Abstract: A signal device for turbo-engines which, by way of moving blades arranged on a rotor, when passing through a defined circumferential position of the housing, generates signals which are precise with respect to time. The device includes a probe which has fiber optical waveguides for emitting and receiving light. An illuminating beam is emitted which is focussed in the direction of the rotor. The probe is arranged on the housing at a distance with respect to free end faces of the moving blades. The probe emits the illuminating beam with an elliptical cross-section, through which the moving blades travel, in such a manner that, on each corresponding free end face, an elliptical illumination spot is imaged whose large axis is aligned essentially in parallel to the delivery-side or suction-side edges of the free end faces. The signals are generated from the light reflected by the free end faces.

Abstract: An arrangement limits a fuel supply from a fuel pressure reservoir by way of a controllable injection valve into the combustion space of an internal-combustion engine. The fuel flow is interrupted as a function of the forces applied to a spring-prestressed valve separating piston in the event of an outlet-side pressure drop. A reliable limiting of the maximal injected fuel quantity is achieved by providing a flow-through opening penetrating the separating piston with a closing device. This flow-through opening can be closed as a function of the displacing direction of the separating piston. If the displacing device closes the flow-through opening in the starting position, during the injection phase and in the piston end position, the limiting valve will continuously interrupt the fuel flow in the case of an outlet-side pressure drop.

Abstract: A galvanizing magazine has electrically conducting electrodes for holding a multitude of small parts in positions that assure uniform coating conditions for all parts held in any of electrodes held in the magazine. A hollow cylindrical electrode with slots therein forms the magazine, or a plurality of rod electrodes held in a current distributing disk at one end and in a mounting disk at the other end form the magazine. The electrodes have receptacles so that each receptacle holds one small part in such a way that the longitudinal axis of the small part and the central axis of the receptacle extend at a right angle and radially to a rotational axis of the magazine. The receptacles are uniformly spaced from each other in a row along a respective electrode and also uniformly spaced with angular spacings in the circumferential direction around the longitudinal rotational axis of the magazine.

Abstract: A ceramic heat insulation layer applied to a metal structural part or to an intermediate adherent layer thereon, has the surfaces of its inner, open pore structure coated with a passivating ceramic material or a metal deposition material for improving the properties of the heat insulation layer.

Abstract: A support housing for the fastening of the exhaust gas turbochargers of an internal-combustion engine is provided. The support housing encloses a hollow space which is used for receiving the turbines of the exhaust gas turbochargers while the compressors are situated outside the hollow space. In order to simplify the manufacturing and assembly and to reduce the costs, bearing housings of the exhaust gas turbochargers are integrated in the support housing. The manufacturing and the assembly may also be simplified and rendered less expensive by the fact that the support housing is divided into two symmetrical housing parts along a plane extending through the perpendicular axis in the center of the support housing. In this case, the two housing parts are preferably constructed to be centrically symmetrical with respect to the central perpendicular axis.

Abstract: An injection system provides an intermittent supply of fuel mixture into combustion spaces of an internal-combustion engine. The system includes a valve and a pipe by way of which a control space in the injection valves may alternatively be acted upon by a pressure. The control space is formed by a valve member and a piston. A first pressure spring presses the valve member onto an injection opening, and a second pressure spring presses the piston away from the injection opening.

Abstract: This invention relates to a component of an iron, cobalt or nickel-base alloy with a protective arrangement to prevent aluminizing or chromizing during gas diffusion coating, with a first layer as an interlayer and a second layer as a getter layer for reaction gases, where the first layer is a slip casting layer composed of oxide ceramic particles carried in a low-carbon vehicle free from halide, and the second layer is a metal layer or a metallic slip casting layer. The metal layer contains at least 50% by weight of the base-metal fraction of the component and exhibits all major alloy constituents of the component. The metal layer may be a sintered metal shape.

Abstract: The production of harmful substances during the operation of multi-cylinder diesel engines is reduced by separating the cylinders of the engine into two groups in combination with an exhaust gas return from one group to the other. The first group includes a plurality of the cylinders (2 to 6). The second group includes at least one cylinder (7), which is separated from the first group as far as combustion is concerned. A first fresh air suction intake (9) supplies fresh air to the group of first cylinders (2 to 6). An exhaust gas return device (24) feeds either directly or indirectly exhaust gas from the at least one second cylinder (7) through the first fresh air suction intake (9) to the group of first cylinders (2 to 6). A second fresh air suction intake (10) supplies fresh air to the second group of cylinders (7). The second fresh air suction intake (10) may also receive some exhaust gas which is then combusted by an additional fuel supply in the second fresh air suction intake (10).

Abstract: Two components, such as an engine block (1) and a gear case (2), are coupled to each other by at least two flexible coupling links (7, 8) and by a rigid coupling link (10). One end of each flexible coupling link is connected to the engine block or gear case by a first screw connector (11, 11A, 11B) having a threaded bolt (13) passing through a twin cone (16) acting as a centering member. The conical surfaces of the twin cone centering member (16) cooperate with respective conical surfaces (12) in the gear case (2) and in an expander ring (17) bearing with its outer surface against an inner surface of a hole in the coupling link (7, 8) or an intermediate bushing in the coupling link, whereby the force transmitting connection is accomplished with radial clamping forces. The cooperation of the conical surfaces compensates for alignment tolerances and uneven stress distributions are avoided.

Abstract: An embedded unit for a concrete foundation is used for the fixing of elastic machine bearing elements in the concrete foundation. The embedded unit is constructed from a plurality of rods and metal sheets which are fitted together while forming damping joints. This type of an embedded unit dampens the machine vibrations entering into the foundation, may have a high impedance, and can be sufficiently anchored in concrete material.

