| 摘要 |
PROBLEM TO BE SOLVED: To provide a cooling rotor blade capable of suppressing pressure drop in an aerofoil to the minimum extent. SOLUTION: An internal passage structure of the rotor blade includes a first radial passage 48, a second radial passage 50, a rib 53 provided between these passages to separate these passages from each other, a plurality of crossing holes 52 provided in the rib, and a plurality of trip strips 58. The plurality of trip strips 58 are attached to an internal surface of either or both of a positive pressure side wall and a negative pressure side wall and are provided in the first radial passage 48 at an angleαinclined to the direction 60 of cooling air stream in the first radial passage. Each of the plurality of trip strips 58 is positioned to collect toward the rib 53. A rib end part 62 of the plurality of trip strips 58 in at least a part is provided between a pair of adjacent crossing holes 52. COPYRIGHT: (C)2006,JPO&NCIPI
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