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.
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Review Article|
July 01 1955
U.S. Patent Specifications
Publisher: Emerald Publishing
Online ISSN: 2059-9366
Print ISSN: 0002-2667
© MCB UP Limited
1955
Aircraft Engineering (1955) 27 (7): 234.
Citation
(1955), "U.S. Patent Specifications". Aircraft Engineering, Vol. 27 No. 7 pp. 234, doi: https://doi.org/10.1108/eb032584
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