| 摘要 |
A gas turbine engine hollow airfoil has an airfoil outer wall with widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of the airfoil and extending radially from a radially inner base to a radially outer airfoil tip. A cooling circuit within the airfoil has radially extending first, middle, and last channels arranged respectively in series with the first channel in fluid communication with a source of cooling air from outside the airfoil. The last channel is in fluid communication with one of the edges. A refresher passageway extends through a radially inner wall bounding a radially inner portion of the last channel and is in fluid communication with the source of cooling air. The refresher passageway is separate, spaced apart, and independent from the first channel. In one embodiment, a metering plate covers an inlet to the refresher passageway and the metering plate has a metering hole over the inlet and the metering hole is adjustable. The hollow airfoil may be part of a gas turbine engine blade extending radially outwardly from a root with the first channel extending through the root and having an entrance at a bottom surface of the root. The refresher passageway extends through a radially inner wall bounding a radially inner portion of the last channel and through the root and the inlet to the refresher passageway is located at the bottom surface of the root and is separate and spaced apart from the entrance of the first channel. The metering plate is disposed on the bottom surface of the root.
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