EP2918915B1 - Combustion chamber shingle of a gas turbine - Google Patents

Combustion chamber shingle of a gas turbine Download PDF

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Publication number
EP2918915B1
EP2918915B1 EP15158450.5A EP15158450A EP2918915B1 EP 2918915 B1 EP2918915 B1 EP 2918915B1 EP 15158450 A EP15158450 A EP 15158450A EP 2918915 B1 EP2918915 B1 EP 2918915B1
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EP
European Patent Office
Prior art keywords
combustion chamber
bolt
chamber tile
accordance
mounting
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.)
Not-in-force
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EP15158450.5A
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German (de)
French (fr)
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EP2918915A1 (en
Inventor
Carsten Clemen
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Publication of EP2918915A1 publication Critical patent/EP2918915A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to gas turbine combustors with combustor shingles, wherein the combustor shingles are attached to a supporting structure of the combustion chamber outer walls.
  • the combustion chamber shingles have any (very high, often several thousand) number of Effusionskühllöchern on the side facing the combustion chamber side. These effusion cooling holes serve to cool the shingle from the high temperatures in the combustion chamber.
  • located on the combustion chamber shingle at least one mixing air hole, which serves to air from the outer chamber surrounding the combustion chamber (annulus) in the combustion chamber for the purpose of cooling and Abmagerns combustion and thus the reduction of NOx formation in the combustion chamber conduct.
  • the shingles are often still provided with a ceramic coating, which acts as an insulating layer against the high temperatures in the combustion chamber.
  • the FIG. 2 schematically shows a combustion chamber 15.
  • the combustion chamber 15 includes a fuel nozzle 29, which is supported in a conventional manner to a combustion chamber head. Furthermore, a combustion chamber outer housing 30 and a combustion chamber inner housing 31 are provided.
  • a combustion chamber wall 32 encloses the actual combustion chamber 15 and carries combustion chamber shingles 34.
  • the reference numeral 33 schematically shows a Turbinenvorleit Herbert. By Zumischlöcher 35 air is supplied in the usual manner. The inflow direction is designated by the reference numeral 36.
  • FIG. 3 shows a shingle 34 with effusion cooling holes 37 according to the prior art.
  • the geometry (diameter, shape) of the mixing hole 35 can be suitably formed as known in the art. The same applies to the size and arrangement of the effusion cooling holes 37.
  • the training of Zumischlöcher 35 often takes place so that they are constructive as a funnel or a tube which projects into the combustion chamber 15, are formed.
  • the shingles 34 are usually formed either by casting, coating with a ceramic layer and drilling the effusion cooling holes 37 (e.g., laser), or by casting, drilling, and coating, or by an additive manufacturing method, such as a laser. Selective laser sintering, direct laser depositioning or by electron beam welding. In the additive process, the effusion cooling holes 37 are introduced directly into the shingle 34 and the costly drilling is eliminated.
  • the effusion cooling holes 37 e.g., laser
  • the construction of the shank with integrated threaded pin is only conditionally for an additive manufacturing, e.g. Selective laser sintering, direct laser deposition or electron beam deposition welding, suitable because either the costly horizontal production must be selected or a complex substructure must be provided to support the threaded pin.
  • an additive manufacturing e.g. Selective laser sintering, direct laser deposition or electron beam deposition welding
  • Such a substructure has significant disadvantages. It is a) material-intensive, b) it extends the manufacturing process and c) it has to be removed from the shingle after production. This is very expensive.
  • the EP 2 270 395 A1 shows a heat shield element arrangement for gas turbines, in which heat shield elements by means of spring elements and screws from the hot Side of the heat shield element from being attached to a support structure.
  • the screw used for this purpose can be provided with a centric air channel.
  • the invention has for its object to provide a combustion chamber shingle gas turbine and a mounting option such a combustion chamber, which avoid the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and ensure good fastenability.
  • the shingle is formed substantially plate-shaped and on one side (namely at the combustion chamber wall facing side) has at least one bearing element which is integrally formed on the shingle.
  • the bearing element is designed so that a bolt, which is made as a separate component, can be anchored or fastened in a form-fitting manner.
  • the combustion chamber shingle according to the invention is thus designed so that a separate bolt, which according to the invention may be a threaded bolt or a bolt to be fastened with a securing element, is anchored in a form-fitting manner to the shingle.
  • a separate bolt which according to the invention may be a threaded bolt or a bolt to be fastened with a securing element, is anchored in a form-fitting manner to the shingle.
  • the bolt is preferably made for the bolt to be provided at its end region with a bearing area arranged at right angles to the bolt axis, which bearing area is arranged in a recess of the bearing element.
  • the bolt is thus similar to a hook, and is inserted into the recess of the bearing element.
  • the storage area of the bolt can be dimensioned in a suitable manner, for example plate-shaped or with any other cross-sections, for example round, oval, square or rectangular.
  • the combustion chamber shingle thus has by the bearing element and the recess provided therein a receptacle for the bolt, so that it can be hooked in a form-fitting manner in the shingle. It is inventively possible to include the storage area with play or without play in the recess, in particular to take into account different thermal expansions or the like.
  • the recess of the bearing element is designed so that the storage area of the bolt can be inserted laterally.
  • the recesses open to different directions. As a result, a release of the bolt is prevented.
  • the bolt according to the invention is inserted in a conventional manner through a hole of the combustion chamber outer wall, so that the actual attachment of the bolt does not differ significantly from the prior art. Thus, it is possible to unscrew a nut in a conventional manner in a threaded bolt.
  • the embodiment of the invention also makes it possible to support the shingle relative to the combustion chamber wall or, in an alternative embodiment, to apply the shingle directly to the combustion chamber wall.
  • different cooling concepts can be formed, as is known from the prior art.
  • the outer contour of the bearing element which is attached to the combustion chamber shingle aerodynamic form, for example, to provide with bevelled edges.
  • effusion cooling holes may be formed to ensure the cooling of the combustion chamber shingles.
  • the bolt has a central passage opening through which cooling air can be introduced.
  • the recess of the bearing element is designed and dimensioned such that when the bolt or mounted combustion chamber shingles a cavity between the bearing portion of the bolt and the surface of the combustion chamber shingles results, which is traversed by cooling air. This also leads to a particularly good cooling.
  • the bearing element is provided with additional cooling holes. These may be formed as impact cooling holes to additionally cool the lower portion of the bolt and its storage area.
  • the inventive bolt with the storage area formed on it can be cast, milled or produced by an additive process.
  • the combustion chamber shingle is designed such that it can be produced by means of an additive method.
  • additive methods are, for example, selective laser sintering, direct laser depositioning (DLD) or electron beam deposition welding.
  • DLD direct laser depositioning
  • the shingle is so manufacturable that neither a costly horizontal production, nor a complex substructure are required. Thus, the shingle can be inexpensively and easily manufactured.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate-pressure compressor 13 and the high-pressure compressor 14 each comprise a plurality of stages, each of which has a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, extending radially inward from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 4 shows different side views according to the prior art, in which a support 41 of the combustion chamber shingle 34 is shown against the combustion chamber wall 32.
  • the Fig. 5 shows a simplified plan view of a combustor shingle 34 according to the invention.
  • rims 51 are provided at the edge, which, as well as from Fig. 6 can be seen, are formed in the form of a web-like edge.
  • a bearing element 40 is provided in the four corners of the combustion chamber shingle 34 in the four corners of the combustion chamber shingle 34 in the four corners of the combustion chamber shingle 34 in the four corners of the combustion chamber shingle 34 each have a bearing element 40 is provided, which is provided with a slot-like or pocket-like recess 44. It can be seen that the opening directions of the recesses 44 are oriented differently, so that inserted bolts 38 in the assembled state can not slip out, even if the nuts 39 solve, since the bolts 38 are located in recesses or holes of the associated combustion chamber wall 32.
  • a bearing element 40 is arranged in the central area of the Fig. 5 in the central area of the Fig. 5 in the central area of the Fig.
  • Fig. 6 shows in a greatly simplified form a mounted side view, analogous to the representation of Fig. 5 ,
  • the Fig. 7 shows in the upper and lower rows respectively threaded bolts 38. These each have a central through-hole 48 in the form of a hole through which the through-hole cooling air can pass. From the pictures of Fig. 7 It can be seen that each bolt 38 is provided with a perpendicular to its central axis aligned bearing portion 47, which is insertable into a suitable recess 44 of the bearing member 40, as shown in FIG Fig. 10 is shown. From the Fig. 7 It turns out that different forms of Storage areas 47 may be provided, namely round, square, rectangular, rounded or trapezoidal. Other shapes are also possible. The Fig. 7 shows that the storage area 47 may be provided with at least one cooling air hole 50 to cool the storage area 47 and thus the lower area of the bolt 38.
  • the Fig. 8 shows a wide variety of design variants of bolts 38 with bearing areas 47, analogous to the representations of Fig. 7 ,
  • associated bearing elements 40 are shown with suitable recesses 44.
  • the bearing elements 40 may also be provided with cooling holes 52. It follows that the recesses 44 of the bearing elements 40 are each dimensioned so that the bolts 38 can be inserted laterally with the bearing areas 47.
  • Fig. 9 arise in a variety of design variants in the assembled state, in particular it can be seen how the storage areas 47 are respectively inserted into the slot-like or pocket-like recesses 44 of the bearing elements 40.
  • the bearing areas 47 rest against the upper limbs or surfaces of the bearing elements 40, so that a cavity 49 forms below the bearing areas 47, in which cooling air is introduced on the one hand through the through-hole 48 of the bolt 38 and on the other hand through additional cooling holes 52.
  • additional cooling holes 52 for cooling air flow are also lateral recesses 53, which on the two right below in Fig. 9 shown embodiment variants are shown.
  • the Fig. 10 shows in a simplified sectional view of an assembled state of the bolt 38 according to the invention with its storage area 47 in a recess 44 of a bearing element 40. Again, the cavity 49 is clarified, which is filled with cooling air. Furthermore, cooling air can flow through effusion cooling holes 37.
  • the Fig. 11 shows a further embodiment variant, in which the storage areas 40 are each provided with lateral cooling holes 52, which are provided in rows or in regular arrangements to introduce cooling air to the lower portion of the bolt 38.
  • the Fig. 12 shows in different perspective partial views again possible embodiments of the bearing elements 40. It follows that these may be bell-like or bow-shaped and each having a lateral slot or a lateral opening to insert the bolt 38.

