Generatively produced turbine blade and device and method for producing same

Abstract

The present invention relates to a method for producing gas turbine components, in particular aircraft turbine components, preferably low-pressure turbine blades, from a powder which is sintered selectively in layers by locally limited introduction of radiant energy, wherein the sintering is carried out in a closed first housing ( 2 ), so that a defined atmosphere can be set, wherein the powder or at least a part of the powder is generated in the same first housing ( 2 ) or in a second housing connected to the first housing in a gas-tight manner. The invention further relates to a corresponding apparatus and to a gas turbine blade produced thereby.

1 .- 10 . (canceled) 
     
     
         11 . A method for producing a gas turbine component, wherein the method comprises producing the component from a powder which is sintered selectively in layers by locally limited introduction of radiant energy, and wherein the sintering is carried out in a closed, first housing so that a defined atmosphere can be set, and the powder or at least a part of the powder is produced in the same first housing or in a second housing connected to the first housing in a gas-tight manner. 
     
     
         12 . The method of  claim 11 , wherein the sintering is effected by a laser beam or an electron beam. 
     
     
         13 . The method of  claim 11 , wherein a plurality of radiation beams for introducing radiant energy are used at the same time for sintering. 
     
     
         14 . The method of  claim 11 , wherein a substantially oxygen-free atmosphere or a vacuum is set. 
     
     
         15 . The method of  claim 11 , wherein a metallic powder is used. 
     
     
         16 . The method of  claim 11 , wherein a powder of TiAl alloy or a powder for producing a TiAl alloy is used. 
     
     
         17 . The method of  claim 11 , wherein the powder is mechanically alloyed and/or a particle size distribution thereof is set. 
     
     
         18 . The method of  claim 11 , wherein differently alloyed powder and/or powder set in terms of powder size is sintered in different regions of the component. 
     
     
         19 . The method of  claim 11 , wherein the powder is produced by atomization. 
     
     
         20 . An apparatus for producing a gas turbine component, wherein the apparatus comprises a first housing in which there are arranged (i) a reservoir for a powder bed and (ii) a radiation source for generating at least one radiation beam for introducing radiant energy into the powder bed and (iii) an arrangement for applying thin powder layers to the powder bed, and wherein a device for producing powder is also arranged in the first housing or is arranged in a second housing that is connected to the first housing in a gas-tight manner. 
     
     
         21 . A gas turbine blade, wherein the blade is formed as a hollow blade with an internal supporting structure. 
     
     
         22 . The turbine blade of  claim 21 , wherein the blade is a low-pressure turbine blade made of a TiAl material. 
     
     
         23 . The turbine blade of  claim 21 , wherein the blade is made by a method which comprises producing the blade from a powder which is sintered selectively in layers by locally limited introduction of radiant energy, and wherein the sintering is carried out in a closed, first housing so that a defined atmosphere can be set, and the powder or at least a part of the powder is produced in the same first housing or in a second housing connected to the first housing in a gas-tight manner. 
     
     
         24 . The turbine blade of  claim 23 , wherein the blade is a low-pressure turbine blade made of a TiAl material. 
     
     
         25 . The blade of  claim 21 , wherein the blade exhibits at least one of a fine-grained microstructure in which 95% of grains have a grain size of less than 100 nm, a locally differing alloy composition, and a locally differing grain size distribution. 
     
     
         26 . The blade of  claim 22 , wherein the blade exhibits at least one of a fine-grained microstructure in which 95% of grains have a grain size of less than 100 nm, a locally differing alloy composition, and a locally differing grain size distribution. 
     
     
         27 . The blade of  claim 23 , wherein the blade exhibits at least one of a fine-grained microstructure in which 95% of grains have a grain size of less than 100 nm, a locally differing alloy composition, and a locally differing grain size distribution. 
     
     
         28 . The The blade of  claim 24 , wherein the blade exhibits at least one of a fine-grained microstructure in which 95% of grains have a grain size of less than 100 nm, a locally differing alloy composition, and a locally differing grain size distribution.