Method for connecting at least one turbine blade to a turbine disk or a turbine ring

Abstract

The invention relates to a method for connecting at least one turbine blade ( 10 ) to a turbine disk ( 18 ) or a turbine ring for a turbine stage of a turbomachine, particularly a thermal gas turbine, wherein first a connecting body ( 16 ) is formed on the at least one turbine blade ( 10 ) by means of a cold gas spraying method, and the connecting body ( 16 ) is subsequently connected to turbine disk ( 18 ) or to the turbine ring by means of a fusion-welding method. The invention further relates to a turbine stage for a turbine of a turbomachine as well as a turbomachine having a turbine.

1 . A method for connecting at least one turbine blade ( 10 ) that cannot be fusion welded or can be fusion welded only with great difficulty to a turbine disk ( 18 ) that can be fusion welded or a turbine ring that can be fusion welded for a turbine stage of a turbomachine, particularly a thermal gas turbine, in which a geometrically defined connecting body ( 16 ) is first formed on the at least one turbine blade ( 10 ) by means of a cold gas spraying method and the connecting body ( 16 ) is subsequently connected to turbine disk ( 18 ) or to the turbine ring by means of a fusion-welding method, wherein connecting body ( 16 ) is formed in the region of a blade foot ( 14 ) of turbine blade ( 10 ) and/or as a blade foot ( 14 ) of turbine blade ( 10 ) as a function of the geometry of turbine blade ( 10 ) and/or of turbine disk ( 18 ) or of the turbine ring and is precision-machined prior to the fusion-welding method. 
     
     
         2 . The method according to  claim 1 ,
 further characterized in that   an electron-beam welding method and/or a laser welding method and/or an inductive high-frequency welding method and/or an inductive low-frequency welding method is used.   
     
     
         3 . The method according to  claim 1 ,
 further characterized in that   several turbine blades ( 10 ) are connected to turbine disk ( 18 ) or to the turbine ring via respective connecting bodies ( 16 ).   
     
     
         4 . A turbine stage for a turbine of a turbomachine, particularly a thermal gas turbine having a turbine disk ( 18 ) or a turbine ring, which is connected to at least one turbine blade ( 10 ) at least indirectly,
 is hereby characterized in that   the at least one turbine blade ( 10 ) is connected to turbine disk ( 18 ) or to the turbine ring via a geometrically defined connecting body ( 16 ) formed on turbine blade ( 10 ) by means of a cold gas spraying method, wherein connecting body ( 16 ) is formed in the region of a blade foot ( 14 ) of turbine blade ( 10 ) and/or as a blade foot ( 14 ) of turbine blade ( 10 ) as a function of the geometry of turbine blade ( 10 ) and/or of turbine disk ( 18 ) or of the turbine ring, is precision-machined for its connection to turbine disk ( 18 ) or to the turbine ring and is connected to turbine disk ( 18 ) or to the turbine ring by means of a fusion-welding method.   
     
     
         5 . The turbine stage according to  claim 4 ,
 further characterized in that   turbine disk ( 18 ) or the turbine ring and/or turbine blade ( 10 ) is manufactured from a nickel base alloy and/or a cobalt base alloy and/or a titanium aluminide and/or a metal-matrix composite material and/or a ceramic-matrix composite material.   
     
     
         6 . A turbomachine, particularly a thermal gas turbine, with a turbine that comprises a turbine stage having a turbine disk ( 18 ) or a turbine ring that is connected to at least one turbine blade ( 10 ) at least indirectly,
 is hereby characterized in that   turbine disk ( 18 ) or the turbine ring and the at least one turbine blade ( 10 ) of the turbine stage are connected to one another by means of a method according to  claim 1  and/or that the turbine stage is formed according to one of  claims 4 .