| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an aerodynamically optimal airfoil profile obtained by improving a conventional airfoil to eliminate flow separation from a ventral side of a blade surface in a first stage blade adopting an axial entry method. <P>SOLUTION: In this turbine blade, the airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vain root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The turbine blade has a blade airfoil profile shape in an envelope within a range of ±2.0 mm in a direction normal to any surface location of an airfoil profile portion, wherein the airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates of X, Y and Z set forth in Tables 1 through 7 (not shown) wherein the Z is a distance representing a sectional height from a root of the airfoil profile portion, and contours represented by the X and Y at each section Z is joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion. <P>COPYRIGHT: (C)2008,JPO&INPIT |
