 33 strömen kann. Im Bereich der Stege 29 deformiert das Hitzeschutzelement 27 die Trennschicht 25. Zwischen den Anlageflachen von Hitzeschutzelement 27 und Steg 29 entstehende, nicht naher dargestellte Spaltöffnungen werden von der Trennschicht 25 verschlossen, bzw. ihrer Quer- schnittsflache verringert. Dadurch wird der Austritt von Sperrluft S aus dem Hohlraum 33 in die zwischen zwei Hitze- 13The separating layer 25 is embodied as a felt made of thin, heat-resistant metal wires (not shown in more detail), which lines the inside of the support structure 23 facing the combustion chamber 2. The separating layer 25 has openings in the area of a through-opening 26 of the bolt 29 through the support structure 23 and in the area of the mouth 32 of the channel 31. The bolt 29 is guided in the passage opening 26, while sealing air S can flow through the other opening from the channel 31 m through the cavity 33 formed by the heat protection element 27 and the support structure 23. In the area of the webs 29, the heat protection element 27 deforms the separating layer 25. The gap openings 25, which are not shown in detail between the contact surfaces of the heat protection element 27 and the web 29, are closed by the separating layer 25 or their cross-sectional area is reduced. As a result, the exit of sealing air S from the cavity 33 into the between two heat 13
Schutzelementen 27 entstehenden Dehnspalte 35 verhindert, bzw. verringert. Heißes Aktionsfluid A kann damit nicht bis zur metallischen Tragstruktur 23 vordringen oder die Hitze- schutzelemente 27 hmterstromen.Protective elements 27 resulting expansion gaps 35 prevented or reduced. Hot action fluid A cannot penetrate as far as the metallic support structure 23 or the heat protection elements 27 can flow.
Figur 4 zeigt eine weitere Ausführungsform eines Wandsegmentes 1. Das Wandsegment 1 umfaßt eine metallische Tragstruktur 41 mit einem Hitzeschutzelement 47. Das Hitzeschutzelement 47 ist analog zu dem m Figur 1 beschriebenen Bolzen auf der In- nenseite 43 der Tragstruktur 41 mittels eines Bolzens 49 federnd an dieser angebunden. Zwischen der dem Brennraum 2 zugewandten Seite der Tragstruktur 41 und brennraumabgewandten Seite 51 des Hitzeschutzelementes 47 ist eine hitzebestandige Trennschicht 45 auf die Tragstruktur 41 aufgebracht. Die hit- zebestandige Trennschicht ist als eine dünne, hitzebestandige Beschichtung 45 auf der metallischen Tragstruktur 41 ausgeführt. Die dünne, verformbare Beschichtung 45 füllt den gesamten Raum zwischen Hitzeschutzelement 47 und Tragstruktur 41 aus, so daß fertigungsbedingte oder wahrend des Betriebs der Anlage entstandene Unebenheiten der Tragstruktur 41 und/oder des Hitzeschutzelementes 47 ausgeglichen werden. Außerdem kann das Hitzeschutzelement 47 so nicht vom heißen Aktionsfluid A mterstromt werden kann. Das Aktionsfluid A kann durch d e von benachbarten Hitzeschutzelementen 47 ge- bildeten Dehnspalte 22 bis zur hitzebestandigen Beschichtung 45 vordringen. Die Beschichtung 45 verhindert den direkten Kontakt des Aktionsfluids A mit der metallischen Tragstruktur 41. Relativbewegungen des Hitzeschutzelementes 47 und der Tragstruktur 41 können durch die elastische und/oder plasti- sehe Verformung der Beschichtung 45 ausgeglichen werden. Beschädigungen des Hitzeschutzelementes und/oder der Tragstruktur 41 werden somit vermieden. FIG. 4 shows a further embodiment of a wall segment 1. The wall segment 1 comprises a metallic support structure 41 with a heat protection element 47. The heat protection element 47 is resiliently attached to the inside 43 of the support structure 41 by means of a bolt 49, analogous to the bolt described in FIG this tied up. Between the side of the support structure 41 facing the combustion chamber 2 and the side 51 of the heat protection element 47 facing away from the combustion chamber, a heat-resistant separating layer 45 is applied to the support structure 41. The heat-resistant separating layer is designed as a thin, heat-resistant coating 45 on the metallic support structure 41. The thin, deformable coating 45 fills the entire space between the heat protection element 47 and the support structure 41, so that unevenness in the support structure 41 and / or the heat protection element 47 caused during production or during operation of the system is compensated for. In addition, the heat protection element 47 cannot be flowed through by the hot action fluid A. The action fluid A can penetrate through the expansion gaps 22 formed by adjacent heat protection elements 47 to the heat-resistant coating 45. The coating 45 prevents direct contact of the action fluid A with the metallic support structure 41. Relative movements of the heat protection element 47 and the support structure 41 can be compensated for by the elastic and / or plastic deformation of the coating 45. Damage to the heat protection element and / or the support structure 41 is thus avoided.

