Blade for a gas turbine

Abstract

Disclosed is a blade for a gas turbine, in particular for an aircraft engine, wherein the blade comprises at least one internal and/or external supporting structure of a metallic and/or intermetallic material. Also disclosed are a blade cluster having at least one such blade for a gas turbine, a method for producing such a blade cluster and a gas turbine.

1 - 19 . (canceled) 
     
     
         20 . A blade for a gas turbine, wherein the blade comprises at least one internal and/or external supporting structure of a metallic and/or intermetallic material. 
     
     
         21 . The blade of  claim 20 , wherein the supporting structure is surrounded, at least in certain regions, by a casing of at least one ceramic fiber composite material. 
     
     
         22 . The blade of  claim 20 , wherein the supporting structure is, at least in certain regions, solid and/or pierced and/or grid-like and/or porous. 
     
     
         23 . The blade of  claim 21 , wherein the supporting structure bears, at least in certain regions, directly on an inner side of the casing and/or at least one cavity is arranged between the supporting structure and the casing. 
     
     
         24 . The blade of  claim 21 , wherein the supporting structure is supported by at least one supporting element on an inner wall of the casing and/or the casing is slotted onto the supporting structure. 
     
     
         25 . The blade of  claim 21 , wherein the casing forms
 a substantially convex suction side and/or   a substantially concave pressure side and/or   a leading edge connecting the suction side and the pressure side and/or   a trailing edge connecting the suction side and the pressure side of a blade airfoil of the blade.   
     
     
         26 . The blade of  claim 21 , wherein the casing comprises at least one end region which projects away from the supporting structure so as to cover, at least in certain regions, a component of the gas turbine and/or so as to bind to an adjoining casing of a further blade and/or so as to line, at least in certain regions, a flow duct of the gas turbine. 
     
     
         27 . The blade of  claim 20 , wherein the blade is connected to a hub and/or is formed as a rotor blade and/or as a guide blade and/or is present as a blade cluster together with at least one further blade. 
     
     
         28 . A blade cluster for a gas turbine, wherein the blade cluster comprises at least two blades connected to one another, at least one of the blades being the blade of  claim 20 , and/or at least one of the blades of the blade cluster being formed at least partially from at least one ceramic composite material and at least one other blade of the blade cluster is formed from a metallic and/or intermetallic material and is substantially free from ceramic composite material. 
     
     
         29 . The blade cluster of  claim 28 , wherein the at least two blades are connected to an inner platform and/or to an outer platform. 
     
     
         30 . The blade cluster of  claim 28 , wherein the blade cluster comprises an odd number of blades and/or comprises in alternation one blade which consists entirely of a metallic and/or intermetallic material and one blade that comprises at least one internal and/or external supporting structure of a metallic and/or intermetallic material. 
     
     
         31 . The blade cluster of  claim 28 , wherein the supporting structure of a blade is surrounded, at least in certain regions, by a casing of at least one ceramic fiber composite material and mutually adjoining casings of at least two blades are connected to each other in a form-fitting and/or material-bonded manner. 
     
     
         32 . The blade cluster of  claim 28 , wherein the cluster further comprises a covering of the inner and/or outer shroud or platform and/or a housing covering and/or a lining for a flow duct of at least one ceramic fiber composite material. 
     
     
         33 . The blade cluster of  claim 32 , wherein a hub covering and/or the housing covering and/or the lining of the flow duct is formed, at least in certain regions, by a casing of at least one blade. 
     
     
         34 . A method for producing a blade cluster for a gas turbine in which at least two blades are connected to one another, wherein the method comprises connecting at least one metallic and/or intermetallic internal and/or external supporting structure of at least one blade to an inner platform of the blade cluster and to an outer platform of the blade cluster and/or comprises at least partially forming at least one of the blades of the blade cluster from at least one ceramic composite material and forming at least one other blade of the blade cluster from a metallic and/or intermetallic material that is substantially free from ceramic composite material. 
     
     
         35 . The method of  claim 34 , wherein the supporting structure is, at least in certain regions, sheathed with a casing made from at least one ceramic fiber composite material. 
     
     
         36 . The method of  claim 35 , wherein
 the inner platform and at least one supporting structure are first produced in a composite assembly, after which the casing is slotted onto the supporting structure and the supporting structure is connected to the outer platform; and/or   the outer platform and at least one supporting structure are first produced in a composite assembly, after which the casing is slotted onto the supporting structure and the supporting structure is connected to the inner platform; and/or   the inner platform, the outer platform and at least one supporting structure are first produced independently from one another, are connected to one another and the supporting structure is subsequently provided with the casing.   
     
     
         37 . The method of  claim 35 , wherein the casing of the at least one blade is connected to the inner platform and/or to the outer platform via a plug connection and/or a clip connection. 
     
     
         38 . A gas turbine, wherein the gas turbine comprises the blade of  claim 20 . 
     
     
         39 . A gas turbine, wherein the gas turbine comprises the blade cluster of  claim 28 .