Abstract: A device for detecting and identifying wearable identification units (20) for users at a predetermined distance around a central station (2). The central station (2) has a transmitter (4) and a receiver (6) for electromagnetic signals and a control unit (8), which initiates the sending of a polling signal at predetermined time. The time may be based on multiples of intervals.

Abstract: An arrangement for adjusting guide blades by thermal expansion has an expansion rod which has a significantly different coefficient of linear expansion with respect to the supporting housing and is aligned in the circumferential direction of the turbo-engine and is connected with an adjusting ring by way of a step-up lever. As a result, a guide blade adjustment can be achieved easily as a function of the working gas temperature.

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 turbo-engine constructed to maintain the radial gap between the rotor and casing. The casing of the engine includes an inner casing having shell-shaped parts with centering seats and adjacent parts are secured a given distance apart axially.Each shell-shaped part comprises a plurality of angular segments which are secured together by fasteners aligned in a plane extending perpendicularly to the axis of rotation of the rotor.

Abstract: An apparatus for optimizing blade and sealing slots of a compressor of a gas turbine comprising a rotor including a plurality of axially spaced discs and rotor blades on the discs and a stator casing surrounding the blades and forming clearance slots therewith. The blades and stator casing form a path for flow of air in a main stream in which the air is compressed and discharged at a discharge end of the compressor. A seal at the last of the discs opposes outflow of compressed air thereat and forms sealing slots through which leakage air can flow from the main stream. The leakage air is conveyed from the compressor and a portion thereof is diverted as a secondary stream in a direction opposite the main stream of air flow in the compressor, and discharged towards the last rotor disc and at least the next adjacent rotor disc to flow thereon.

Abstract: The spreading of a so-called titanium fire is prevented in a turbine engine in which at least one turbocomponent, e.g. the compressor, including its stator inner and outer housing sections and the rotor are made substantially or completely of titanium or of a titanium alloy, by a heat-dissipating layer on an outer housing section surrounding an inner housing section directly facing the rotor. A radial spacing is provided between the inner and outer stator housing sections. The heat-dissipating layer of a highly heat-conducting material covers the inner surface of the outer stator section and permits the concentrated thermal energy of, e.g., a glowing titanium particle, after is has burned through the stationary inner stator section or wall, to be dissipated fast enough to prevent an ignition of the outer stator section to thereby restrict the damage to the inner stator section.

Abstract: In machine assemblies made of titanium or titanium alloys, such as turbo-compressors, where at least one rotating member is arranged directly adjacent to at least one stationary structural titanium member, the radially outer contours or surfaces of a radially inner stationary member, as viewed relative to the respective axis of rotation, are provided with a surface layer of a highly heat-conductive material. This heat-conducting layer enables the heat of friction generated when a fragment is jammed inbetween a moving and a stationary member, to be dissipated extremely rapidly over a large surface area to keep the titanium casing material from reaching the ignition temperature, whereby the ignition of titanium fires is prevented.

Abstract: A seal between two machine parts for sealing separate spaces at different pressure from each other comprising a brush seal extending at an acute angle to a principal axis of at least one machine part for use in spatially constricted constructions with small clearances, particularly fluid-flow engines such as airplane jet engines, for sealing rotating or stationary parts.

Abstract: An apparatus for ventilating a liquid tank in which ventilation pipes are arranged so that the orifice of at least one ventilation pipe is above the liquid level and the orifice of at least one ventilation pipe is below the liquid level. The remaining ends of the ventilation pipes connected to separate chambers which are sealed off from the tank interior. These chambers are associated with a rotary slide valve which can be controlled by the flight attitude. The control slots of this valve are staggered (offset) in such a way that with simultaneous free flow passage via at least one ventilation pipe located above the liquid level, flow passage via at least one ventilation pipe located below the liquid level is blocked.