| 摘要 |
A turbine blade ( 20 ) has cooling air passageways ( 30 ) and ( 30 a, 30 b, 30 c.) through the leading edge wall portion ( 24 ) which are positionally arranged so as to intersect each other within the wall thickness so as to transmit mechanical stresses into the thicker, non-perforated material of the blade aerofoil ( 22 ). Further passageways near the blade root portion ( 42 ) do not intersect, the reduced cooling in that area causes expansion and stress absorption.
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