| 摘要 |
A gas turbine engine component (10), such as a high pressure turbine blade, has an airfoil portion (14), a platform (20), and micro-circuits (50,80) within the platform (20) for cooling at least one of a platform edge (38) adjacent the pressure side (30) of the airfoil portion (14) and the trailing edge (36) of the platform (20). The micro-circuits (50,80) include a first micro-circuit (50) on a suction side (32) of the airfoil (14) and a second micro-circuit (80) on a pressure side (30) of the airfoil. The micro-circuits (50,80) within the platform achieve high thermal convective efficiency, high film coverage, and high cooling effectiveness.
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