Claims

14 Patentansprüche 14 claims
1. Wandsegment (1) für einen Brennraum (2), welcher mit einem heißen Fluid (A) beaufschlagbar ist, mit einer metallischen Tragstruktur (3) und einem auf der metallischen Tragstruktur (3) befestigten Hitzeschutzelement (9) , d a d u r c h g e k e n n z e i c h n e t , daß die metallische Tragstruktur (3) zumindest bereichsweise mit einer dünnen, hitzebestandigen Trennschicht (7) versehen ist, wobei die Trennschicht (7) zwischen der metallischen Tragstruktur (3) und dem Hitzeschutzelement (9) angebracht ist.1. Wall segment (1) for a combustion chamber (2), which can be acted upon with a hot fluid (A), with a metallic support structure (3) and a heat protection element (9) attached to the metallic support structure (3), characterized in that the metallic support structure (3) is provided at least in some areas with a thin, heat-resistant separating layer (7), the separating layer (7) being attached between the metallic supporting structure (3) and the heat protection element (9).
2. Wandsegment (1) für einen Brennraum (2), welcher mit einem heißen Fluid (A) beaufschlagbar ist, mit einer metallischen Tragstruktur (3) und einem auf der metallischen Tragstruktur (3) befestigten Hitzeschutzelement (9), d a d u r c h g e k e n n z e i c h n e t , daß die metallische Tragstruktur (3) zumindest bereichsweise mit einer metallischen, hitzebestandigen Trennschicht (7) versehen ist, wobei die Trennschicht (7) zwischen der metallischen2. Wall segment (1) for a combustion chamber (2) which can be acted upon with a hot fluid (A), with a metallic support structure (3) and a heat protection element (9) attached to the metallic support structure (3), characterized in that the metallic support structure (3) is at least partially provided with a metallic, heat-resistant separating layer (7), the separating layer (7) between the metallic
Tragstruktur (3) und dem Hitzeschutzelement (9) angebracht ist .Support structure (3) and the heat protection element (9) is attached.
3. Wandsegment (1) nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t , daß die hitzebestandige Trennschicht (7) durch das Hitzeschutzelement (9) elastisch und/oder plastisch verformbar ist.3. Wall segment (1) according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t that the heat-resistant separating layer (7) by the heat protection element (9) is elastically and / or plastically deformable.
4. Wandsegment (1) nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , daß die Trennschicht (3) eine Schichtdicke aufweist, die geringer als die Hohe des Hitzeschutzelements ist.4. Wall segment (1) according to one of the preceding claims, d a d u r c h g e k e n n z e i c h n e t that the separating layer (3) has a layer thickness which is less than the height of the heat protection element.
5. Wandsegment (1) nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , daß die Trennschicht (3) eine Schichtdicke von bis zu einigen Millimetern, insbesondere unter 1 mm, aufweist. 155. Wall segment (1) according to one of the preceding claims, characterized in that the separating layer (3) has a layer thickness of up to a few millimeters, in particular less than 1 mm. 15
6. Wandsegment (1) nach einem der Ansprüche 1 bis 5, d a d u r c h g e k e n n z e i c h n e t , daß die hitzebestandige Trennschicht (7) em Metallgitter mit wabenformigen Zellen umfaßt.6. Wall segment (1) according to one of claims 1 to 5, d a d u r c h g e k e n n z e i c h n e t that the heat-resistant separating layer (7) comprises a metal grid with honeycomb cells.
