| 摘要 |
A gas turbine engine component is described which, comprises: a shell (1000) having an internal cavity (1001, 1003) for receiving a multi-part insert (1010, 1020); 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the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.. Corresponding method of forming a gas turbine engine component. |
