| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine flow passage in a gas turbine engine. SOLUTION: A turbine blade-shaped part 12 includes opposing positive pressure side face 18 and negative pressure side face 20 extending over a span from a flow passage face 28. The flow passage face 28 has laterally opposing first and second end faces 34, 36 corresponding to front and rear end fringes 30, 32 opposing in the direction of blade chord and the blade-shaped part positive pressure and negative pressure side faces 18, 20. The flow passage face 28 joins the first end face 34 in a form of a front bull nose 42 at a front end fringe 30 and joins the second end face 36 in a form of a rear bull nose 44 at a rear end fringe 32. Radii of the bull noses 42, 44 are changed from opposing end fringes 30, 32. COPYRIGHT: (C)2006,JPO&NCIPI
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