Abstract: The invention is directed to a method for producing a corrosion-resistant and oxidization-resistant layer that is applied onto a component part, whereby the method can be simply and cost-beneficially implemented in fabrication-oriented terms and comprises the steps: a) producing a slip by mixing powder containing at least one of the elements Cr, Ni or Ce with a binding agent; b) applying the slip onto the component part; c) drying the slip at temperatures from room temperature through 300° C.; and d) alitizing the slip layer.

Abstract: A method for producing matched surfaces on rotor units with integral blades comprising a hub and at least one blade ring, by removing by machine after integral joining with component overmeasure in the area of the joining zone, whereby at least one actual surface is acquired by measuring method, and a surface matching it, is produced. Acquisition by measuring method and production take place on a process machine in one clamping of the rotor unit. The desired surface of each processing area is provided in the form of stored data. Starting from at least one measured actual surface, a matched surface is produced beyond the joining zone, with the surface everywhere adjoining the actual surface and/or a so-called repair surface of which there is at least one, without any kinks or steps at a specifiable minimum curvature.

Abstract: The invention pertains to differential pressure transducers for gas turbine motors, for measuring variable pressure differences within a medium or between different media. The differential pressure transducer is constructed as a linear displacement sensor according to the linear variable displacement transducer (LVDT) principle, and has a ferromagnetic core that can be moved in a translatory manner, a spring element for the set position of the core given nominal differential pressure, a primary coil and two secondary coils arranged in succession axially over the length of the stroke range of the core, and a tubular housing having a delivery connection on both sides of the stroke area of the core.

Abstract: A brush seal for sealing a rotor against a housing. The brush seal includes a front panel and a supporting plate attached to the housing wherein a number of bristles are disposed between the front panel and supporting plate. A seal housing that defines a fit surface is formed by cold joining the front panel and supporting plate. The front panel or the supporting plate include a beaded lip for firmly joining the front panel to the supporting plate.

Abstract: A brush seal for sealing a rotor against a housing. The brush seal includes a number of bristles that are each attached to the housing by a clamp member. The clamp member is positioned between a supporting plate and a front panel. The supporting plate has a supporting section for supporting the bristles in an inclined position.

Abstract: A fuel metering system for a turbojet engine includes (1) a pump-supplied feed pipe; (2) a supply pipe to the engine; (3) a recirculation pipe; (4) a main metering valve; (5) a pressure control device for the main metering valve; (6) an emergency device for an unintentional opening of the main metering valve; and (7) an automatic pressure limiting device for the pipe system. Control-related connections of the main metering valve and the emergency device exist to an electronic engine controller. The pressure control device and the emergency device are combined in a recirculation valve and are controlled by the engine controller.

Abstract: A method and an electrical circuit for converting highly structured analog signals arriving with variable pulse frequency into trigger pulses with an electronic circuit that locks the trigger pulses for a specific time, which is referred to as a dead time. The dead time being adapted to the current pulse frequency of the analog signals.

Abstract: A cover for a component surface to provide protection against hot metal splashes, during processing of the component itself or a component in its vicinity. The material for the cover is an elastic rubber plastic of adequate temperature stability which can be fixed to, and removed from, the component by adhesion/sticking. The surface geometry facing the component, of the cover is exactly complementary to the geometry of the component surface. The thickness of the cover is matched to the energy content of the expected metal splashes with the highest energy, and maintains a specified minimum dimension at every position.

Abstract: A blade with optimized vibration behavior for turbomachinery components in an axial-type construction having a solid, thin and elongated blade body, the blade, at a distance from both a radially inner blade body end and a radially outer blade body end, having at least one plate-like rib which is disposed in an upright position on the blade body surface and is oriented in a neutral manner with regard to the flow and is also integrally connected to the blade body on one of the suction and pressure sides of the blade.