Description

Die Erfindung bezieht sich auf Gasturbinenbrennkammern mit Brennkammerschindeln, wobei die Brennkammerschindeln an einer tragenden Struktur der Brennkammeraußenwände befestigt sind.The invention relates to gas turbine combustors with combustor shingles, wherein the combustor shingles are attached to a supporting structure of the combustion chamber outer walls.

Die Brennkammerschindeln weisen eine beliebige (sehr hohe, oftmals mehrere Tausend) Anzahl von Effusionskühllöchern auf der zur Brennkammer gerichteten Seite auf. Diese Effusionskühllöcher dienen dazu, die Schindel gegenüber den hohen Temperaturen in der Brennkammer zu kühlen. Darüber hinaus befindet sich auf der Brennkammerschindel mindestens ein Mischluftloch, das dazu dient, Luft aus dem die Brennkammer außen umgebenden Raum (Ringkanal/Annulus) in die Brennkammer zum Zwecke des Abkühlens und Abmagerns der Verbrennung und damit der Reduktion der NOx Entstehung in die Brennkammer zu leiten. Neben der Kühlung durch die Effusionskühllöcher sind die Schindeln häufig noch mit einer keramischen Beschichtung versehen, die als Dämmschicht gegen die hohen Temperaturen in der Brennkammer wirkt.The combustion chamber shingles have any (very high, often several thousand) number of Effusionskühllöchern on the side facing the combustion chamber side. These effusion cooling holes serve to cool the shingle from the high temperatures in the combustion chamber. In addition, located on the combustion chamber shingle at least one mixing air hole, which serves to air from the outer chamber surrounding the combustion chamber (annulus) in the combustion chamber for the purpose of cooling and Abmagerns combustion and thus the reduction of NOx formation in the combustion chamber conduct. In addition to cooling by the Effusionskühllöcher the shingles are often still provided with a ceramic coating, which acts as an insulating layer against the high temperatures in the combustion chamber.

