| 摘要 |
A turbine blade for use in a gas turbine engine having an internal serpentine flow cooling circuit with pin fins and trip strips to promote heat transfer for obtaining a thermally balanced blade sectional temperature distribution. The serpentine flow cooling circuit forms a 7-pass serpentine flow circuit from the leading edge, along the pressure side, through the trailing edge region, and then along the suction side. The serpentine flow circuit of the present invention is formed by a printing process without the need for a ceramic core and casting, and where the pin fins for all of the channels can be aligned perpendicular to the airfoil surface. The metallic and ceramic printing process can be used to form a single piece airfoil with all of the internal cooling passages and features as a single piece.
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