| 摘要 |
A turbine rotor blade with a leading edge region cooled by a series of impingement cooling cavities that repeats from near the platform to the blade tip to provide impingement cooling for the leading edge without a loss of cooling air flow volume. A cooling supply cavity delivers cooling air to a series of impingement cavities located on the pressure side, the leading edge and the suction side of the airfoil in a series flow. The spent cooling air from the series then flows up into the next series of impingement cavities to provide impingement cooling to the next section of the leading edge. The cooling air flows through multiple series of impingement cooling cavities until the blade tip, which then discharges the spent impingement cooling air through tip cooling holes.
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