| 摘要 |
PROBLEM TO BE SOLVED: To provide a rotor blade of a gas turbine engine and more particularly a method and a device for reducing turbine blade temperature. SOLUTION: An airfoil (42) for a gas turbine engine (10) includes a first side wall (44) and a second side wall (46) joined together at a leading edge (48) and a trailing edge (50) to define a cavity (56) therebetween. A plurality of rib walls (70) at least partially extend between the first and second side walls and define at least one cooling circuit (60) having at least three cooling chambers (80, 82, 84). At least one row of openings (88) extend through at least one of the rib walls, the first cooling chamber supplies cooling fluid to the cavity and the remaining cooling chambers are connected in fluid communication with the first cooling chamber through the openings. COPYRIGHT: (C)2006,JPO&NCIPI
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