Abstract: Apparatus for the compact assembly of a gas turbine engine with a recuperative exhaust gas heat exchanger wherein inlet and outlet ducts of the core of the heat exchanger are supported by support plates attached to the casing of the heat exchanger. The support plates are connected to the engine casing with capability of relative movement between the ducts and the support plates so that thermally produced expansions and contractions are taken up without stress at the support points of the ducts with the support plates and within the heat exchanger. As a consequence, no expansion joints are necessary in the connection lines.

Abstract: Apparatus for the support and adjustment of stator blades of a gas turbine, in which an adjusting ring is connected to the stator blades by adjustment levers disposed outside the turbine housing. The adjusting ring is supported for rotation in the circumferential direction on a support ring, which has elastic resilience in the radial direction, the support ring being suspended on and centered in a movable manner on radial pins fixed in an outer housing of the turbine. The connection of the adjusting ring and the support ring is achieved by a ball-bearing which is pre-stressed. When the adjusting ring is displaced circumferentially, the stator blades are pivoted around suspension shafts by levers fixed to the shafts and connected to the adjusting ring for universal pivotal movement.

Abstract: The air ducts of a heat exchanger are formed of a plurality of duct sections arranged axially one after the other and are clamped together in sealed relation by tension bars arranged symmetrically at the inner surface of the duct sections. The tension bars conform in shape to that of the duct sections to abut thereagainst.

Abstract: A sealing ring device includes a sealing ring and a mounting or carrier ring which are supported relative to each other and relative to a housing or further hollow shaft. Thus, two pressure members are inserted between the sealing ring and the carrier ring at locations which are displaced by about 180.degree. from each other. Further, two additional pressure members are inserted between the carrier ring and the housing, whereby these additional pressure members are again displaced relative to each other at diametrically opposite locations. Thus, the angular spacing between neighboring pressure members is about 90.degree.. This construction makes sure that any bearing play or clearance remains small and independent of any centering errors in the shaft relative to its bearing in a housing or in another hollow shaft.

Abstract: Apparatus for the production by powder metallurgy of a heat exchanger block in which two spaced concentric half shells are provided with holes in which profiled pipes are inserted. The profiled pipes are internally supported by pins when metal powder is injected into the hollow space between the half shells for forming a wall section of a header. The radially outer half shell is formed by a plurality of half rings arranged with their side faces in contact with one another and the half rings are individually removed after the wall section is formed.

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: A valve for a fluid flow engine is constructed so that it can cause a required pressure build-up, so that it can drain excess fuel back to a tank, and so that the engine can be shut-off. Hot fuels that must be returned into the tank are prevented from damaging the fuel intake slots. The pressure build-up is controlled or determined by a separate fuel metering surface.

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 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: An exhaust section of a reaction engine, especially for aircraft, including a fixed pipe and a nozzle pipe carried by the fixed pipe. Pins project from each pipe into slots in the other pipe, and each of a plurality of actuating elements extends between, and is pivoted to, the exteriors of both pipes. The actuating elements are adjustable lengthwise to pivot the nozzle pipe with respect to the fixed pipe. There may be four pairs of pins and slots, and four actuating elements. Each actuating element may include two cooperating actuating members, one of the members being pivoted to the fixed pipe and the other member being pivoted to the nozzle pipe. The actuating members may be a hydraulic piston/cylinder device or a threaded spindle and nut arrangement. Means are provided for operating the actuating elements of each diametrically-opposed pair in opposite directions. The pins and slots may be carried by supporting arms projecting longitudinally from the pipes.

Abstract: Fuel dispensing apparatus for dispensing fuel to a gas turbine engine is provided which includes a fuel metering slide valve having a control slide piston which directly controls an opening for supply of fuel to a gas turbine engine. A piston-cylinder servo-mechanism is provided for controlling flow of a servo fluid which acts on the control slide piston to assist in the movement thereof between respective positions. An auxiliary control slide piston of the servo-mechanism is in turn acted upon by supply of pressure to respective oppositely facing pressure surfaces from an electro-hydraulic converter. The electro-hydraulic converter is controlled by an electronic control mechanism responsive to control an engine operating parameters.

Abstract: A control system for a gas turbine engine, especially a vehicular gas turbine engine, having a speed governor responsive to a controlled variable which is the speed of a gas generator shaft for providing an output to control fuel flow to the engine, a temperature regulator device responsive to a controlled variable which is the gas temperature of the gas generator of the engine for providing an output to control the positioning of variable guide vanes of the engine, and a control arrangement for controlling the controlled variable and outputs of the speed governor and temperature regulator device as a function of the engine characteristics to ensure optimum engine operation.

Abstract: A regulating system for a prime mover, especially a single-spool gas turbine for use in propelling a motor vehicle or aircraft, in which system there is provided a first speed governor for controlling the fuel flow or input power and a second speed governor for controlling the power output. The two speed governors act concurrently in response to the speed of the prime mover and regulate the power input and power output independently of one another.