| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a blade or vane for an airfoil portion with internal cooling improved from the prior-art in consideration, for example, of a uniformly high igniting temperature or a low-temperature cooling flow. <P>SOLUTION: A center cavity part is divided into a front edge region 7a and a rear edge region 7b with a first web 15 which connects a suction side outer wall 13 to a pressure side outer wall 14 and extends in at least one longitudinal direction, to define a front edge chamber 1 in the front edge region 7a. It has a second web 16 extending in the longitudinal direction for connecting the first web 15 to the suction side outer wall 13, to define a first inlet chamber 2 on a suction side 10 of the second web 16 and a second inlet chamber 3 in the rear edge region for cooled air. The first web 15 has at least one crossing hole H1 between the first inlet chamber 2 and the front edge chamber 1, and the second web 16 therefore has no opening portion. <P>COPYRIGHT: (C)2010,JPO&INPIT |
