Aerofoil joint recess

Abstract

An aerofoil configured to be connected to a second component, the aerofoil comprising a first face including a bi-cast groove for joining the aerofoil to the second component by bi-casting; a second face connected to a main body of the aerofoil; an angled sealing face between the first and second face, the angled sealing face being angled with respect to the second face and configured to provide a sealing interface between the first face and the second face; and a concave face forming a recessed surface at the intersection of the sealing face and the second face.

We claim: 
     
         1 . An aerofoil configured to be connected to a second component, the aerofoil comprising:
 a first face including a bi-cast groove for joining the aerofoil to the second component by bi-casting;   a second face connected to a gas path surface of the aerofoil;   an angled sealing face between the first and second face, the angled sealing face being angled with respect to the second face and configured to provide a sealing interface between the first face and the second face; and   a concave face forming a recessed surface at the intersection of the sealing face and the second face.   
     
     
         2 . The aerofoil according to  claim 1 , further comprising a through-hole, wherein one end of the through-hole opens at the concave face. 
     
     
         3 . The aerofoil according to  claim 1 , wherein the second face is coated with a thermal barrier coating. 
     
     
         4 . The aerofoil according to  claim 1 , wherein the angle between the angled sealing face and the second face is an obtuse angle. 
     
     
         5 . The aerofoil according to  claim 1 , wherein the angle between the angled sealing face and the second face is a right angle. 
     
     
         6 . The aerofoil according to  claim 1 , wherein the first face is at the root of the aerofoil. 
     
     
         7 . The aerofoil according to  claim 1 , wherein the first face is at the tip of the aerofoil. 
     
     
         8 . The aerofoil according to  claim 1 , wherein the aerofoil is a stator vane. 
     
     
         9 . The aerofoil according to  claim 1 , wherein the aerofoil is a rotor blade. 
     
     
         10 . The aerofoil according to  claim 1 , wherein the cross-section of the recessed surface is a continuous curve between the angled sealing face and the second face. 
     
     
         11 . The aerofoil according to  claim 1 , wherein the cross-section of the recessed surface includes a discontinuity. 
     
     
         12 . An assembly comprising the aerofoil according to  claim 1 , and a second component, wherein the aerofoil and second component are joined by bi-cast metal filling the bi-cast groove of the aerofoil and a corresponding bi-cast groove on the second component. 
     
     
         13 . A method of manufacturing an aerofoil comprising:
 providing an aerofoil with a first face including a bi-cast groove; a second face connected to a main body of the aerofoil; and an angled sealing face between the first and second face, the angled sealing face being angled with respect to the second face and configured to seal the bi-cast groove; and   removing material at the intersection of the angled sealing face and the second face to form a concave face, thus forming a recessed surface.   
     
     
         14 . A method of manufacturing an assembly comprising
 manufacturing an aerofoil according to the method of  claim 13 ; and   joining the aerofoil to a second component by filling the bi-cast groove of the aerofoil and a corresponding bi-cast groove on the second component with bi-cast metal.