Method of producing a component

Abstract

The present technology relates to a method for producing a component, especially a gas turbine component, with at least the following steps: a) production of a component with several component surfaces, in which at least one transitional area between two component surfaces has a transition radius that is greater than 0.05 mm and less than 0.30 mm; b) strengthening of the component, at least on the transitional area or each transitional area, by ultrasonic shot peening.

1 . A method for producing a component comprising the following steps:
 a) Producing a component having two or more component surfaces, in which at least one transitional area between two component surfaces has a transition radius that is greater than about 0.05 mm and less than about 0.30 mm, and   b) Strengthening the component in at least one transitional area or each transitional area by ultrasonic shot peening.   
     
     
         2 . The method according to  claim 1 , wherein the method is used to produce a gas turbine component. 
     
     
         3 . The method according to  claim 1 , wherein the component is produced by forging, by fine casting, or by powder metallurgical injection molding. 
     
     
         4 . The method according to  claim 1 , wherein the component produced is a gas turbine blade having a transitional area between a suction side surface and a pressure side surface on a blade trailing edge of a blade body that is greater than about 0.05 mm and less than about 0.30 mm. 
     
     
         5 . The method according to  claim 4 , wherein the gas turbine blade is a rotor blade. 
     
     
         6 . The method according to  claim 3 , wherein the component produced is a gas turbine blade having a transitional area between a suction side surface and a pressure side surface on a blade trailing edge of a blade body that is greater than about 0.05 mm and less than about 0.30 mm. 
     
     
         7 . The method according to  claim 5 , wherein the gas turbine blade is a rotor blade. 
     
     
         8 . The method according to  claim 1 , wherein the component produced is a gas turbine blade having at least on one blade foot having a transitional area between a dendritic or dovetail profiled surface, running in the longitudinal direction of the gas turbine blade, and an end surface, running in the transverse direction of the gas turbine blade, with a transition radius that is greater than about 0.05 mm and less than about 0.30 mm. 
     
     
         9 . The method according to  claim 5 , wherein the gas turbine glad is a rotor blade. 
     
     
         10 . A method according to  claim 1 , wherein the ultrasonic shot peening step is carried out with precision balls having a smooth surface. 
     
     
         11 . A method according to  claim 8 , wherein the ultrasonic shot peening step is carried out with precision balls having a smooth surface. 
     
     
         12 . A method according to  claim 1 , further comprising the optional step of rounding the transitional area by a brush-like tool before the component is strengthened by the ultrasonic shot peening. 
     
     
         13 . A method according to  claim 5 , further comprising the optional step of rounding the transitional area by a brush-like tool before the component is strengthened by the ultrasonic shot peening.