Gas turbine engine component

Abstract

Described is a gas turbine engine component ( 100 ), comprising a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises multiple separate parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; wherein the assembled insert includes at least one retention part, the retention part engaging with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.

1 . A gas turbine engine component, comprising
 a shell having an internal cavity for receiving a multi-part insert;   a multi-part insert located within the cavity, wherein the multi-part insert comprises multiple separate parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert;   wherein the assembled insert includes at least one retention part, the retention part engaging with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.   
     
     
         2 . A gas turbine component as claimed in  claim 1 , wherein the retention part is configured to provide an interference fit with one or more other of the insert parts and or a wall of the cavity. 
     
     
         3 . A gas turbine component as claimed in  claim 2 , wherein the retention part provides a resilient bias which acts to urge the retention part or another insert part against one or more walls of the shell. 
     
     
         4 . A gas turbine component as claimed in  claim 3 , wherein the retention part includes at least two members connected by a hinge portion, wherein the hinge portion provides the biasing force. 
     
     
         5 . A gas turbine component as claimed in  claim 1 , wherein the cavity includes an insertion portion into which the insert parts are inserted, and a receiving portion in which at least one of the insert parts is located when the insert is assembled. 
     
     
         6 . A gas turbine engine component as claimed in  claim 1 , wherein the insert includes:
 a first wall containing first impingement holes which, in use, jet cooling air onto a first region of the inner surface of the shell;   a second wall containing second impingement holes which, in use, jet cooling air onto a second region of the inner surface of the shell; and   a fluid pathway formed between the two walls, the pathway recycling the cooling air jetted onto the first region to the inlets of the second impingement holes for jetting onto the second region.   
     
     
         7 . A gas turbine engine component according to  claim 1 , wherein the insert includes heat transfer formations at the first and second regions which support the insert within the shell and which guide the cooling air around the inner surface of the shell. 
     
     
         8 . A gas turbine engine component according to  claim 1 , wherein the shell includes exterior film cooling holes fed by cooling air that has been jetted onto the second region of the inner surface. 
     
     
         9 . A gas turbine engine component according to  claim 1 , wherein the insert includes trip strip formations which lie along the inner surface of the shell. 
     
     
         10 . A gas turbine engine component according to  claim 1  which is an aerofoil and the first and second regions are located at the suction side of the aerofoil. 
     
     
         11 . A gas turbine engine aerofoil according to  claim 7  wherein the insert defines one or more flow channels which, in use, collect cooling air from one or both ends of the aerofoil and distribute the cooling air through the shell, at least a portion of the cooling air being distributed to the inlets of the first impingement holes for jetting onto the first region. 
     
     
         12 . A method of providing an assembled multi-part insert within a shell of a gas turbine component according to  claim 1 , comprising,
 providing the shell;   providing a plurality of insert parts which are configured to be assembled in an abutting relation with one another within the cavity to provide the multi-part insert;   wherein the assembled insert includes at least one retention part which engages with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.   
     
     
         13 . A method as claimed in  claim 12 , wherein at least one of the insert parts is a retention part which is oversized in relation to corresponding portion of the cavity in which it is located in use, the oversize being sufficient to require elastic deformation of part during insertion into the cavity to provide the biasing force. 
     
     
         14 . A method as claimed in  claim 13 , wherein the insert part has at least two members connected by a hinge portion, the method further comprising deforming the insert part so as to bring the two members closer together such that the hinge portion is elastically deformed prior to insertion. 
     
     
         15 . A method as claimed in  claim 12 , wherein, prior to insertion of the retention part, the retention part is deformed so as to plastically deform a portion thereof.