Diese Anordnung ist aus dem Stand der Technik bekannt, siehe EP 972 992 B1 oder DE 102 14 570 A1 .This arrangement is known from the prior art, see EP 972 992 B1 or DE 102 14 570 A1 ,

Die Figur 2 zeigt schematisch eine Brennkammer 15. Die Brennkammer 15 umfasst eine Treibstoffdüse 29, welche in üblicher Weise an einem Brennkammerkopf gehaltert ist. Weiterhin sind ein Brennkammeraußengehäuse 30 sowie ein Brennkammerinnengehäuse 31 vorgesehen. Eine Brennkammerwand 32 umschließt die eigentliche Brennkammer 15 und trägt Brennkammerschindeln 34. Das Bezugszeichen 33 zeigt schematisch eine Turbinenvorleitreihe. Durch Zumischlöcher 35 wird in üblicher Weise Luft zugeführt. Die Zuströmrichtung ist mit dem Bezugszeichen 36 bezeichnet.The FIG. 2 schematically shows a combustion chamber 15. The combustion chamber 15 includes a fuel nozzle 29, which is supported in a conventional manner to a combustion chamber head. Furthermore, a combustion chamber outer housing 30 and a combustion chamber inner housing 31 are provided. A combustion chamber wall 32 encloses the actual combustion chamber 15 and carries combustion chamber shingles 34. The reference numeral 33 schematically shows a Turbinenvorleitreihe. By Zumischlöcher 35 air is supplied in the usual manner. The inflow direction is designated by the reference numeral 36.

Die Figur 3 zeigt eine Schindel 34 mit Effusionskühllöchern 37 gemäß dem Stand der Technik. Die Geometrie (Durchmesser, Form) des Zumischlochs 35 kann, wie aus dem Stand der Technik bekannt, in geeigneter Weise ausgebildet werden. Gleiches trifft für die Größe und Anordnung der Effusionskühllöcher 37 zu. Die Ausbildung der Zumischlöcher 35 erfolgt häufig so, dass diese konstruktiv wie ein Trichter oder ein Rohr, das in die Brennkammer 15 hineinragt, ausgebildet sind.The FIG. 3 shows a shingle 34 with effusion cooling holes 37 according to the prior art. The geometry (diameter, shape) of the mixing hole 35 can be suitably formed as known in the art. The same applies to the size and arrangement of the effusion cooling holes 37. The training of Zumischlöcher 35 often takes place so that they are constructive as a funnel or a tube which projects into the combustion chamber 15, are formed.

Die Herstellung der Schindeln 34 erfolgt üblicherweise entweder durch Gießen, Beschichten mit einer keramischen Schicht und Bohren der Effusionskühllöcher 37 (z.B. mit Laser) oder durch Gießen, Bohren und Beschichten oder durch ein additives Fertigungsverfahren, wie z.B. Selective Laser Sintering, Direct Laser Depositioning oder mittels Elektronenstrahlauftragsschweißen. Bei den additiven Verfahren werden dabei die Effusionskühllöcher 37 direkt in die Schindel 34 eingebracht und das aufwändige Bohren entfällt.The shingles 34 are usually formed either by casting, coating with a ceramic layer and drilling the effusion cooling holes 37 (e.g., laser), or by casting, drilling, and coating, or by an additive manufacturing method, such as a laser. Selective laser sintering, direct laser depositioning or by electron beam welding. In the additive process, the effusion cooling holes 37 are introduced directly into the shingle 34 and the costly drilling is eliminated.

Während des Betriebs treten immer wieder Probleme mit sogenanntem Kriechen des Materials auf, welches zum Versagen des Gewindestiftes führen kann und damit zu einem Verlust der Schindel.During operation, problems occur repeatedly with so-called creep of the material, which can lead to failure of the set screw and thus to a loss of shingles.

Darüber hinaus ist die Konstruktion der Schindel mit integriertem Gewindestift nur bedingt für eine additive Fertigung, z.B. Selective Laser Sintering, Direct Laser Depositioning oder Elektronenstrahlauftragsschweißen, geeignet, da entweder die kostenintensive horizontale Fertigung gewählt werden muss oder eine aufwändige Unterkonstruktion zur Abstützung des Gewindestiftes vorgesehen werden muss. Eine solche Unterkonstruktion hat wesentliche Nachteile. Sie ist a) materialintensiv, b) sie verlängert den Fertigungsprozess und c) sie muss nach der Fertigung von der Schindel entfernt werden. Dies ist sehr kostenintensiv.Moreover, the construction of the shank with integrated threaded pin is only conditionally for an additive manufacturing, e.g. Selective laser sintering, direct laser deposition or electron beam deposition welding, suitable because either the costly horizontal production must be selected or a complex substructure must be provided to support the threaded pin. Such a substructure has significant disadvantages. It is a) material-intensive, b) it extends the manufacturing process and c) it has to be removed from the shingle after production. This is very expensive.

Aus der US 2001/0035003 A1 , welche den Oberbegriff des Anspruchs 1 offenbart, ist ein System bekannt, bei welchem an einer Wandung eine plattenförmige Abschirmung zur thermischen Isolation befestigt ist. An der Abschirmung sind Lagerkanäle befestigt, in welche durch seitliche Schlitze Gewindeschrauben eingeschoben werden, die mit der Wandung verschraubt werden. Eine Kühlung der Abschirmung ist nicht weiter vorgesehen.From the US 2001/0035003 A1 Disclosing the preamble of claim 1, a system is known in which a plate-shaped shield for thermal insulation is attached to a wall. On the shield bearing channels are fixed, in which through lateral slots threaded screws are inserted, which are bolted to the wall. Cooling of the shield is not provided further.

