U.S. Patent Specifications

Abstract

A multi‐stage axial‐flow compressor having an inner duct wall and an outer duct wall defining an annular compressor duct between them, and an inlet row of stator blades each of which extends the whole way across said compressor duct and each of which comprises a plurality of relatively adjustable parts mounted for relative adjustment about an axis substantially radial to the axis of rotation of the compressor.

Citation

(1955), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 27 No. 1, pp. 32-32. https://doi.org/10.1108/eb032520