| 摘要 |
PROBLEM TO BE SOLVED: To provide a moving blade of a radial turbine which increase turbine efficiency by uniformly setting the gas inflow angle at an inlet of the moving blade of a turbine in a height direction of the moving blade for restricting collision loss of gas due to irregularity of the gas inflow angle and secondary flow loss inside the moving blade. SOLUTION: In the radial turbine, working gas is made to flow from a spiral scroll to this moving blade of a turbine rotor positioned inside the scroll to work on the moving blade, and then to be discharge in an axial direction for driving the turbine rotor to rotate. In the moving blade, a cut-off part is formed by cutting of a prescribed quantity of an angular part on the shroud side and the hub side of an inlet end face to which the working gas flows in. The cut-off part is formed in such a way that at least its radial cut-off length is 10-20% the height of the inlet end face. COPYRIGHT: (C)2003,JPO
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