| 摘要 |
A method of manufacturing a fan blade ( 26 ) for a gas turbine engine by powder metallurgy comprises the steps of forming a container ( 52 ) and placing at least one metal insert ( 52 ) at a predetermined position within the container ( 52 ) and filling the container ( 52 ) with metal powder ( 60 ). The at least one metal insert ( 62 ) has a predetermined pattern of stop off material ( 68,70 ) on at least one surface of the metal insert ( 64,66 ). The container ( 52 ) is evacuated and then sealed. The container ( 52 ) is hot pressed to consolidate the metal powder ( 60 ) into a consolidated metal powder preform ( 72 ). The container ( 52 ) is removed from the consolidated metal powder preform ( 72 ). The consolidated metal powder preform ( 72 ) is heated and a fluid is supplied to the predetermined pattern of stop off material ( 68,70 ) to hot form at least a portion of the consolidated metal powder preform ( 72 ) to form the hollow metal fan blade ( 26 ).
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