Die EP 2 270 395 A1 zeigt eine Hitzeschildelementanordnung für Gasturbinen, bei welcher Hitzeschildelemente mittels Federelementen und Schrauben von der heißen
Seite des Hitzeschildelements aus an einer Tragstruktur befestigt werden. Die hierfür verwendete Schraube kann mit einem zentrischen Luftkanal versehen sein.The EP 2 270 395 A1 shows a heat shield element arrangement for gas turbines, in which heat shield elements by means of spring elements and screws from the hot
Side of the heat shield element from being attached to a support structure. The screw used for this purpose can be provided with a centric air channel.

Eine ähnliche Konstruktion zeigt die GB 2 380 236 A . Auch hierbei werden Schindeln von der heißen Seite aus mittels Gewindeschrauben mit einer Wandung verschraubt, wobei die Schrauben eine zentrische Kühlluftausnehmung aufweisen.A similar construction shows the GB 2 380 236 A , Here, too, shingles are screwed from the hot side by means of threaded screws with a wall, wherein the screws have a central Kühlluftausnehmung.

Der Erfindung liegt die Aufgabe zugrunde, eine Brennkammerschindel einer Gasturbine und eine Befestigungsmöglichkeit einer derartigen Brennkammer zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit die Nachteile des Standes der Technik vermeiden und eine gute Befestigbarkeit gewährleisten.The invention has for its object to provide a combustion chamber shingle gas turbine and a mounting option such a combustion chamber, which avoid the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and ensure good fastenability.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruches 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the feature combination of claim 1, the dependent claims show further advantageous embodiments of the invention.

Erfindungsgemäß ist somit vorgesehen, dass die Schindel im Wesentlichen plattenförmig ausgebildet ist und an einer Seite (nämlich an der der Brennkammerwand
zugewandten Seite) zumindest ein Lagerelement aufweist, welches einstückig an der Schindel ausgebildet ist. Das Lagerelement ist so ausgebildet, dass an diesem ein Bolzen, welcher als separates Bauteil gefertigt ist, formschlüssig verankerbar oder befestigbar ist.According to the invention it is thus provided that the shingle is formed substantially plate-shaped and on one side (namely at the combustion chamber wall
facing side) has at least one bearing element which is integrally formed on the shingle. The bearing element is designed so that a bolt, which is made as a separate component, can be anchored or fastened in a form-fitting manner.

Die erfindungsgemäße Brennkammerschindel ist somit so ausgebildet, dass ein separater Bolzen, der erfindungsgemäß ein Gewindebolzen oder ein mit einem Sicherungselement zu befestigender Bolzen sein kann, formschlüssig an der Schindel verankert wird. Somit ist es erfindungsgemäß möglich, den Bolzen aus einem anderen Material zu fertigen, als die Schindel. Weiterhin ist es möglich, für die Schindel ein einfaches und kostengünstiges Herstellungsverfahren zu wählen, da der Bolzen als separates Bauteil hergestellt werden kann. Insbesondere durch die Möglichkeit, für die Schindel und den Bolzen unterschiedliche Materialien zu verwenden, ist es möglich, die beim Stand der Technik bekannten Befestigungsprobleme zu lösen und ein Kriechen des Bolzen-Werkstoffs zu unterbinden oder zu minimieren.The combustion chamber shingle according to the invention is thus designed so that a separate bolt, which according to the invention may be a threaded bolt or a bolt to be fastened with a securing element, is anchored in a form-fitting manner to the shingle. Thus, it is possible according to the invention to produce the bolt of a different material than the shingle. Furthermore, it is possible to choose a simple and cost-effective production method for the shingle, since the bolt can be manufactured as a separate component. In particular, by the possibility of using different materials for the shingle and the bolt, it is possible to solve the fastening problems known in the prior art and to prevent or minimize creep of the bolt material.

Erfindungsgemäß ist bevorzugterweise vorgesehen, dass der Bolzen an seinem Endbereich mit einem rechtwinklig zur Bolzenachse angeordneten Lagerbereich versehen ist, welcher in einer Ausnehmung des Lagerelements angeordnet ist. Der Bolzen ist somit ähnlich eines Hakens ausgebildet, und wird in die Ausnehmung des Lagerelements eingesteckt. Dabei kann der Lagerbereich des Bolzens in geeigneter Weise dimensioniert werden, beispielsweise plattenförmig oder mit beliebigen sonstigen Querschnitten, beispielsweise rund, oval, viereckig oder rechteckig. Die Brennkammerschindel hat somit durch das Lagerelement und die darin vorgesehene Ausnehmung eine Aufnahme für den Bolzen, so dass dieser formschlüssig in die Schindel eingehängt werden kann. Dabei ist es erfindungsgemäß möglich, den Lagerbereich mit Spiel oder ohne Spiel in der Ausnehmung aufzunehmen, insbesondere, um unterschiedliche Wärmeausdehnungen oder ähnliches zu berücksichtigen.According to the invention, provision is preferably made for the bolt to be provided at its end region with a bearing area arranged at right angles to the bolt axis, which bearing area is arranged in a recess of the bearing element. The bolt is thus similar to a hook, and is inserted into the recess of the bearing element. In this case, the storage area of the bolt can be dimensioned in a suitable manner, for example plate-shaped or with any other cross-sections, for example round, oval, square or rectangular. The combustion chamber shingle thus has by the bearing element and the recess provided therein a receptacle for the bolt, so that it can be hooked in a form-fitting manner in the shingle. It is inventively possible to include the storage area with play or without play in the recess, in particular to take into account different thermal expansions or the like.

