U.S. Patent Specifications

Abstract

For use with a turbine providing coolant for the blading, a nozzle vane comprising a root portion, a neck portion joined thereto, and a blade portion extending from said neck portion; said blade portion being partially defined by a leading edge and a trailing edge; a distributing chamber formed within said blade portion; said trailing edge having a series of openings therein; a plurality of small passages radiating from said chamber and communicating with said trailing edge; said root and neck portions being formed with a passage through them communicating with said chamber thereby providing a continuous path for the transfer of coolant from said root portion through said neck portion and said plurality of passages to said series of openings in said trailing edge.

Citation

(1955), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 27 No. 7, pp. 234-234. https://doi.org/10.1108/eb032584