Abstract: A pre-mixing combustion chamber (8) for a gas turbine is disclosed which includes a main stage with at least one pre-mixing chamber and a combustion chamber fashioned at least partly dynamically balanced relative to its longitudinal axis with a main combustion zone (3) and an after-combustion zone (5) placed downstream, whereby the at least one pre-mixing chamber discharges into the combustion chamber in the region of the main combustion zone tangentially producing twisting action. The pre-mixing chamber also includes a pilot stage (4) with a pilot injection means, whereby the main combustion zone in the combustion chamber proceeds essentially coaxial to the after-combustion zone, and the pilot stage is arranged at that end of the combustion chamber remote from the after-combustion zone.

Abstract: In a gas phase coating process for coating turbines blades or housing parts, one or more workpieces to be coated are arranged in a container that is heated. Propellant is supplied to the container via a propellant pipe. A donor substance is arranged at the floor of the container together with an activator and forms a coating gas that is circulated pulse-like in the interior of the container by means for circulation, for example, a Venturi nozzle from which the propellant emerges.

Abstract: The invention concerns a device for the precise positioning of a measurement probe along a probe axis A and which can rotate around this axis. By the coaxial arrangement of adjustment units for rotating and longitudinal displacement of the probe as well as by an rpm step-down gear arranged therebetween, a compact construction of the device is made possible and a coaxially situated passage is kept free, through which the probe shaft can be inserted and removed.

Abstract: A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by means of beam cutting and is connected therewith.

Abstract: A hollow structural part having an internal hollow space, preferably a blade for a turbodrive, is made of a metal alloy with a columnar structure solidified in an oriented manner with longitudinally extending grain boundaries. A series of holes are laser drilled in the blade to connect the outer surface of the blade with the hollow space. The blade is formed with a single crystal column in the region where the series of holes are formed so that the holes are away from the grain boundaries. Such structural parts are preferably used as the blade of a rotor and the laser drilled holes serve for supply of cooling air to the leading edge or pressure region of the blade or for influencing the position of the boundary layer on the suction side of the blade, or the laser-drilled holes are shaped as outflow openings for air to intensify a cooling film for increasing the blade efficiency.

Abstract: The present invention relates to a testing apparatus for testing vibration damping elements of moving blades, with a mounting means to be attached to an oscillating apparatus, whereby a damping element to be tested is to be arranged between the mounting means and the blades, and at least one extendable body that can be charged with pressure is arranged between the mounting means and the damping element.

Abstract: A protective coating is applied on a local region of a surface of a component on which direct deposit of a uniform coating of protective material is impeded due to a complex shape of the region to be covered or inaccessibility or inability to apply a uniform deposition or electrical field therefor. The coating is formed by a foil having a solder backing layer with a thin layer of uniform thickness of the protective material electrolytically deposited on the backing layer, the foil being cut to size corresponding to an area of the local region of the component to be protected. The cut to size foil is positioned and held on the local region of the component to be protected; and fixed in place by melting the solder to fuse the foil to the component and cover the local region.

Abstract: Apparatus for vibration damping a rotor rotatably supported in a stationary housing by a bearing whose retainer housing is concentrically engaged in the stationary housing in an axial position by elastic elements. In order to avoid or reduce vibrations produced by rotation of the rotor particularly resonance vibrations, an oil space is formed between the stationary housing and the bearing retainer which is sealed at its ends by axially spaced sealing rings. An inlet channel is provided in the stationary housing for supplying oil under pressure into the space and outlet channels for the oil are formed in the bearing retainer in the vicinity of the sealing rings. The oil discharge channels are provided with constricted regions whose flow cross-sections and lengths are related to the flow cross-section of the oil inlet channel such that the oil discharge channels act as chokes or throttles.

Abstract: A brush seal for sealing a gap between two spaces at different pressures on opposite sides of a rotor and a stator. The brush seal is formed as a plurality of bristles and the bristles are mounted in the stator to project radially therefrom, across said gap, to contact the rotor. A clamping ring clamps a stack of the bristles around an annular core in U-shaped fashion with legs of the bristles extending through an annular slot towards the rotor. The clamping ring includes a C-shaped section which clamps the bristles against the core and reverse bend portions at opposite ends of the C-shaped section. The reverse bend portions are axially spaced from one another and form the annular slot through which the legs of the bristles extend.

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 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.