| 摘要 |
PROBLEM TO BE SOLVED: To improve convective heat-transfer at a front edge nose section of a cavity in the radial-flow front-edge cavity of a turbine engine component by using a trip-strip structure. SOLUTION: The turbine engine component comprises an air foil section having the front edge 30, a negative pressure side 46, and a positive pressure side 42; and the radial-flow front-edge cavity 34 in which a cooling fluid for cooling the front edge 30 flows. Further, the trip-strips 40 and 44 for generating, at the front edge cavity 34, a swirl 49 colliding with a nose section 36 of the front edge cavity 34 have structures of zigzag arrangement. COPYRIGHT: (C)2008,JPO&INPIT
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