U.S. Patent Specifications

Abstract

In combination with a by‐pass gas turbine engine comprising a low‐pressure compressor stage, a high‐pressure stage connected with the outlet of said low‐pressure compressor stage, combustion equipment connected with the outlet from the high‐pressure compressor stage, turbine means adapted to drive the compressor stages and connected to receive combustion gases from the combustion equipment, fuel supply means adapted to deliver fuel to said combustion equipment and including a fuel delivery conduit through which said fuel is delivered, a propelling nozzle, and a by‐pass duct connected at its inlet end to the outlet of said low‐pressure compressor stage and adapted to deliver the by‐passed air to the propelling nozzle to pass therethrough to atmosphere as a propulsive jet; a control arrangement comprising pressure‐responsive means connected to said by‐pass duct and adapted to respond to a rapid fall in pressure in said by‐pass duct, and valve means in said fuel delivery conduit and connected to said pressure‐responsive means to be operated thereby to reduce the fuel flow to the engine on sensing of a rapid fall in pressure in the by‐pass duct.

Citation

(1958), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 30 No. 3, pp. 92-92. https://doi.org/10.1108/eb032949