7. Wandsegment (1) nach Anspruch 6, d a d u r c h g e k e n n z e i c h n e t , daß die wabenformigen Zellen der hitzebestandigen Trennschicht (7) mit einem deformierbaren Fullmaterial gefüllt sind.7. Wall segment (1) according to claim 6, that the honeycomb-shaped cells of the heat-resistant separating layer (7) are filled with a deformable full material.
8. Wandsegment (1) nach einem der Anspr che 1 bis 5, d a d u r c h g e k e n n z e i c h n e t , daß die hitzebestandige Trennschicht (7) em Filz aus Metalldrahten umfaßt.8. Wall segment (1) according to one of claims 1 to 5, d a d u r c h g e k e n e z e i c h n e t that the heat-resistant separating layer (7) comprises a felt made of metal wires.
9. Wandsegment (1) nach einem der Ansprüche 1 bis 8, d a d u r c h g e k e n n z e i c h n e t , daß die hitzebestandige Trennschicht (7) eine dünne Beschichtung auf der metallische Tragstruktur (3) ist.9. Wall segment (1) according to one of claims 1 to 8, d a d u r c h g e k e n n z e i c h n e t that the heat-resistant separating layer (7) is a thin coating on the metallic support structure (3).
10. Wandsegment (1) nach einem der Ansprüche 1 bis 9, d a d u r c h g e k e n n z e i c h n e t , daß die hitzebestandige Trennschicht (3) bei einer Temperatur von über 500°C, insbesondere bis ca. 800°C, zunderfest ist.10. Wall segment (1) according to one of claims 1 to 9, d a d u r c h g e k e n n z e i c h n e t that the heat-resistant separating layer (3) at a temperature of over 500 ° C, in particular up to about 800 ° C, is scale-resistant.
11. Wandsegment (1) nach einem der Ansprüche 1 bis 10, d a d u r c h g e k e n n z e i c h n e t , daß das Hitzeschutzelement (9) mechanisch an die metallische Tragstruktur (3) angebunden ist.11. Wall segment (1) according to one of claims 1 to 10, d a d u r c h g e k e n n z e i c h n e t that the heat protection element (9) is mechanically connected to the metallic support structure (3).
12. Wandsegment (1) nach Anspruch 11, d a d u r c h g e k e n n z e i c h n e t , daß das Hitzeschutzelement (9) durch eine Feder-Nut-Verbmdung mit der metallischen Tragstruktur (3) verbunden ist.12. Wall segment (1) according to claim 11, so that the heat protection element (9) is connected by a tongue and groove connection to the metallic support structure (3).
13. Wandsegment (1) Anspruch 11, d a d u r c h g e k e n n z e i c h n e t , daß 16 das Hitzeschutzelement (9) durch einen Bolzen 11) mit der metallischen Tragstruktur (3) verbunden ist.13. Wall segment (1) claim 11, characterized in that 16 the heat protection element (9) is connected by a bolt 11) to the metallic support structure (3).
14. Brennraum (2) mit einem Wandsegment (1) nach einem der14. combustion chamber (2) with a wall segment (1) according to one of the
Ansprüche 1 bis 13, d a d u r c h g e k e n n z e i c h n e t , daß das Wandsegment (1) Teil einer Brennkammer einer Gasturbine ist. Claims 1 to 13, so that the wall segment (1) is part of a combustion chamber of a gas turbine.
