| 摘要 |
PROBLEM TO BE SOLVED: To provide a cascade impingement cooled airfoil. SOLUTION: A turbine blade (10) includes the airfoil (12) having opposite pressure and suction sidewalls (18, 20) joined together at opposite leading and trailing edges (22, 24) and extending longitudinally from a root (26) to a tip (28). A plurality of independent cooling circuits (34-38) are disposed inside the airfoil correspondingly along the pressure and suction sidewalls (18, 20) of the airfoil. Each cooling circuit (34-38) includes an inlet channel (40-44) extending through a dovetail (14). One (34) of the cooling circuits includes a plurality of longitudinal cascade channels (46) which are separated by corresponding perforate partitions (48) each including a row of impingement holes (50) for cascade impingement cooling the inner surface of the airfoil. COPYRIGHT: (C)2006,JPO&NCIPI
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