Abstract: A control circuit arrangement for a gas turbine engine has first and second identical control circuits which are responsive to groups of input signals to provide nominally identical first and second output signals. It is arranged that input signals to the first control circuit are nominally identical with corresponding input signals to the second control circuit. Means are provided, responsive to malfunction of either one of the first and second control circuits, to render the malfunctioning circuit inoperative and to render the other of the control circuits operative. A third control circuit is responsive to at least one pair of corresponding input signals to the first and second circuits, to provide a third output signal to the engine. The first, second and third output signals do not control the engine reheat system, and the arrangement may include a fourth control circuit for controlling this reheat system.

Abstract: A rotary internal combustion engine is disclosed which is entirely cylindrical. The engine includes a cylindrical stator having mounted for rotation therein two pairs of blades on concentric shafts. Means, preferably a universal joint is provided which operates through a gear case to control the relative speeds of the shafts and thus the angle between the blades to change the volume of the combustion chamber through the four operations of intake, compression, expansion (power) and exhaust.

Abstract: A fuel control system for a gas turbine engine includes a variable metering device from whose downstream side a pair of passages lead respectively to pilot and main engine burners. A throttle valve controls flow to the main burners and is urged open by the pressure downstream of the metering device. A biasing spring urges the throttle valve shut and the bias applied by the spring is variable in accordance with engine speed or during starting of the engine. Variation in spring bias is applied through alteration in the position of a spill valve connected across the metering device.

Abstract: A coordinated fan pitch, fuel flow and fan exhaust nozzle area control for a gas turbine powered aircraft propulsor of the bypass duct, variable pitch and exhaust nozzle configuration serves to effectuate reverse pitch change through feather, by minimizing forward thrust excursion and shaft torque to obtain rapid reverse thrust response.

Abstract: A control for a variable pitch fan propulsor driven by a turbine type of power plant which fan is mounted in an engine bypass duct having a variable exit nozzle. The control serves to coordinate the control of fuel flow to the engine, the area of the fan exit nozzle, and the pitch of the fan blades by biasing the power lever position signal with Flight Mach No. An additional feature is the inclusion of fan surge control derived from signals of flight Mach No. and corrected free turbine speed.

Abstract: A combustion liner suitable for an automotive gas turbine has variable primary and secondary air admission ports through the wall of the liner. The areas of these sets of ports are varied jointly by two annular valve sleeve assemblies reciprocable on the surface of the liner. Each valve sleeve assembly comprises an outer rigid ring, four approximately quarter-cylindrical valve plates extending around the outer surface of the liner within the ring and coupled to the ring for reciprocation by it, and a leaf spring disposed between the ring and each valve plate to hold the valve plate in contact with the liner.

Abstract: A fuel control system for a gas turbine engine includes a metering device having a sleeve which is movable to vary fuel flow to the engine. A stop cooperates with the sleeve to define a minimum fuel flow. The stop is movable between a first, normal running position and a second, engine starting position, the second position corresponding to a smaller minimum flow through the metering arrangement.