EP99916770A 1998-03-19 1999-03-01 Wall segment for a combustion chamber and combustion chamber Expired - Lifetime EP1064510B1 (en)

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PCT/DE1999/000542 WO1999047874A1 (en) 1998-03-19 1999-03-01 Wall segment for a combustion chamber and combustion chamber

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1302723A1 (en) 2001-10-15 2003-04-16 Siemens Aktiengesellschaft Lining for combustion chamber inside walls

Families Citing this family (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10003728A1 (en) * 2000-01-28 2001-08-09 Siemens Ag Heat shield arrangement for a component carrying hot gas, in particular for structural parts of gas turbines
EP1126221A1 (en) 2000-02-17 2001-08-22 Siemens Aktiengesellschaft Padded refactory tile as liner for a gas turbine combustor
US6540508B1 (en) * 2000-09-18 2003-04-01 The Boc Group, Inc. Process of installing roof mounted oxygen-fuel burners in a glass melting furnace
DE10046094C2 (en) 2000-09-18 2002-09-19 Siemens Ag Heat shield brick for lining a combustion chamber wall
EP1191285A1 (en) 2000-09-22 2002-03-27 Siemens Aktiengesellschaft Heat shield panel, combustion chamber with inner lining and a gas turbine
EP1381811A1 (en) * 2001-04-27 2004-01-21 Siemens Aktiengesellschaft Combustion chamber, in particular of a gas turbine
GB0117110D0 (en) * 2001-07-13 2001-09-05 Siemens Ag Coolable segment for a turbomachinery and combustion turbine
EP1312865A1 (en) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Gas turbine annular combustion chamber
US6640546B2 (en) * 2001-12-20 2003-11-04 General Electric Company Foil formed cooling area enhancement
US7178299B2 (en) * 2003-05-16 2007-02-20 Exxonmobil Research And Engineering Company Tiles with embedded locating rods for erosion resistant linings
JP2005030570A (en) * 2003-07-11 2005-02-03 Nichias Corp Vibration-proof heat shielding plate
EP1507116A1 (en) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Heat shield arrangement for a high temperature gas conveying component, in particular for a gas turbine combustion chamber
EP1507117A1 (en) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Combustion chamber, in particular gas turbine combustion chamber
EP1508761A1 (en) 2003-08-22 2005-02-23 Siemens Aktiengesellschaft Thermal shielding brick for lining a combustion chamber wall, combustion chamber and a gas turbine
EP1528343A1 (en) 2003-10-27 2005-05-04 Siemens Aktiengesellschaft Refractory tile with reinforcing members embedded therein, as liner for gas turbine combustion chamber
DE10350115A1 (en) * 2003-10-28 2005-06-16 Burwitz Feuerungsbau Gmbh Wall and / or ceiling construction, as well as wall modules and fastening devices therefor
EP1650503A1 (en) * 2004-10-25 2006-04-26 Siemens Aktiengesellschaft Method for cooling a heat shield element and a heat shield element
EP1701095B1 (en) * 2005-02-07 2012-01-18 Siemens Aktiengesellschaft Heat shield
EP1715271A1 (en) 2005-04-19 2006-10-25 Siemens Aktiengesellschaft Heat shield element, combustion chamber and gas turbine
JP2011508173A (en) * 2007-12-22 2011-03-10 ユンガー・プルス・グレーター・ゲゼルシャフト・ミト・ベシュレンクテル・ハフツング・フォイアーフェストバウ Industrial furnace wall lining
GB0801839D0 (en) * 2008-02-01 2008-03-05 Rolls Royce Plc combustion apparatus
WO2009122474A1 (en) * 2008-03-31 2009-10-08 川崎重工業株式会社 Cooling structure for gas turbine combustor
EP2224167A1 (en) * 2009-02-25 2010-09-01 Siemens Aktiengesellschaft Gas turbine casing
ES2531099T3 (en) * 2009-06-09 2015-03-10 Siemens Ag Thermal shield element arrangement and procedure for mounting a thermal shield element
US8372251B2 (en) 2010-05-21 2013-02-12 General Electric Company System for protecting gasifier surfaces from corrosion
CH703656A1 (en) * 2010-08-27 2012-02-29 Alstom Technology Ltd From hot gases flowed through housing body with internal heat shield.
