Abstract: A system is provided for cooling especially the backplate of a flame tube of a combustion chamber for gas turbine engines, of the type having at least one burner arranged on the backplate and having a fuel nozzle and at least one swirler arranged coaxially with the fuel nozzle for the supply of combustion air. The backplate is cooled with compressed air diverted from a compressor and ducted to a head end of the combustion chamber. The backplate forms at least one cooling air duct to carry the compressed air supplied for backplate cooling, and the cooling air duct communicates at its outlet end at the burner with the flame tube such that the compressed air issuing from the cooling air duct enters into combustion in the primary zone. At its outlet end the cooling air duct can communicate with the air inlets of at least one swirler.

Abstract: A heat exchanger of a plate construction, as used, for example, in a water-cooled charge air cooler with air-side lamella plates avoids undesirable thermal expansion effects which occur in the transient operation of a charge air cooler and result in damage. The otherwise completely hard-soldered cooler block is divided along a plane parallel to the plate planes into two or more partial blocks. When the partial blocks are combined at a mutual distance to form a cooler block assembly, each partial block receives a clearance in the transverse direction which compensates the thermally caused transverse expansions of the individual blocks.

Abstract: An abrasive coating is formed on the tip of a component of a drive unit for abrading an abradable coating during a stripping operation by thermal spraying a ceramic layer on the component, the ceramic layer being profiled and providing a succession of abrading edges and intermediate spaces between the abrading edges to take up and remove abraded material. The abrading edges can be formed as deposits of ceramic material on the component or, as a ceramic layer applied on a profiled surface etched on the component.

Abstract: A brush seal assembly for turbo-engines is provided for sealing off spaces on a circumferential gap which are differently acted upon by pressure, particularly between an engine stator and an engine rotor. A holding device for a bristle bundle is provided on the engine stator, from which holding device the bristle bundle is guided between circumferential webs in a sealing manner against the engine rotor and forms an axial gap in the circumferential direction with respect to one web facing the high-pressure side. In this case, at least on the side which faces the space of the higher pressure on the seal, the bristle bundle is to have devices for the shielding against a turbulent flow triggered by the engine rotor.

Abstract: Rotor blades (1) are held by means of toothed roots (3) in correspondingly profiled axial grooves (4) of a rotor wheel rim (5). Between each root end and the base of an axial groove (4), there is formed a radial gap (S) accommodating a rivet (6). Each rivet (6) is centrally guided on two inserts (9, 9') resting against the base of the axial groove (4) in the radial gap (S) and having bent or angled end parts (10, 10') resting against the front and rear faces of the wheel rim (5). Seating wedges (11, 11') surround the upset head (8) and the set head (7) of the rivet (6) and are axially and radially clamped to wedge-shaped complementary surfaces (G, G') of the root end and of the respective insert (9, 9') by riveting. As a result, an improved radial and axial clamping of the rotor blades is achieved.

Abstract: A bearing arrangement is provided for rotors of jet engines with a bearing, which is mounted on a rotor carrier via a bearing carrier. In the event of failure, for example if the blade of a compressor rotor breaks, damage to or destruction of the rotor carrier or of the housing should be prevented by the fact that a breaking piece, which breaks under a defined load, is arranged concentrically between the rotor carrier and the bearing carrier. In this way, the transfer of extreme radial loads to the rotor carrier or to the rotor housing enclosing it is largely avoided, provided that the rotating member has not yet come to a standstill. The bearing arrangement is particularly of interest for turbo jet engines for aeroplanes, where for example, in the case of damage to a fan-rotor blade, the effect of a destructive force of a rotor running at high speed on neighboring housing areas can be reduced.

Abstract: The blades of a turbine rotor are secured to a rotor disk by inserting the blade foot with its serrations into a respective serrated groove in the rim of the rotor disk, whereby serrations of blade foot side surfaces mesh with corresponding serrations in the side walls of the grooves in the rotor rim to interlock the blade foot with the rotor disk in the radial direction. The axial locking of the blade foot in the groove is accomplished by a rivet connection having a rivet shaft positioned in a gap between the radially inwardly facing sole of the blade foot and the radially outwardly facing bottom of the groove. The rivet heads rest against washers or washer rings. If flat head rivets are used, these heads are received in countersunk recesses in the washers or washer rings that bear partially against the side surface of the rotor disk rim and partially against an axial end surface of the respective blade foot.

Abstract: A method for selectively protecting a component made of an iron-base alloy, cobalt-base alloy or nickel-base alloy with a protective arrangement which protects select areas of the component from aluminizing or chromizing during gas diffusion coating, wherein a first layer acts as an interlayer and a second layer acts as a getter layer for reaction gases. The method comprises the steps of depositing a first layer of slip cast material comprising oxide ceramic particles carried in a low-carbon, halide free, liquid vehicle; depositing a second layer comprising metal or a metallic slip, which comprises at least 50% by weight of the base metal of the component and all major alloy constituents of the component; aluminizing or chromizing by gas diffusion coating; and removing the protective arrangement from the component.

Abstract: The invention provides a fuel cell system with stacked fuel cells arranged in a fuel cell block, with an inlet for fresh combustion gas at the anodes on one side of fuel cell block and an outlet for the used combustion gas on the opposite side, as well as inlet for fresh cathode gas at the cathodes on another side of fuel cell block and an outlet for used cathode gas on the opposite side. A reforming device, which utilizes heat given off in the fuel cell reaction to reform the fresh combustion gas fed to the anode inlet of fuel cells, has an area provided with a catalyst. An inlet to the catalyst area receives fresh combustion gas to be reformed, which passes through the area containing the catalyst, in which the reforming process takes place, and exits through an outlet. The reforming device is designed as a heat exchanger located in the exhaust gas stream directly behind the fuel cell block.