Die Ausnehmung des Lagerelements ist so ausgebildet, dass der Lagerbereich des Bolzens seitlich eingesteckt werden kann. Um beim Betrieb ein Herausrutschen des Lagerbereichs des Bolzens aus der Ausnehmung des Lagerelements zu vermeiden, kann es in Weiterbildung der Erfindung günstig sein, an einer Schindel mehrere derartige Lagerelemente vorzusehen, deren Ausnehmungen sich zu unterschiedlichen Richtungen hin öffnen. Hierdurch wird ein Lösen des Bolzens verhindert.The recess of the bearing element is designed so that the storage area of the bolt can be inserted laterally. In order to avoid slipping out of the storage area of the bolt from the recess of the bearing element during operation, it may be beneficial in a further development of the invention, on a shingle more provide such bearing elements, the recesses open to different directions. As a result, a release of the bolt is prevented.

Der erfindungsgemäße Bolzen wird in üblicher Weise durch ein Loch der Brennkammeraußenwand gesteckt, so dass sich die eigentliche Befestigung des Bolzens nicht wesentlich vom Stand der Technik unterscheidet. So ist es möglich, bei einem Gewindebolzen in üblicher Weise eine Mutter aufzuschrauben.The bolt according to the invention is inserted in a conventional manner through a hole of the combustion chamber outer wall, so that the actual attachment of the bolt does not differ significantly from the prior art. Thus, it is possible to unscrew a nut in a conventional manner in a threaded bolt.

Die erfindungsgemäße Ausgestaltung ermöglicht es auch, die Schindel gegenüber der Brennkammerwand abzustützen oder in alternativer Ausgestaltung die Schindel direkt an die Brennkammerwand anzulegen. Somit können unterschiedliche Kühlkonzepte ausgebildet werden, so wie dies auch aus dem Stand der Technik bekannt ist.The embodiment of the invention also makes it possible to support the shingle relative to the combustion chamber wall or, in an alternative embodiment, to apply the shingle directly to the combustion chamber wall. Thus, different cooling concepts can be formed, as is known from the prior art.

Weiterhin ist es erfindungsgemäß möglich, die Außenkontur des Lagerelements, welches an der Brennkammerschindel befestigt ist, strömungsgünstig auszubilden, beispielsweise mit abgeschrägten Flanken zu versehen. In dem Lagerelement können erfindungsgemäß auch Effusionskühllöcher ausgebildet sein, um die Kühlung der Brennkammerschindel zu gewährleisten.Furthermore, it is possible according to the invention, the outer contour of the bearing element, which is attached to the combustion chamber shingle aerodynamic form, for example, to provide with bevelled edges. In the bearing element according to the invention also effusion cooling holes may be formed to ensure the cooling of the combustion chamber shingles.

Erfindungsgemäß ist somit vorgesehen, dass der Bolzen eine zentrische Durchgangsöffnung aufweist, durch welche Kühlluft einleitbar ist. Hierdurch erfolgt eine zuverlässige und effektive Kühlung des Bolzens, so dass die aus dem Stand der Technik bekannten thermischen Probleme (Kriechen des Werkstoffs) vermieden werden. Weiterhin ist die Ausnehmung des Lagerelements so ausgebildet und dimensioniert, dass sich bei montiertem Bolzen bzw. montierter Brennkammerschindel ein Hohlraum zwischen dem Lagerbereich des Bolzens und der Oberfläche der Brennkammerschindel ergibt, welcher mit Kühlluft durchströmt wird. Auch dies führt zu einer besonders guten Kühlung.According to the invention it is thus provided that the bolt has a central passage opening through which cooling air can be introduced. This results in a reliable and effective cooling of the bolt, so that the known from the prior art thermal problems (creep of the material) can be avoided. Furthermore, the recess of the bearing element is designed and dimensioned such that when the bolt or mounted combustion chamber shingles a cavity between the bearing portion of the bolt and the surface of the combustion chamber shingles results, which is traversed by cooling air. This also leads to a particularly good cooling.

In Weiterbildung der Erfindung ist weiterhin vorgesehen, dass das Lagerelement mit zusätzlichen Kühllöchern versehen ist. Diese können als Prallkühllöcher ausgebildet sein, um den unteren Bereich des Bolzens und dessen Lagerbereich zusätzlich zu kühlen.In a further development of the invention is further provided that the bearing element is provided with additional cooling holes. These may be formed as impact cooling holes to additionally cool the lower portion of the bolt and its storage area.

Der erfindungsgemäße Bolzen mit dem an ihm ausgebildeten Lagerbereich kann gegossen, gefräst oder durch ein additives Verfahren hergestellt werden. Erfindungsgemäß ist die Brennkammerschindel so ausgebildet, dass diese mittels eines additiven Verfahrens herstellbar ist. Derartige additive Verfahren sind beispielsweise das Selective Laser Sintering, das Direct Laser Depositioning (DLD) oder das Elektronenstrahlauftragsschweißen. Dabei ist die Schindel so herstellbar, dass weder eine kostenintensive horizontale Fertigung, noch eine aufwendige Unterkonstruktion erforderlich sind. Somit kann die Schindel kostengünstig und einfach hergestellt werden.The inventive bolt with the storage area formed on it can be cast, milled or produced by an additive process. According to the invention, the combustion chamber shingle is designed such that it can be produced by means of an additive method. Such additive methods are, for example, selective laser sintering, direct laser depositioning (DLD) or electron beam deposition welding. The shingle is so manufacturable that neither a costly horizontal production, nor a complex substructure are required. Thus, the shingle can be inexpensively and easily manufactured.

