Turbine airfoil with body microcircuits terminating in platform

摘要

A turbine engine component includes a platform and one or more microcircuit cooling passages embedded within one or more walls of an airfoil portion of the component. Each microcircuit cooling passage terminates within the thickness of the platform so as to provide cooling to the initial 10% span of the airfoil portion. Each microcircuit cooling passage has an inlet for receiving cooling fluid, which inlet is also embedded within the platform.

主权项

1. A turbine engine component comprising:
An airfoil portion having a platform, a pressure side wall, a suction side wall, and a root portion; said platform having an upper surface and a lower surface; at least one microcircuit cooling passage embedded within and extending into at least one of said pressure side wall and said suction side wall; said at least one microcircuit cooling passage being collinear with at least one of said pressure side wall and said suction side wall; said at least one microcircuit cooling passage terminating in a location between said upper surface and said lower surface, wherein said platform has a thickness and each said microcircuit cooling passage terminates at a mid-region of said thickness; at least one central core; each said microcircuit cooling passage having an inlet at an angle to said microcircuit cooling passage which communicates with said at least one central core and with said terminating location of said at least one microcircuit cooling passage, wherein said inlet is located in the mid-region of said thickness; and each said microcircuit cooling passage providing cooling within an initial 10% span of said airfoil portion.