Abstract: A gas turbine engine with an exhaust gas heat exchanger comprising a connection between the heat-exchanger outlet and an inlet of a combustion chamber for supplying heated compressed air to the combustion chamber, the connection including two pipes with a flexible element in the form of a metal bellows to compensate for thermal expansion. The pipes are symmetrically disposed and laterally spaced with respect to a line connecting the axis of the gas turbine to the axis of the heat exchanger outlet such that the metal bellows converge at an acute angle in the direction towards the heat exchanger. At one end the pipes are connected to the outlet of the heat exchanger by a pipe elbow and at their other ends to an inlet casing of the combustion chamber. In this way, differential temperature displacements are minimized.

Abstract: A self-acting gap seal for a gap existing between individual modules of a composite, annular pressure vessel comprising a flat, thin-walled seal element on the inside of the pressure vessel to bridge the gap plus the circumferential region adjacent the gap. Internal pressure urges the seal element against the inner wall of the vessel to close and seal the gap to prevent exit of the pressure medium in the vessel.

Abstract: A device for compensating variations in pressure and flow in fuel supply systems of gas-turbine engines comprising a pump for supply of fuel under pressure into a fuel line and an accumulator which can be connected to the fuel line as a function of operating conditions. An accumulator disconnection valve relieves the accumulator from existing variations in pressure in the supply system and serves as a shutoff valve controlled by pressure differential between the fuel line and the accumulator. The valve comprises two valve members which are connected opposite each other and are spring-loaded in directions opposite each other.

Abstract: A device for controlling the load distribution and speed of gas turbine systems and particularly gas turbine engines comprising for each engine a fuel control unit having a proportionally acting speed governor and a master speed governor for a common output shaft of the gas turbine systems and a load distributing control device. The master speed governor forms signals from the speed deviation and the load distributing control device forms signals from load deviations of the gas turbine systems from one another. The signals influence the speed set points of the proportionally acting governors through electronic operational amplifiers forming signal outputs from the deviation signals and preferably an auxiliary quantity and electronic summing amplifiers for adding the signal outputs together to form the control signals.

Abstract: A system for the displacement of two thrust reversers for two jet engines of an airplane. Each thrust reverser has a drive motor operated by compressed air, a valve controlling the flow of compressed air to the motor, a set-point indicator including an input piston controllable by the action of compressed air, a differential transmission, and a feedback system from the motor to the differential transmission. The valve is actuated by the input piston and the motor via the differential transmission. The displacement of the two thrust reversers is halted by a system of stops acting on the input pistons at identical intermediate points in the paths of travel thereof and the displacement is thereafter continued after the thrust reversers have both reached their intermediate points in their paths of travel by deactivation of the stops.