| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a gas turbine engine airfoil part (204) and a method of manufacturing the same. <P>SOLUTION: This airfoil part includes an inside cooling flow passage (220) having the front edge (212), the rear edge (214), a pair of side surfaces (208 and 210) extending to the rear edge from the front edge and the passing axis (222) formed between the side surfaces and making air flow along it. The airfoil part includes a plurality of flow passages (256, 260, 264, 268, 272, 276, 280, 284 and 288) extending by penetrating through at least one of the side surfaces so that the flow passages are configured to deliver cooling air from the inside cooling flow passage, and the respective flow passages have the bent flow passage axes (258, 262, 266, 270, 274, 278, 282, 286 and 290) oriented so as to cross at an acute angle with the passing axis. <P>COPYRIGHT: (C)2013,JPO&INPIT |