Im Folgenden wird die Erfindung anhand von Ausführungsbeispielen in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:

Fig. 1
eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung,
Fig. 2
eine schematische Seitenansicht (im Schnitt) einer Brennkammer gemäß dem Stand der Technik,
Fig. 3
eine Draufsicht und eine Seitenansicht einer aus dem Stand der Technik bekannten Brennkammerschindel,
Fig. 4
eine Seiten-Schnittansicht einer Befestigungsmöglichkeit einer Brennkammerschindel an der Brennkammeraußenwand gemäß dem Stand der Technik,
Fig. 5
eine vereinfachte schematische Draufsicht auf eine erfindungsgemäße Schindel mit Lagerelementen für einen Lagerbereich eines Bolzens,
Fig. 6
eine schematische Seitenansicht einer Schindel, welche in erfindungsgemäßer Weise an einer Brennkammerwand montiert ist,
Fig.7
Seitenansichten und Draufsichten unterschiedlicher Ausgestaltungsvarianten von Bolzen mit Lagerbereichen,
Fig. 8
unterschiedlichste Ausgestaltungsvarianten von Bolzen mit Lagerbereichen sowie von Lagerelementen mit taschenartigen Ausnehmungen,
Fig. 9
unterschiedliche Ausgestaltungsvarianten in Seitenansicht und Draufsicht,
Fig. 10
eine vereinfachte Seitenansicht, analog Fig. 6, im montierten Zustand,
Fig. 11
perspektivische Teil-Ansichten von Lagerelementen mit Kühllöchern, und
Fig. 12
unterschiedlichste Ausgestaltungsvarianten von Lagerelementen, welche nicht Teil der Erfindung sind, in perspektivischer Teilansicht.
In the following the invention will be described by means of embodiments in conjunction with the drawing. Showing:
Fig. 1
a schematic representation of a gas turbine engine according to the present invention,
Fig. 2
a schematic side view (in section) of a combustion chamber according to the prior art,
Fig. 3
a top view and a side view of a known from the prior art combustion chamber shingles,
Fig. 4
1 is a side sectional view of a possibility of attachment of a combustion chamber shingle to the combustion chamber outer wall according to the prior art,
Fig. 5
a simplified schematic plan view of a shingle according to the invention with bearing elements for a storage area of a bolt,
Fig. 6
a schematic side view of a shingle, which is mounted according to the invention on a combustion chamber wall,
Figure 7
Side views and top views of different design variants of bolts with bearing areas,
Fig. 8
various design variants of bolts with bearing areas as well as bearing elements with pocket-like recesses,
Fig. 9
different design variants in side view and top view,
Fig. 10
a simplified side view, analog Fig. 6 , when assembled,
Fig. 11
partial perspective views of bearing elements with cooling holes, and
Fig. 12
A wide variety of design variants of bearing elements, which are not part of the invention, in a perspective partial view.

Das Gasturbinentriebwerk 10 gemäß Fig. 1 ist ein Beispiel einer Turbomaschine, bei der die Erfindung Anwendung finden kann. Aus dem Folgenden wird jedoch klar, dass die Erfindung auch bei anderen Turbomaschinen verwendet werden kann. Das Triebwerk 10 ist in herkömmlicher Weise ausgebildet und umfasst in Strömungsrichtung hintereinander einen Lufteinlass 11, einen in einem Gehäuse umlaufenden Fan 12, einen Mitteldruckkompressor 13, einen Hochdruckkompressor 14, Brennkammern 15, eine Hochdruckturbine 16, eine Mitteldruckturbine 17 und eine Niederdruckturbine 18 sowie eine Abgasdüse 19, die sämtlich um eine zentrale Triebwerksachse 1 angeordnet sind.The gas turbine engine 10 according to Fig. 1 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well. The engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.

Der Mitteldruckkompressor 13 und der Hochdruckkompressor 14 umfassen jeweils mehrere Stufen, von denen jede eine in Umfangsrichtung verlaufende Anordnung fester stationärer Leitschaufeln 20 aufweist, die allgemein als Statorschaufeln bezeichnet werden und die radial nach innen vom Triebwerksgehäuse 21 in einem ringförmigen Strömungskanal durch die Kompressoren 13, 14 vorstehen. Die Kompressoren weisen weiter eine Anordnung von Kompressorlaufschaufeln 22 auf, die radial nach außen von einer drehbaren Trommel oder Scheibe 26 vorstehen, die mit Naben 27 der Hochdruckturbine 16 bzw. der Mitteldruckturbine 17 gekoppelt sind.The intermediate-pressure compressor 13 and the high-pressure compressor 14 each comprise a plurality of stages, each of which has a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, extending radially inward from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude. The compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.

Die Turbinenabschnitte 16, 17, 18 weisen ähnliche Stufen auf, umfassend eine Anordnung von festen Leitschaufeln 23, die radial nach innen vom Gehäuse 21 in den ringförmigen Strömungskanal durch die Turbinen 16, 17, 18 vorstehen, und eine nachfolgende Anordnung von Turbinenschaufeln 24, die nach außen von einer drehbaren Nabe 27 vorstehen. Die Kompressortrommel oder Kompressorscheibe 26 und die darauf angeordneten Schaufeln 22 sowie die Turbinenrotornabe 27 und die darauf angeordneten Turbinenlaufschaufeln 24 drehen sich im Betrieb um die Triebwerksachse 1.The turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27. The compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.

Die Fig. 4 zeigt unterschiedliche Seitenansichten gemäß dem Stand der Technik, in denen eine Abstützung 41 der Brennkammerschindel 34 gegen die Brennkammerwand 32 dargestellt ist.The Fig. 4 shows different side views according to the prior art, in which a support 41 of the combustion chamber shingle 34 is shown against the combustion chamber wall 32.

