U.S. Patent Specifications

Abstract

A starter system for an aircraft gas‐turbine engine comprising a starter motor and a gear mechanism connected between the starter motor and the engine whereby during starting the motor drives a turbine/compressor rotor assembly of the engine, which gear mechanism comprises a first gear train giving a first ratio of motor rotational speed to rotor assembly rotational speed suitable for starting under normal ground conditions and a second gear train giving a second ratio less than the first ratio and suitable for starting the engine in flight, and means for selecting the desired gear train.

Citation

(1954), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 26 No. 5, pp. 172-172. https://doi.org/10.1108/eb032431