Gas turbine engine component

Abstract

A gas turbine engine component is described which ( 100 ), comprises: 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 separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.

1 . 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 separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert;   an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.   
     
     
         2 . 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. 
     
     
         3 . A gas turbine component as claimed in  claim 2 , wherein the receiving portion is at least partially obscured by a wall or an internal protuberant feature of the shell when viewed from the insertion aperture. 
     
     
         4 . A gas turbine component as claimed in  claim 3 , wherein the obstruction of the receiving portion is caused by a twist along the length of the cavity. 
     
     
         5 . A gas turbine component as claimed in  claim 3 , wherein the cavity includes a widened portion along the length thereof and the receiving portion may be located within the widened portion of the cavity. 
     
     
         6 . A gas turbine engine as claimed in  claim 1  where the assembled insert includes at least one retention part, wherein the retention part acts to engage with a portion of the cavity and the at least one other insert part so as to retain the assembled insert within the cavity. 
     
     
         7 . A gas turbine component as claimed in  claim 1 , wherein the retention part provides a resilient bias which acts to urge the retention part and or another insert part against one or more walls of the shell. 
     
     
         8 . A gas turbine component as claimed in  claim 1 , wherein the retention part may be oversized relative to the size required when in situ such that inserting the retention part into the cavity requires a deformation of the part and a resulting stressing to provide the bias. 
     
     
         9 . A gas turbine component as claimed in  claim 1 , wherein at least one insert piece is made by additive layer manufacturing; and
 wherein the insert includes formations which support the insert within the shell and guide the cooling air around the inner surface of the shell.   
     
     
         10 . A gas turbine engine component as claimed in  claim 1 , wherein the shell is a ceramic matrix composite shell. 
     
     
         11 . A gas turbine engine component as claimed in  claim 1 , wherein the formations include projections. 
     
     
         12 . A gas turbine engine component according to  claim 1 , wherein at least one of the insert parts predominantly includes trip strip formations which lie along the inner surface of the shell when the insert is assembled. 
     
     
         13 . A gas turbine engine component as claimed in  claim 1 , wherein the shell forms an aerofoil and includes a wall which divides the shell into a front cavity at a leading edge region of the component and a rear cavity at a trailing edge region of the component; and wherein the multi-part insert is located in the front cavity or a rear insert located in the rear cavity. 
     
     
         14 . A gas turbine engine component as claimed in  claim 13 , wherein the divider wall includes apertures which provide fluid communication between the front and rear cavity, and at least one part of the multiple insert parts includes a sealing plate to restrict or prevent the flow of cooling air across the divider wall. 
     
     
         15 . A method of forming the gas turbine engine component according to  claim 1 , the method including the steps of:
 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.