| 摘要 |
PROBLEM TO BE SOLVED: To provide a moving blade of a radial turbine capable of improving the turbine efficiency of a turbine having a matching point (operation point) of a small velocity ratio (U/C<SB>0</SB>) by reducing an impact loss of flow-in gas generated at an inlet of a turbine moving blade, especially a moving blade inlet near both walls at a shroud side and a hub side and suppressing a secondary flow developed in the moving blade. SOLUTION: The moving blade is formed in such a manner that directions of a blade tip shape near both walls at a shroud side and a hub side forming a height direction of a moving blade inlet in which working gas flows are consistent with flows in directions -β<SB>A</SB>, -β<SB>C</SB>of gas relative flow-in velocity components of velocity triangles formed of flow-in velocities C<SB>A</SB>, C<SB>C</SB>of working gas flowing in the moving blade inlet, rotation velocities U<SB>A</SB>, U<SB>C</SB>in a circumference direction of the moving blade, and gas relative flow-in velocities W<SB>A</SB>, W<SB>C</SB>. COPYRIGHT: (C)2011,JPO&INPIT |
