| 摘要 |
The invention relates to a method of making a cast metal blade for a gas turbine engine with a closure for an internal cooling passage, and to the blade made by this method. According to the method a composite casting core is formed from two materials, the first of which (17) defines a cavity 31 within the metal blade Fig. 5 while the second of which (15) forms a closure for this cavity. The core is used in the conventional lost-wax coating process to provide a shell mould 29, Fig. 4 but only the part (17) of the core made of the first material is leached out after casting. This produces a cavity (31) closed by the piece (15) of the core left in situ. <IMAGE>
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