Blade of a turbomachine made of different materials and method for the production thereof

Abstract

The present invention relates to a blade for a turbomachine, in particular for an aircraft engine, which comprises a blade root ( 2 ) for arranging the blade ( 1 ) in the turbomachine and a main blade part ( 3 ) for interaction with a fluid flowing through the turbomachine, the blade root and the main blade part being formed from different materials and the main blade part being formed from a metal-intermetallic composite material. The metal matrix, in which intermetallic phases are incorporated for forming the metal-intermetallic composite material, is formed by a molybdenum alloy. The invention also relates to a corresponding method for producing such a blade.

What is claimed is: 
     
         1 . A blade for a turbomachine, wherein the blade comprises a blade root for arranging the blade in the turbomachine and a main blade part for interaction with a fluid flowing through the turbomachine, the blade root and the main blade part being formed from different materials and the main blade part being formed from a metal-intermetallic composite (MIC) material wherein a metal matrix, in which intermetallic phases are incorporated for forming the MIC material, is formed by a molybdenum alloy. 
     
     
         2 . The blade of  claim 1 , wherein the blade root is formed from a MIC material in which the metal matrix, in which intermetallic phases are incorporated for forming the MIC material, is formed from a molybdenum alloy, a proportion of intermetallic phases being lower in the MIC material compared to the MIC material of the main blade part. 
     
     
         3 . The blade of  claim 1 , wherein the blade root is formed from an alloy which is selected from nickel alloys, Mo alloys, and Co alloys. 
     
     
         4 . The blade of  claim 1 , wherein the intermetallic phases are or comprise silicides. 
     
     
         5 . The blade of  claim 4 , wherein the silicides comprise one or both of (Mo, Ti) 5 Si 3  and (Mo, Ti) 5 SiB 2 . 
     
     
         6 . The blade of  claim 4 , wherein the silicides comprise one or more of Mo 5 Si 3  Mo 5 SiB 2  and Mo 3 Si. 
     
     
         7 . The blade of  claim 2 , wherein the intermetallic phases are or comprise silicides. 
     
     
         8 . The blade of  claim 1 , wherein the MIC material of the main blade part comprises a silicide proportion of higher than or equal to 50% by volume. 
     
     
         9 . The blade of  claim 2 , wherein the MIC material of the blade root has a silicide proportion of lower than 50% by volume. 
     
     
         10 . The blade of  claim 1 , wherein in addition to molybdenum and silicon, the molybdenum alloy forming the metal matrix of the MIC material of the main blade part comprises one or more of boron, titanium, zirconium, niobium, tungsten, iron, yttrium. 
     
     
         11 . The blade of  claim 10 , wherein the molybdenum alloy comprises from 9 at % to 15 at. % silicon, from 5 at % to 12 at. % boron, and from 18 at % to 32 at. % titanium. 
     
     
         12 . The blade of  claim 2 , wherein in addition to molybdenum and silicon, the molybdenum alloy forming the metal matrix of the MIC material of the blade root comprises one or more of boron, titanium, zirconium, niobium, tungsten, iron, yttrium. 
     
     
         13 . The blade of  claim 1 , wherein a transition from the material of the blade root to the material of the main blade part is graded with a continuously running transition. 
     
     
         14 . The blade of  claim 1 , wherein a transition from the material of the blade root to the material of the main blade part is stepped with one or more sudden changes. 
     
     
         15 . A method for producing a blade for a turbomachine, wherein the method comprises providing a first material for a blade root and a second material for a main blade part, the second material being different from the first material, and wherein the first material and the second material are provided in the form of a powder or a powder mixture or as solid bodies, and the blade is produced by (i) joining at least two solid bodies or (ii) joining a solid body to a powder or a powder mixture or (iii) joining at least two different powders or powder mixtures. 
     
     
         16 . The method of  claim 15 , wherein the solid bodies are joined by at least one of welding, friction welding, diffusion welding, laser beam welding, electron beam welding and inductive pressure welding. 
     
     
         17 . The method as claimed in  claim 15 , wherein a powder or a powder mixture is joined to a solid body by a generative production method for a layered application of powder particles or by providing the powder particles in a mold or capsule on the solid body and by compaction and connection of the powder particles to one another and to the solid body by at least one of hot isostatic pressing, cold isostatic pressing, hot pressing, sintering, pressure sintering and reaction sintering. 
     
     
         18 . The method as claimed in  claim 15 , wherein at least two different powders or powder mixtures are joined by a generative production method for a layered connection of powder particles or by providing the powder particles in a mold or capsule and by compaction and connection of the powder particles to one another by at least one of hot isostatic pressing, cold isostatic pressing, hot pressing, sintering, pressure sintering and reaction sintering. 
     
     
         19 . An turbomachine which comprises the blade of  claim 1 . 
     
     
         20 . The turbomachine of  claim 19 , which is an aircraft engine.