| 摘要 |
PROBLEM TO BE SOLVED: To provide a cooling air circuit for a rotor blade and a stator blade for a turbine in a gas turbine engine. SOLUTION: A hollow airfoil part 12 of the gas turbine engine comprises a positive pressure side wall and a negative pressure side wall 16 and 18 disposed at an interval from each other in a width direction, and jointed with each other at a front edge and a rear edge 20 and 22 of the airfoil part 12 disposed apart in a chord direction, and it has an airfoil part outer wall 15 extended outward in a radial direction from a bottom part to a tip part. The airfoil part 12 is provided with a single three-passage zigzag cooling circuit 36 flowing rearward, and a through type front edge cooling passage penetrating the airfoil part 12 to be extended in a radial direction to have the front edge 20 as a boundary partly. In an embodiment, a through type single passage front edge feed passage 49 is provided to feed cooling air to a rear edge cooling chamber 72 and a front edge cooling chamber 72. COPYRIGHT: (C)2004,JPO |
