| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine blade for a gas turbine engine. SOLUTION: The turbine blade 10 comprises an airfoil 12, a platform 14, and an integrated dovetail 16. The airfoil 12 has opposed positive and negative pressure side faces 20, 22 extending between opposed leading edge and trailing edge 24, 26 over a blade chord and extending over a span from a root 28 to a front end 30, and the front end 30 includes first and second ribs 36, 38 extending from a front end floor 40 along the positive and negative side faces 20, 22. The first and second ribs 36, 38 are joined at their leading edge and trailing edge 24, 26 to each other and arranged at a space in a blade cross direction, and it includes trifurcate front end baffles 42, 44, 46 having triple front end pockets 48, 50, 52 formed as counter contours extending from the second rib 38 toward the blade chord and located adjacent to one another. COPYRIGHT: (C)2008,JPO&INPIT |