EP2423596A1 (en) * 2010-08-27 2012-02-29 Siemens Aktiengesellschaft Heat shield element
US20120317984A1 (en) * 2011-06-16 2012-12-20 Dierberger James A Cell structure thermal barrier coating
AT12612U1 (en) * 2011-07-01 2012-08-15 Lasco Heutechnik Gmbh COMBUSTION CHAMBER FOR A MOBILE SOLID FUEL HEATING SYSTEM
US9534783B2 (en) * 2011-07-21 2017-01-03 United Technologies Corporation Insert adjacent to a heat shield element for a gas turbine engine combustor
WO2013014369A1 (en) * 2011-07-22 2013-01-31 Snecma Method for assembling a titanium shell and a titanium fire-resistant alloy shell
CN102400721B (en) * 2011-11-01 2014-04-02 沈阳黎明航空发动机(集团)有限责任公司 Replacement method of fulcrum heat-insulating screen of turbine bearing
EP2711634A1 (en) * 2012-09-21 2014-03-26 Siemens Aktiengesellschaft Heat shield with a support structure and method for cooling the support structure
US20150362192A1 (en) * 2013-01-17 2015-12-17 United Technologies Corporation Gas turbine engine combustor liner assembly with convergent hyperbolic profile
WO2014173568A1 (en) * 2013-04-22 2014-10-30 Siemens Aktiengesellschaft Heat shield block for a heat shield of a combustion chamber
WO2015017180A1 (en) * 2013-08-01 2015-02-05 United Technologies Corporation Attachment scheme for a ceramic bulkhead panel
EP3066390B1 (en) * 2013-11-04 2020-10-21 United Technologies Corporation Gas turbine engine wall assembly with offset rail
EP3084310A4 (en) * 2013-12-19 2017-01-04 United Technologies Corporation Gas turbine engine wall assembly with circumferential rail stud architecture
US10533745B2 (en) * 2014-02-03 2020-01-14 United Technologies Corporation Film cooling a combustor wall of a turbine engine
EP3040617B1 (en) 2014-12-31 2017-12-06 Rolls-Royce North American Technologies, Inc. Retention system for gas turbine engine assemblies
EP3211307B1 (en) 2016-02-26 2019-06-05 Jünger + Gräter GmbH Feuerfestbau Protective refractory element
DE102016103443B4 (en) * 2016-02-26 2022-04-28 Jünger+Gräter GmbH refractory protection segment
DE102016114177B4 (en) * 2016-04-15 2023-11-23 Jünger+Gräter GmbH Refractory protection segment
US10935235B2 (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
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
US20180230602A1 (en) * 2016-11-10 2018-08-16 United Technologies Corporation Coated combustor panel shell for a gas turbine engine combustor
DE102018204453B4 (en) * 2018-03-22 2024-01-18 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto
US10969106B2 (en) * 2019-08-13 2021-04-06 General Electric Company Axial retention assembly for combustor components of a gas turbine engine
JP2023183452A (en) * 2022-06-16 2023-12-28 川崎重工業株式会社 Combustor of gas turbine

Family Cites Families (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2867112A (en) * 1953-11-20 1959-01-06 Gen Electric Wire mesh supported refractory
US3204939A (en) * 1963-12-02 1965-09-07 The Illinois National Bank Co Heat treating apparatus
US3362698A (en) * 1966-01-26 1968-01-09 Detrick M H Co Refractory lining structure for a rotary kiln
US3584972A (en) * 1966-02-09 1971-06-15 Gen Motors Corp Laminated porous metal
DE2321561A1 (en) * 1973-04-28 1974-11-14 Plibrico Co Gmbh Refractory lining for rotary kiln - with prepd. high strength blocks of complicated shapes
GB1590449A (en) * 1977-05-06 1981-06-03 Bloom Eng Co Inc Reinforced insulating members
JPS5857658B2 (en) * 1980-04-02 1983-12-21 工業技術院長 Heat shielding structure for walls exposed to high heat using ceramics
US4379382A (en) * 1980-06-02 1983-04-12 Sauder Industries, Inc. Method and apparatus for insulating a furnace having a corrosive atmosphere
CA1215831A (en) * 1982-06-10 1986-12-30 Mitsuo Yamashita Furnace wall construction for industrial use
SU1167202A1 (en) * 1983-04-27 1985-07-15 Украинский Государственный Институт По Проектированию Металлургических Заводов Blast furnace air heater
US4642993A (en) * 1985-04-29 1987-02-17 Avco Corporation Combustor liner wall
EP0224817B1 (en) * 1985-12-02 1989-07-12 Siemens Aktiengesellschaft Heat shield arrangement, especially for the structural components of a gas turbine plant
US4751962A (en) * 1986-02-10 1988-06-21 General Motors Corporation Temperature responsive laminated porous metal panel
US4840131A (en) 1986-09-13 1989-06-20 Foseco International Limited Insulating linings for furnaces and kilns
US4709643A (en) * 1987-02-24 1987-12-01 Prutech Ii Primary stage combustor lining
FR2611864B1 (en) * 1987-02-27 1989-05-05 Stein Industrie DEVICE FOR PROTECTING BOILER SCREENS, PARTICULARLY FOR GARBAGE INCINERATION FURNACES, AND METHOD FOR MANUFACTURING THE SAME
US4838030A (en) * 1987-08-06 1989-06-13 Avco Corporation Combustion chamber liner having failure activated cooling and dectection system
US4838031A (en) * 1987-08-06 1989-06-13 Avco Corporation Internally cooled combustion chamber liner
FR2624952B1 (en) * 1987-12-22 1990-04-06 Stein Industrie DEVICE FOR PROTECTING A HEAT RECOVERY BOILER SCREEN AND MANUFACTURING METHOD THEREOF
DE58908665D1 (en) * 1988-06-13 1995-01-05 Siemens Ag HEAT SHIELD ARRANGEMENT WITH LOW COOLING FLUID REQUIREMENT.
