| 摘要 |
A process for investment casting of an engine part (100), e.g. a high-performance turbine blade for an aircraft engine, having at least one internal cast wall (120), the wall (120) being defined during the casting thereof by a pair of core members (110a, 110b) having respective ones of a pair of opposed faces, major portions of the said opposed faces being spaced from each other by a first distance (W) corresponding to a predetermined minimum thickness (W) of a major portion of the resulting cast wall (120),
a face of a first core member (110a) of the pair which faces a second core member (110b) of the pair being provided with one or more protrusions (130) thereon, and a face of the second core member (110b) of the pair which faces the first core member (110a) of the pair being provided with one or more respective open recesses (150) therein, the or each respective protrusion (130) on the first core member (110a) facing the or a respective one of the said open recesses (150) in the second core member(110b),
wherein during at least part of the casting procedure the first (110a) and second (110b) core members are maintained in a spatial position relative to each other such that:
the said major portions of the opposed faces of the first and second core members (110a, 110b) assume a mutual spacing which substantially equals the said first distance (W) corresponding to the predetermined minimum thickness (W) of the major portion of the resulting cast wall (120); and
at least a head portion of the or each protrusion (130) on the first core member (110a) is located within the or a respective open recess (150) in the second core member (110b), such that the or each respective protrusion (130) and the or each respective open recess (150) define therebetween a respective minor portion of the resulting cast wall (120) which is laterally displaced from the major portion of the resulting cast wall (120). |