Die Fig. 5 zeigt eine vereinfache Draufsicht auf eine erfindungsgemäße Brennkammerschindel 34. An dieser sind am Rand Randborde 51 vorgesehen, welche, wie auch aus Fig. 6 ersichtlich ist, in Form eines stegartigen Randes ausgebildet sind. In den vier Ecken der Brennkammerschindel 34 ist jeweils ein Lagerelement 40 vorgesehen, welches mit einer schlitzartigen oder taschenartigen Ausnehmung 44 versehen ist. Es ist ersichtlich, dass die Öffnungsrichtungen der Ausnehmungen 44 unterschiedlich orientiert sind, so dass eingeschobene Bolzen 38 im montierten Zustand nicht herausrutschen können, auch wenn sich die Muttern 39 lösen, da die Bolzen 38 sich in Ausnehmungen oder Bohrungen der zugeordneten Brennkammerwand 32 befinden. Im mittigen Bereich der Fig. 5 ist nochmals ein Lagerelement 40 angeordnet.The Fig. 5 shows a simplified plan view of a combustor shingle 34 according to the invention. At this edge rims 51 are provided at the edge, which, as well as from Fig. 6 can be seen, are formed in the form of a web-like edge. In the four corners of the combustion chamber shingle 34 each have a bearing element 40 is provided, which is provided with a slot-like or pocket-like recess 44. It can be seen that the opening directions of the recesses 44 are oriented differently, so that inserted bolts 38 in the assembled state can not slip out, even if the nuts 39 solve, since the bolts 38 are located in recesses or holes of the associated combustion chamber wall 32. In the central area of the Fig. 5 is again a bearing element 40 is arranged.

Die Fig. 6 zeigt in stark vereinfachter Form eine montierte Seitenansicht, analog der Darstellung der Fig. 5.The Fig. 6 shows in a greatly simplified form a mounted side view, analogous to the representation of Fig. 5 ,

Die Fig. 7 zeigt in der oberen und unteren Reihe jeweils mit einem Gewinde versehene Bolzen 38. Diese weisen jeweils eine zentrische Durchgangsausnehmung 48 in Form eines Loches auf, durch welche die Durchgangsausnehmung Kühlluft durchleiten kann. Aus den Abbildungen der Fig. 7 ist ersichtlich, dass jeder Bolzen 38 mit einem senkrecht zu seiner Mittelachse ausgerichteten Lagerbereich 47 versehen ist, welcher in eine geeignete Ausnehmung 44 des Lagerelements 40 einsteckbar ist, so wie dies in Fig. 10 gezeigt ist. Aus der Fig. 7 ergibt sich, dass unterschiedlichste Formen von Lagerbereichen 47 vorgesehen sein können, nämlich runde, quadratische, rechteckige, abgerundete oder trapezförmige. Weitere Formen sind ebenfalls möglich. Die Fig. 7 zeigt weiterhin, dass der Lagerbereich 47 mit zumindest einem Kühlluftloch 50 versehen sein kann, um den Lagerbereich 47 und damit den unteren Bereich des Bolzens 38 zu kühlen.The Fig. 7 shows in the upper and lower rows respectively threaded bolts 38. These each have a central through-hole 48 in the form of a hole through which the through-hole cooling air can pass. From the pictures of Fig. 7 It can be seen that each bolt 38 is provided with a perpendicular to its central axis aligned bearing portion 47, which is insertable into a suitable recess 44 of the bearing member 40, as shown in FIG Fig. 10 is shown. From the Fig. 7 It turns out that different forms of Storage areas 47 may be provided, namely round, square, rectangular, rounded or trapezoidal. Other shapes are also possible. The Fig. 7 shows that the storage area 47 may be provided with at least one cooling air hole 50 to cool the storage area 47 and thus the lower area of the bolt 38.

Die Fig. 8 zeigt unterschiedlichste Ausgestaltungsvarianten von Bolzen 38 mit Lagerbereichen 47, analog den Darstellungen der Fig. 7. Zusätzlich sind zugeordnete Lagerelemente 40 mit geeigneten Ausnehmungen 44 dargestellt. Die Lagerelemente 40 können ebenfalls mit Kühllöchern 52 versehen sein. Es ergibt sich, dass die Ausnehmungen 44 der Lagerelemente 40 jeweils so dimensioniert sind, dass die Bolzen 38 mit den Lagerbereichen 47 seitlich eingeschoben werden können.The Fig. 8 shows a wide variety of design variants of bolts 38 with bearing areas 47, analogous to the representations of Fig. 7 , In addition, associated bearing elements 40 are shown with suitable recesses 44. The bearing elements 40 may also be provided with cooling holes 52. It follows that the recesses 44 of the bearing elements 40 are each dimensioned so that the bolts 38 can be inserted laterally with the bearing areas 47.

Aus der Fig. 9 ergeben sich unterschiedlichste Ausgestaltungsvarianten in montiertem Zustand, wobei insbesondere ersichtlich ist, wie die Lagerbereiche 47 jeweils in die schlitzartigen oder taschenartigen Ausnehmungen 44 der Lagerelemente 40 eingeschoben sind. Dabei liegen die Lagerbereiche 47 gegen die oberen Schenkel oder Flächen der Lagerelemente 40 an, so dass sich unterhalb der Lagerbereiche 47 jeweils ein Hohlraum 49 bildet, in welchen Kühlluft einerseits durch die Durchgangsausnehmung 48 des Bolzens 38 und andererseits durch zusätzliche Kühllöcher 52 eingeführt wird. Zur Kühlluftdurchströmung dienen auch seitliche Aussparungen 53, welche auf den beiden rechts unten in Fig. 9 gezeigten Ausgestaltungsvarianten dargestellt sind.From the Fig. 9 arise in a variety of design variants in the assembled state, in particular it can be seen how the storage areas 47 are respectively inserted into the slot-like or pocket-like recesses 44 of the bearing elements 40. In this case, the bearing areas 47 rest against the upper limbs or surfaces of the bearing elements 40, so that a cavity 49 forms below the bearing areas 47, in which cooling air is introduced on the one hand through the through-hole 48 of the bolt 38 and on the other hand through additional cooling holes 52. For cooling air flow are also lateral recesses 53, which on the two right below in Fig. 9 shown embodiment variants are shown.

