Abstract: An adjusting mechanism for pivotal guide blades of turbo-propulsion units in which a rotatable adjusting ring is supported in a concentric support ring. The support ring is heat-insulatingly connected with the turbine housing by way of several connecting lugs or slide block guidances distributed over the circumference and the adjusting ring is connected with the guide blades by way of bendable pivot levers. It is achieved thereby that the heat flow from the hot turbine housing to the adjusting mechanism remains small and an exact adjustment of the guide blades can be achieved in this manner.

Abstract: Apparatus for the synchronized displacement of two thrust reversers for two jet engines of an airplane, comprising first and second systems for displacing respective thrust reversers. Each system includes a compressed air motor, a valve controlling the operation of the motor by controlling the flow of compressed air thereto, and an input system for operating each valve to control the displacement of the respective motor. A synchronizing system synchronizes the displacement of the thrust reversers by measuring displacement in the first and second systems at respective corresponding locations and controlling the operation of the first and second motors such that the displacements of the thrust reversers by the respective motors are equalized.

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.