| 摘要 |
<p>PROBLEM TO BE SOLVED: To reduce lowering of efficiency related to an aerodynamic loss and end wall impact by restricting the number of impact in a passage of each inter- blade. SOLUTION: A swept turbo machine blade to be used for a cascade of a blade is disclosed. The blade 12 has a uniformly swept aerofoil 64 an end wall impact 64 in length in the restricted diameterical direction and a passage impact 66 match with each other, and a working medium 48 flowing through an inter- blade passage 50 receives a single coincided impact rather than individual impacts. Consequently, an inside transitive point 40 where the extreme front end of the aerofoil 64 is positioned at an inside transitive diameter rt-inner is specified. A sweeping angle of the aerofoil is not reduced as the diameter increases from an inside transitive diameter rt-outer , that is, from the inside transitive diameter to an aerofoil head end 26, and it does not increase as a diameter between an outside transitive diameter and the aerofoil head end 26 increases.</p> |