Abstract: A gas turbine combustor has at least one fuel nozzle located at a head end of the combustor. At least one swirl device is adjustable as a function of a load for supplying combustion air. The swirl device includes radial/tangential apertures formed between profiles of an annular body arranged coaxially with respect to the nozzle. The apertures are uniformly distributed around the circumference of the annular body and have aperture cross-sections that are constant along their entire length. The swirl device further includes a sleeve having fingers which extend inwardly to engage the apertures. The sleeve is adjustable with respect to the annular body. The fingers are axially displaceable within the apertures via the sleeve. The fingers are each arranged parallel to aperture walls spaced from the fingers to bound a maximal adjusting path of the fingers to form duct walls of the apertures.

Abstract: In order to have carbon fiber reinforced carbon resistant to oxidation, the proposal is for a process by means of which a bonding layer of amorphous SiNx is applied to the carbon fiber reinforced carbon to which in turn is applied a protective layer which is oxidation resistant at a temperature T, where T>400.degree. C. consisting preferably of Si.sub.3 N.sub.4.

Abstract: For the sealing of a gap between at least two components or groups of components which are movably arranged with respect to one another, particularly of a heat exchanger, a device is indicated in the case of which a strip-shaped sealing body, which is connected with one component, is sealingly and movably guided in a groove of the other component, and in the case of which the sealing body is composed in the manner of layers of elements, in the longitudinal direction of the gap. The layers are arranged to be displaceable and freely expandable, are suspended at one component in a swivelling manner, and are spatially movably guided on the other component by way of the groove, with a clamping effect.

Abstract: A repair process for blades of turboengines damaged in the head or edge regions in which the damaged regions are first separated to leave an undamaged blade stump with an exposed, repair surface. The repair surface of the blade stump is prepared for butt welding and a repair plate of constant thickness which exceeds the maximum profile height of the blade by more than 50% is provided with a front surface adapted to the repair surface. This front surface of the repair plate is abutted against the repair surface and the blade stump and the repair blade are then butt welded. The weld joint and the repair plate are machined to the profile contour of the blade stump and to the desired blade profile. This process is used for the repair of blades of integral rotor disks of turboengines, particularly for blades of integral compressor impellers.

Abstract: A shaft seal (5) for circumferential shaft speeds in excess of 30 m/s and for sealing a differential pressure between two chambers to be sealed, in excess of 100 kP, has several in-line sealing rings (12A, 12B, 20, 22). Preferably, at least two of the high-pressure side seal rings are constructed as slide seal rings (12A, 12B) that are urged against the shaft by a tension spring (17) surrounding the outer circumferential surface of the slide seal rings. One low-pressure side sealing ring is a brush seal (20). A compressed air seal ring (22) is arranged between this brush seal (20) and the slide seal rings (12A, 12B). The air seal ring (22) forms a radial air gap (24) around the shaft (1).

Abstract: In the rotor of a turbomachine, especially the turbine of a gas turbine engine, each rotor blade is mounted in the rotor disk rim by a blade root having a serrated profile that engages a correspondingly formed axial groove in the rotor disk rim. A shroud band is constructed so that at a predetermined operating point of the turbine, adjacent blades are supported against one another so as to damp vibrations. Light weight and heavy weight rotor blades are mounted alternatingly around the circumference of the rotor disk. The blade root and corresponding axial groove associated with each light weight or heavy weight blade are differently dimensioned or shaped to correspond to the differing loads associated with the heavy weight blades and the light weight blades respectively. Different materials, having different densities, are used for the heavy weight blades and the light weight blades.

Abstract: A combustion chamber apparatus 1 for a gas turbine has a pilot stage and a main stage for low-emission lean-burn operation. The pilot stage is separate from the main stage and is formed by a flame tube 2 with an upstream first fuel injector 3a and with a secondary combustion zone 7a. The main stage includes a vaporization chamber 4 and a combustion chamber 5, and a second fuel injector 3b is provided at an upstream end of the vaporization chamber 4. The vaporization chamber 4 produces a homogenous fuel-air mixture which will not burn until it is in the combustion chamber 5. In lean-burn operation of the apparatus, the separate arrangement of the two chambers 4, 5 significantly reduces the formation of nitrogen oxides. For use in aircraft gas turbine engines, the apparatus has an annular shape with several main and pilot stages.

Abstract: A process for producing plastic layers on gap sealing surfaces which are unaffected by temperature changes is provided. Plasma or acetylene oxygen flame is generated by a plasma or flame spraying burner, which melts a plastic mass under a cooling gas flow of from 40 to 150 SLpM and sprays it onto a gap sealing surface. Coatings produced by this process have dense to porous layer structures and, when polyphenylene sulfides are used as the plastic material, may be used up at to temperatures of 250.degree. C.

Abstract: A method is provided for manufacturing a bladed ring for drum-shaped rotors of turbomachinery, especially rotors for axial compressors of gas turbine engines. The bladed ring is to be manufactured by hot isostatic pressing (HIP) and the fiber rings are formed in a metallic powder material for the bladed ring arranged in a circumferential direction. The fiber rings are bonded with spacing therebetween. The fiber rings are reinforced by fibers embedded in a metal matrix. The bladed ring prefabricated in this fashion by HIP is machined down to its required dimensions.

Abstract: An exhaust system for a supercharged internal-combustion engine in which of the exhaust-gas-carrying components, the exhaust gas pipes leading from the cylinder outlets to the turbines, or the turbines, or the turbines and the exhaust gas pipes are arranged jointly in an exhaust-gas-tight housing. Openings in the exhaust-gas-carrying components cause the space formed between the exhaust-gas-carrying components and the housing to be filled with exhaust gas. By way of a bypass pipe which is connected with the space and leads to the turbine, exhaust gas can be blown off from the space. A blow-off valve is arranged in the bypass pipe.