US4944151A (en) * 1988-09-26 1990-07-31 Avco Corporation Segmented combustor panel
US5129223A (en) * 1989-04-07 1992-07-14 Doellner Oscar L Radiant energy power source structure
US5163831A (en) * 1989-09-20 1992-11-17 Frazier-Simplex, Inc. Refractory tile for a suspended furnace wall
US5033959A (en) * 1990-10-15 1991-07-23 J. O. Bernt & Associates Limited Kiln liner
US5431020A (en) * 1990-11-29 1995-07-11 Siemens Aktiengesellschaft Ceramic heat shield on a load-bearing structure
US5142839A (en) * 1991-05-02 1992-09-01 Kraemer Robert P Method for construction of refractory lining for furnace
US5216886A (en) * 1991-08-14 1993-06-08 The United States Of America As Represented By The Secretary Of The Air Force Segmented cell wall liner for a combustion chamber
JPH05322455A (en) * 1992-05-28 1993-12-07 Kawasaki Steel Corp Furnace wall structure of induction heating furnace
US5265411A (en) * 1992-10-05 1993-11-30 United Technologies Corporation Attachment clip
US5331816A (en) * 1992-10-13 1994-07-26 United Technologies Corporation Gas turbine engine combustor fiber reinforced glass ceramic matrix liner with embedded refractory ceramic tiles
FR2707272B1 (en) * 1993-07-09 1995-09-15 Stein Heurtey Improvements brought to the cooled rollers for the handling of products in particular metallurgical and iron and steel.
US5592814A (en) * 1994-12-21 1997-01-14 United Technologies Corporation Attaching brittle composite structures in gas turbine engines for resiliently accommodating thermal expansion
DE19502730A1 (en) * 1995-01-28 1996-08-01 Abb Management Ag Ceramic lining
US5605046A (en) * 1995-10-26 1997-02-25 Liang; George P. Cooled liner apparatus
WO1998005901A1 (en) * 1996-08-07 1998-02-12 Mitsubishi Heavy Industries, Ltd. Water pipe protecting refractory structure
CA2292529C (en) * 1997-05-30 2005-04-05 Hoogovens Staal B.V. Refractory wall structure
EP0895027B1 (en) * 1997-07-28 2002-03-06 Alstom Ceramic lining
US6095807A (en) * 1998-10-02 2000-08-01 Grupo Nutec S.A. De C.V. Anti-sliding bar for furnace wall constructions
EP1006315B1 (en) * 1998-11-30 2004-01-21 ALSTOM (Switzerland) Ltd Ceramic lining for a combustion chamber

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9947874A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1302723A1 (en) 2001-10-15 2003-04-16 Siemens Aktiengesellschaft Lining for combustion chamber inside walls

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US20020050237A1 (en) 2002-05-02
WO1999047874A1 (en) 1999-09-23
US6397765B1 (en) 2002-06-04
DE59903399D1 (en) 2002-12-19
US6612248B2 (en) 2003-09-02
EP1064510B1 (en) 2002-11-13
JP4172913B2 (en) 2008-10-29

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