| 摘要 |
PROBLEM TO BE SOLVED: To provide a hollow rotor blade for a turbine for a gas turbine engine, in which the tip of the blade can be sufficiently cooled to improve reliability without deteriorating aerodynamic characteristics and thermomechanical characteristics of the blade. SOLUTION: This hollow rotary blade includes an inner cooling passage 24, an opening cavity 30 positioned at the tip 14 of the blade bordered by an end wall 26 and a rim 28, and a cooling passage 32 connecting the inner cooling passage 24 to the outer surface of a pressure wall 16 inclined to the pressure wall 16 to appear in the outer surface of the pressure wall 16 close to the top 28a of the rim. As a feature, a reinforcement part 34 for a material exists between the rim 28 and the end wall 26 of the cavity 30 at least along part of the pressure wall 16. The rim 28 is thus expanded at a bottom adjacent to the end wall 26 in such a way that the cooling passage appears close to the top 28a of the rim 28 without deteriorating the mechanical strength of the tip 14 of the blade. COPYRIGHT: (C)2005,JPO&NCIPI
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