Turbine blade with near wall cooling channels

摘要

A turbine rotor blade with a thin thermal skin bonded over a spar to enclose serpentine flow cooling channels that extend from a platform to a blade tip along the airfoil walls. The radial channels discharge into a collection cavity and then flow through exit holes in the trailing edge. The radial cooling channels are formed as semi-circular shaped channels to maximize surface area on the hot side wall and on the cold side wall of the spar.

主权项

1. A turbine rotor blade comprising:
a spar forming a cooling air collection cavity on an inside and a number of serpentine radial flow cooling channels on an outer surface; a thin thermal skin bonded to the outer surface of the spar to enclose the serpentine radial flow cooling channels; a row of exit holes on the trailing edge connected directly to the cooling air collection cavity; the radial flow cooling channels have a semi-circular shape with a flat face against the thin thermal skin; and, the upward flowing channel and the downward flowing channel form a half-circular shape with a rib separating the two channels.