Die Fig. 10 zeigt in vereinfachter Schnittansicht einen montierten Zustand des erfindungsgemäßen Bolzens 38 mit seinem Lagerbereich 47 in einer Ausnehmung 44 eines Lagerelements 40. Auch hierbei ist nochmals der Hohlraum 49 verdeutlicht, welcher mit Kühlluft gefüllt wird. Weiterhin kann Kühlluft durch Effusionskühllöcher 37 strömen.The Fig. 10 shows in a simplified sectional view of an assembled state of the bolt 38 according to the invention with its storage area 47 in a recess 44 of a bearing element 40. Again, the cavity 49 is clarified, which is filled with cooling air. Furthermore, cooling air can flow through effusion cooling holes 37.

Die Fig. 11 zeigt eine weitere Ausgestaltungsvariante, bei welcher die Lagerbereiche 40 jeweils mit seitlichen Kühllöchern 52 versehen sind, die in Reihen oder in regelmäßen Anordnungen vorgesehen sind, um Kühlluft zum unteren Bereich des Bolzens 38 einzuführen.The Fig. 11 shows a further embodiment variant, in which the storage areas 40 are each provided with lateral cooling holes 52, which are provided in rows or in regular arrangements to introduce cooling air to the lower portion of the bolt 38.

Die Fig. 12 zeigt in unterschiedlichen perspektivischen Teil-Ansichten nochmals mögliche Ausgestaltungsformen der Lagerelemente 40. Dabei ergibt sich, dass diese glockenartig oder bügelartig ausgebildet sein können und jeweils einen seitlichen Schlitz oder eine seitliche Öffnung aufweisen, um den Bolzen 38 einzuführen.The Fig. 12 shows in different perspective partial views again possible embodiments of the bearing elements 40. It follows that these may be bell-like or bow-shaped and each having a lateral slot or a lateral opening to insert the bolt 38.

Bezugszeichenliste:LIST OF REFERENCE NUMBERS

11
TriebwerksachseEngine axis
1010
GasturbinentriebwerkGas turbine engine
1111
Lufteinlassair intake
1212
im Gehäuse umlaufender Fanin the housing revolving fan
1313
MitteldruckkompressorMedium pressure compressor
1414
HochdruckkompressorHigh pressure compressor
1515
Brennkammercombustion chamber
1616
HochdruckturbineHigh-pressure turbine
1717
MitteldruckturbineIntermediate pressure turbine
1818
NiederdruckturbineLow-pressure turbine
1919
Abgasdüseexhaust nozzle
2020
Leitschaufelnvanes
2121
TriebwerksgehäuseEngine casing
2222
KompressorlaufschaufelnCompressor blades
2323
Leitschaufelnvanes
2424
Turbinenschaufelnturbine blades
2626
Kompressortrommel oder -ScheibeCompressor drum or disc
2727
TurbinenrotornabeTurbinenrotornabe
2828
Auslasskonusoutlet cone
2929
Treibstoffdüsefuel nozzle
3030
BrennkammeraußengehäuseCombustion chamber outer housing
3131
BrennkammerinnengehäuseCombustion chamber inner housing
3232
Brennkammerwandcombustion chamber wall
3333
TurbinenvorleitreiheTurbinenvorleitreihe
3434
Brennkammerschindelcombustion chamber tile
3535
ZumischlochZumischloch
3636
Zuströmrichtunginflow
3737
EffusionskühllochEffusionskühlloch
3838
Bolzenbolt
3939
Muttermother
4040
Lagerelementbearing element
4141
Abstützungsupport
4343
Gewindethread
4444
Ausnehmungrecess
4545
Schlitzslot
4646
Bolzenachsepin axis
4747
Lagerelementbearing element
4848
Durchgangsausnehmungthrough recess
4949
Hohlraumcavity
5050
Kühllochcooling hole
5151
Randbord / SchindelseitenbordRandbord / shingle side board
5252
Kühllochcooling hole
5353
Aussparungrecess

Claims (9)

  1. Combustion chamber tile of a gas turbine having a bolt (38) for mounting the combustion chamber tile (34) on a combustion chamber wall (32), with the combustion chamber tile (34) being designed substantially plate-like and having on one side at least one mounting element (40), on which the bolt (38), which is provided as a separate component, is positively anchored, where the bolt (38) is provided at its end area with a mounting section (47) arranged at right angles to the bolt axis (46), said mounting section (47) being arranged in a recess (44) of the mounting element (40), where the recess (44) of the mounting element (40) is dimensioned larger than the mounting section (47) of the bolt (38) in order to provide a cavity (49) between the surface of the combustion chamber tile (34) and the mounting section (37) of the bolt (38), characterized in that the bolt (38) has a continuous centric recess (48) and the mounting element (40) is provided with effusion cooling holes (37).
  2. Combustion chamber tile in accordance with Claim 1, characterized in that the mounting element (40) is provided with cooling holes (52).
  3. Combustion chamber tile in accordance with one of the Claims 1 or 2, characterized in that the recess (44) of the mounting element (40) is opened on its side.
  4. Combustion chamber tile in accordance with one of the Claims 1 to 3, characterized in that the mounting element (40) is designed strap-like or bell-like.
  5. Combustion chamber tile in accordance with one of the Claims 1 to 4, characterized in that the bolt (38) with the mounting section (47) can be inserted into the recess (44) in a direction perpendicular to the bolt axis (46) of the bolt (38).
  6. Combustion chamber tile in accordance with one of the Claims 1 to 5, characterized in that several mounting elements (40) are provided on the combustion chamber tile (34), the recesses (44) of which are designed open towards different directions.
  7. Combustion chamber tile in accordance with one of the Claims 1 to 6, characterized in that the mounting section (47) is designed plate-like or bar-like.
  8. Combustion chamber tile in accordance with one of the Claims 1 to 7, characterized in that the mounting element (40) is integrated into an edge board (51) of the combustion chamber tile (34).
  9. Combustion chamber tile in accordance with one of the Claims 1 to 8, characterized in that the bolt (38) is designed as a threaded bolt.
EP15158450.5A 2014-03-11 2015-03-10 Combustion chamber shingle of a gas turbine Not-in-force EP2918915B1 (en)

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US20150260400A1 (en) 2015-09-17
EP2918915A1 (en) 2015-09-16

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