| 摘要 |
PROBLEM TO BE SOLVED: To provide an aerofoil contour of a turbine blade. SOLUTION: A second stage nozzle (12) includes the blade (14) including the aerofoil contour substantially according to Cartesian coordinate values of X, Y and Z indicated in Table I by inches, where the values of the X, Y and Z start in a portion of the radial-directional most inner side in aerodynamic aspect of the aerofoil, and determines the portion with respect to each Z coordinate value, and where the values of the X, Y and Z may be increased or decreased as functions of the same constant or number, to bring an aerofoil portion of an expanded or contracted nozzle. COPYRIGHT: (C)2010,JPO&INPIT |
