Abstract: A method of securing in fluid tight relation the spaced ends of straight legs of heat exchange tubes of a U-shaped matrix to a tubular fluid conveying duct is effected by bending the spaced ends of the straight legs of the matrix to reduce the spacing between the ends of the tubes, thereafter loosely gathering the ends of the tubes to bring them into contact along their surfaces and then encircling the loosely gathered tube ends with frame elements which apply compression forces to the tube ends to deform then and cause them to come into contact with one another over substantially the entire surface areas thereof. The tube ends are then heated to braze them together and unite them with the frame elements as a unified block assembly. The block assembly is then inserted into an opening of conforming shape in the tubular fluid conveying duct and joined to the duct in sealed relation.

Abstract: A composite material is produced from a metal core and fiber-reinforced plastic material, in which the reinforcing fibers penetrate into and entwine around the metal core without coming into contact with the metal core. Parts for aircraft and turbine construction can be made from the composite material to provide higher impact strength and rigidity at less weight as compared to metal components.

Abstract: A propfan turbo-engine has two shrouded propfan rotors arranged upstream of a gas turbine which are driven by a contra-rotating working turbine. In addition to a favorable flow onto the blades, a low weight of the engine can be achieved.

Abstract: An energy supply system for mobile electric weapons, for the operation of a storage unit, has a turbine which can be acted upon for a short time by a combustion chamber with hot gas of a high pressure and temperature. In the idling operation, the turbine is maintained at an idling speed by exhaust gas from a vehicle driving system. As a result, a fast charging of the storage unit is achieved, and at the same time, the space requirement of the storage unit and of the energy generating device is reduced.

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 pipes arranged in spaced relation within the respective ducts sections. The tension pipes are perforated to permit air flow between the ducts and heat exchange tubes connected thereto.

Abstract: Method of apparatus for venting rotor parts of an axial flows compressor of a gas turbine power plant having an axial diffuser arranged behind the rotor and stator vanes at the last compressor stage. An annular chamber is formed downstream of the last rotor disk between adjacent rotor and stator parts and compressed air downstream of the diffuser is introduced into the chamber. The air in the chamber is divided into two individual streams, one of which is recycled to the compressor through an annular slot between the rotor and guide vanes at the last compressor stage and the other of which is discharged as a stream of leakage air into the secondary air system of the turbine.

Abstract: A nozzle vane assembly for a gas turbine exhibits a number of circumferentially spaced vanes connected to a shroud. A second, concentric shroud is arranged separately and urged axially against the unrestrained ends of the vanes through a spring loaded clamping device. This arrangement serves to alleviate thermal stresses and thermal fatigue in the vane assembly.

Abstract: Composite changeover-type reaction power plant for propelling aircraft and spacecraft operating in subsonsic, supersonic and hypersonic regions, embracing a turbofan bypass engine with front fan, and a ramjet engine with a cycle corresponding to that of the fan, where the fan has individually independently supported, operationally counterrotating statorless rotors and variable fan blades which are feathered and immobilized during ramjet operation for low drag during said ramjet operation.

Abstract: A method for the production of a protective layer on a structural part against thermal, chemical and/or mechanical stresses, particularly structural parts of complex shape such as turbine blades in which powder of a starting material for the layer is suspended in a suspension liquid and the suspension is held at a temperature just above the freezing point of the suspension. The structural part to be coated is maintained at a temperature below the freezing point of the dispersing liquid and is dipped into the suspension so that a layer of the powder present in the suspension freezes firmly on the part. The thickness of the layer is dependent on the temperature of the structural part and the length of time during which the structural part remains immersed on the suspension. The structural part now coated with the powder layer is subjected to freeze drying and is thereafter heated to a temperature above the freezing point of the suspension.

Abstract: A method for manufacturing a tubular distributor of a heat exchanger in which the distributor is formed by layers of material between which the ends of heat exchange tubes of a matrix are secured in fluid-tight manner. The layers are made of fibers which are juxtaposed between the tube ends of adjacent rows and the layers are deformed by compression so that they each engage around one-half of the associated row of tubes to form an initially porous structure into which a metallic material is injected to integrate the fibers of the layers with one another and with the ends of the tubes in sealed relation.

