| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To improve a method of cooling a turbine aerofoil. <P>SOLUTION: An insert 128 receives at first cooling air flowing into a chamber 122 to be delivered via a plurality of insert openings 130, and cools an inner face of an outer wall 133. The insert 128 has a shape which is the same to an contour shape of the outer wall 133 of the chamber 122, and arranged spaced apart from the outer wall. The chamber 122 and the insert 128 become thin as extending toward a rear edge 118. The insert 128 terminated finally, and the chamber 122 is terminated in a pin array 152. A position of a downstream end terminal point of the insert 128 is positioned to make a distance get minimum with respect to a position of an upstream start point of the pin array 152, and the pin array portion 152 includes a plurality of openings defining inlets to a plurality of rear edge cooling openings 144 at a downstream end. <P>COPYRIGHT: (C)2010,JPO&INPIT</p> |