Abstract: A fuel injection method and system for a Diesel engine, with an injection nozzle (1) supplied with a first fuel through a high-pressure pump (3) through a reservoir (2), wherein the engine can operate--rather than with the first fuel--with the second fuel in the form of pure fuel or of an emulsion of fuel and another substance that is insoluble in the fuel. Means are provided by which the second fuel is guided in a circuit through injection nozzle (1) and the second fuel, when the injection nozzle is actuated, is injected into the engine through the first fuel, which is under high pressure, from reservoir (2) to injection nozzle (1), with the mixture ratio of the fuel and additional substance in the second fuel being adjusted in the circuit.

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 supercharged multi-cylinder internal combustion engine is provided having exhaust recycling with air supply and exhaust outlet devices, variably controllable air intake and exhaust outlet valves, a first lubricating oil circuit, and an exhaust processing cylinder having a driven piston and a variable control for air intake and exhaust outlet valves on the exhaust processing cylinder. The air intake and exhaust outlet valves on the exhaust processing cylinder are each partially opened during a downward stroke of the driven piston of the exhaust processing cylinder by a control unit. A second lubricating oil circuit is provided for the exhaust processing cylinder.

Abstract: Relative differences between cylinder torque moments are individually determined for each cylinder in a multicylinder internal combustion engine in which individual cylinders may be switched off. The torque moment differences are ascertained indirectly when the engine is subject to inner and outer resistance moments and to the inertia moments of all masses to be accelerated. Under these conditions the crankshaft r.p.m. is measured and the r.p.m. signal is split into components for the individual cylinders by applying the superposition principle of linear systems. The first r.p.m. is determined when all cylinders work. The second r.p.m. is determined with all cylinders but one working and the second r.p.m. is deducted from the first r.p.m. Gradually one cylinder after the other is switched off and the respective differences in the r.p.m. are ascertained. These r.p.m. differences are allocated to the ignition compression and are compared with a difference r.p.m. of a reference cylinder.

Abstract: A model for a casting mold, particularly for the casting of blade wheels for turbo-engines, includes multiple cores which can be fitted into one another. The cores have exterior rings, portions of blade duct cores and connector plates. The portions of the blade duct cores supplement one another.

Abstract: In a repair method for lengthening turbine blades having undersized blade lengths, a sheet metal strip is preformed in a U-shape and is then used as a support form, for which it is tightly pressed against the upper blade contour in a force-locking and exactly contour-fitting manner by an outer synthetic material surround molding. The sheet metal strip is arranged in such a manner that it protrudes beyond the blade tip and protrudes out of the pressing synthetic material mass. In order to lengthen the turbine blade, the space within the sheet metal strip that protrudes beyond the blade tip is filled by laser deposit or build-up welding. Furthermore, a particular support form is provided for carrying out the lengthening of the turbine blade, and a method for producing the support form is described.

Abstract: A structural component which consists of a fiber-reinforced, composite material is provided with a protective coating against erosion. The protective coating includes an adhesion-promoting, intermediate layer on the component, an electrically insulating baked, inorganic lacquer layer for protection against erosion and an electrically conducting covering layer, for protection against lightning strikes. The covering layer consists of a baked and compressed inorganic lacquer and the lacquer of the lacquer layer and of the covering layer is baked on the component below the temperature which causes damage to the structural component or below the softening or decomposition temperature of the component. The protective layer is advantageously used for the external components of propulsion units, such as housings, nose cones or fan blades.

Abstract: A brush seal assembly is provided for sealing off spaces on a circumferential gap which are acted upon by pressure in a different manner, particularly between an engine casing and an engine shaft. On the engine casing, a holding device for a bristle bundle is provided from which the bristle bundle is guided between circumferential webs sealingly against the engine rotor and, with respect to the one web facing the high pressure side, forms an axial gap in the circumferential direction. In the axial gap, a covering ring for the bristle bundle is arranged in an axially and radially movable manner which is operated by the differential pressure and can be displaced with respect to the bristle bundle. With respect to the ends of the webs surrounding the engine shaft at a distance, the covering ring is to project out of the axial gap and surround the engine shaft by means of a radial sealing gap.

Abstract: A PC board to be populated with electronic components, for insertion into the housing of an electronic device, has a core made of two metal plates connected together and spaced apart by reinforcing ribs, said plates being provided with a copper-invar layer and with a cover layer formed by several layers of polyimide film. To achieve high rigidity and good heat transfer, the metal plates are made of aluminum or an aluminum alloy and are fastened in the housings by means of gibs and cotters.

Abstract: Two components such as pipes having radial end flanges with conical flange clamping surfaces are clamped together by a clamping ring having at least two ring sections with conical ring clamping surfaces engaging said conical flange clamping surfaces when clamping screws passing through section ends are tightened. The ring sections have an inner ring radius (RR) slightly larger than a respective flange radius (FR) for providing a positive but gradual engagement between said conical surfaces when said ring sections are clamped together for example by threaded bolts or screws at ring section ends.

Abstract: Injection system for the intermittent introduction of a fuel-liquid mixture into the combustion spaces of an internal-combustion engine with a common-rail pressure reservoir. Lines (16, 30) lead to control spaces (15, 22) of control valves (1). Control space (15) is joined selectively with the common-rail pressure reservoir or a line (18) with a pressure p0 or a line with a pressure p1 for control of injection quantities of the fuel-liquid mixture. Control space (22) is joined selectively to the common-rail pressure reservoir or to a line with pressure p2 or to a line (33) with pressure p0 for control of the liquid fraction of the injection quantity.