U.S. Patent Specifications

Abstract

The combination in a gas turbine engine including a turbine‐driven compressor, a combustion section having an inlet communicating with said compressor, and means for starting said engine, of; means for supplying a combustible charge to said combustion section, means for igniting said combustible charge, and valve means for closing the inlet to said combustion section upon the ignition of said combustible charge comprising a control valve having radial array of pivotal overlapping shutter flaps positioned in the inlet of the said combustion section.

Citation

(1958), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 30 No. 5, pp. 158-158. https://doi.org/10.1108/eb032974