Joining element and method for the production of such a joining element as well as an integrally bladed rotor

Abstract

A joining element, for example, an adapter, for connecting a rotor blade to a rotor disc or a rotor ring, or a rotor blade per se of an aircraft engine is disclosed. The joining element has a base body and a joining surface, with the joining surface formed by a fusion weldable coating made of a compressed powder that is connected in a positive fit to a contour of the base body. A method for the production of such a joining element, as well as an integrally bladed rotor, is also disclosed.

1 . A joining element, comprising:
 a base body, wherein the base body includes a contour; and   a joining surface, wherein the joining surface is a fusion weldable coating of a compressed powder;   wherein the joining surface is connected in a positive fit to the contour of the base body.   
     
     
         2 . The joining element according to  claim 1 , wherein the contour extends over a large area of the base body. 
     
     
         3 . The joining element according to  claim 1 , wherein the coating has a thickness that corresponds to a height of the contour. 
     
     
         4 . The joining element according to  claim 1 , wherein the contour has a fractal structure. 
     
     
         5 . The joining element according to  claim 1  in combination with a rotor blade and a rotor disc, wherein the joining element is arranged between the rotor blade and the rotor disc. 
     
     
         6 . The joining element according to  claim 1 , wherein the joining element is a portion of a rotor blade of a jet engine. 
     
     
         7 . A method for production of a joining element, comprising the steps of:
 providing a base body;   providing a contour to the base body;   surrounding the base body with a frame, at least in a region of the contour, to form a powder basin;   pouring a metal powder into the powder basin at least until the contour is covered by the metal powder;   compressing the metal powder under pressure and temperature to form a coating that is connected to the contour in a form-fitting manner; and   removing the frame from the base body.   
     
     
         8 . The method according to  claim 7 , wherein the step of providing the contour to the base body includes mechanically forming the contour. 
     
     
         9 . The method according to  claim 7 , wherein the step of providing the contour to the base body includes thermally and/or electrochemically forming the contour. 
     
     
         10 . The method according to  claim 7 , wherein the step of providing the contour to the base body includes producing the contour in a generative manner. 
     
     
         11 . The method according to  claim 7 , wherein the step of compressing is hot isostatic pressing. 
     
     
         12 . An integrally bladed rotor of a jet engine, comprising:
 a plurality of blades; and   a rotor disc;   wherein each of the plurality of blades are connected to an outer circumference of the rotor disc by a respective joining element according to  claim 1  with the base body disposed on a side of the blade and the coating disposed on a side of the rotor disc.