| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide an airfoil shape for a compressor in which many system requirements are satisfied at each stage of a flow path section of a gas turbine to meet design goals. <P>SOLUTION: The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a Table 1 (not shown). In Table 1, X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape (22, 23). <P>COPYRIGHT: (C)2008,JPO&INPIT</p> |
