U.S. Patent Specifications

Abstract

Turbo‐compressor propulsive apparatus comprising in combination a turbine, a shaft driven by this turbine, a compressor coupled to this shaft, a casing enclosing the compressor with an intake passage thereto through which air is drawn by the compressor, a bearing for the said turbine driving shaft adjacent to the turbine, means for delivering to this bearing and also to the turbine air which has been compressed by the compressor for the purpose of cooling these parts, said parts including at least one chamber a wall of which forms a part of the intake passage to the said casing enclosing the compressor, at least one passage through which air is delivered by the compressor into this chamber, and at least one passage through which the air after passing through and being cooled in this chamber is led to a part which is to be cooled thereby.

Citation

(1947), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 19 No. 3, pp. 109-110. https://doi.org/10.1108/eb031491