Abstract: A method of producing dispersion hardened metal alloys which incorporate highly reactive metals or their alloys whose oxides are not adapted to be easily reduced. According to the method, the highly reactive metals of their alloys are added as powder particles to a solution of a salt of a reducible metal which is to form a metallic matrix in which the reactive metals or their alloys are to be integrated, after which the solution is atomized to form particles from which the solvent is removed to yield the final product of the metal matrix with the highly reactive metals or their alloys integrated therein as a second phase.

Abstract: A propeller for a prop-jet engine having a propellor blade formed as a hollow shell member whose outer surface has an aerodynamic blade profile, the propellor blade being secured to a rotor via an adjustment pin. The hollow shell member is internally braced partly along its radial length by a flexible spar secured to the pin and made of thermoplastic material. The flexible spar is hollow and receives a metal spar hich is fixed to the pin and is given flexibility in bending by the provision of a slot therein.

Abstract: An anti-rupture ring is slit axially at least at one location and is provided thereat with clamping devices which permit a rapid tightening and loosening of the anti-rupture ring. In one embodiment, the clamping of the anti-rupture ring can be varied hydraulically so as to minimize clearance losses in operation. The invention can be used in all types of turbo engines endangered by breakage of rotor blades, particularly in aircraft gas turbine construction, and it permits simple, damage-free mounting and a well-defined clamping of the anti-rupture ring.

Abstract: In a gas generator of a gas turbine, the turbine is provided with more stages than aerodynamically necessary for reducing the turbine rotational speed. As a result thereof, the stresses of the turbine rotor are reduced, the latter can be made of ceramic material, and the turbine inlet temperature can be increased. In order to permit the compressor to continue to operate at optimum rotational speed, the compressor is coupled with the turbine by way of a transmission providing a speed-up. Owing to this arrangement, the thermal efficiency and therewith the economy of the gas turbine can be considerably increased and the heretofore occurring problems with the use of ceramic material in the turbine are solved in a simple manner.

Abstract: A turbo-engine having a structure for controlling the radial gap and including an inner casing which surrounds a rotor and is assembled from shell-like parts; parts of this casing have a high thermal mass, are arranged around the rotor blades of the rotor and can be fastened in longitudinal direction (axial direction) to other parts.

Abstract: A variable-geometry turbocompressor is provided which includes a tandem variable stator downstream of a rotor stage. The tandem stator includes an inlet stator cascade and an outlet stator cascade arranged adjacent one another and each including variable guide vanes. To accommodate precise control of the air flow over various compressor operating conditions, the inlet and outlet stator cascades are provided with adjusting mechanisms for varying the position of their vanes independently of one another.

Abstract: In a gas turbine propulsion unit with means for branching off compressor air for purposes of cooling hot parts of the turbine, the cooling air is conducted to the hot parts to be cooled along a detour by way of structural parts of high heat capacity and large surface area. It is achieved therewith that with a jump-like change of the cooling air temperature as, for example, during an acceleration operation, the cooling air gives off a portion of its heat content along the detour to the structural parts so that the thermal time behavior of the cooling air is slowed down.

Abstract: A heat exchanger having a matrix of tubes around which hot gases flow, the matrix comprising spaced internested oval profiled tubes connected to a manifold for supply of compressed air to the tubes. The manifold is composed of a plurality of superimposed elements assembled on another in fluid-tight fashion. The profiled tubes have rectangular or square base ends which are fitted into corresponding openings in the superimposed elements.

Abstract: A gas turbine plant in which the drive line of a power turbine extends substantially parallel to the longitudinal axis of the gas generator, the compressor drive turbine and power turbine being traversed in opposite directions by heated exhaust gases from a combustion chamber. A heat exchanger receives exhaust gases from the power turbine to heat compressed air to be delivered to the combustion chamber. The heat exchanger includes a matrix of U-shaped tubes connected to supply and discharge ducts of compressed air. The entire tube matrix is enclosed within an exhaust gas collector housing mounted downstream of the exhaust gas outlet of the power turbine and extending along the combustion chamber. The ducts are arranged in substantially parallel, adjacent relation and are each closed at one end. The open ends of the supply ducts respectively communicate with an outer channel of the plant which terminates at an end of the combustion chamber to receive compressed air to be heated.

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.