Abstract: An axial turbomachine including a rotor blade cascade is provided. The rotor blade cascade includes rotor blades each including front edge, a radially outer free blade tip and an annular enclosure enclosing the rotor blade cascade with an annulus inner side by means of which the annular enclosure is arranged directly adjacent to the blade tips to give a radial gap between the enveloping ends of the blade tips and the annulus inner side. The rotor blades include a radial projection in the region of the front edge on the blade tip and the annular enclosure has an annular radial recess in the annulus inner side, arranged at a radial distance from the ends of the blade tips, such that in the main flow direction of the axial turbomachine the line of the radial projections on the side facing the radial gap matches the line of the radial recess.

Abstract: A compressor blade for an axially permeated compressor, preferably of a stationary gas turbine is provided. The camber line of the blade tip side profile of the blade of the compressor blade includes at least two inflection points for reducing radial gap losses. By means of two inflection points, there is a concavely designed suction side contour segment in a segment from 35% to 50% for the suction side contour, and a convexly implemented pressure side contour segment for the pressure side contour. It is possible by means of the geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor including the compressor blades.

Abstract: An arrangement with a ring diffuser for an axial turbomachine, for example for a gas turbine, is provided. The ring diffuser includes an outer wall and with an inner wall coaxial thereto, between which a diffuser duct extends in ring form along an axial extent so as to diverge from an inflow-side end to an outflow-side end, the inner wall and the outer wall in each case including a wall surface delimiting the diffuser duct. In order to specify a diffuser duct which is adapted to an inflow uneven along the circumference and by means of which a specially efficient conversion of kinetic energy into static energy is possible, the wall surface which delimits the diffuser duct on the inlet side is rotationally asymmetrical.

Abstract: The invention relates to a control device for a brake system of a vehicle (10; 92; 132; 238), said vehicle (10; 92; 132; 238) having a supporting structure (222; 240) and a cabin (224; 242) that is supported by the supporting structure (222; 240) and has at least one driver's seat (226). The control device is located outside the cabin (224; 242) on the supporting structure (222; 240) and the control device has additional functionality for controlling an electronic air spring system.

Abstract: A gas turbine engine having an axial flow compressor, an annular combustion chamber, a turbine, and a diffuser. The diffuser includes a flow-dividing element formed by an inner deflecting flank and an outer deflecting flank that divides a compressed gas flow into two partial flows at a branching point. The two deflecting flanks define: an angle of less than 90° along at least a portion of the deflecting flanks, and an angle between 15° and 90° between the deflecting flank angle bisector and the turbine longitudinal axis. The deflector also includes a main deflecting region arranged upstream of the branching point and directed at an acute angle from the turbine longitudinal axis toward an inner combustion chamber shell.

Abstract: Disclosed is an annular flow duct for a turbomachine, the flow duct arranged concentrically about a machine axis running in the axial direction and defined by a boundary wall of circular cross section for directing a main flow, wherein the boundary wall has a plurality of return flow passages distributed over its circumference and through which in each case a partial flow is detached from the main flow at a bleed position and returned to the main flow at a feed position situated upstream of the bleed position, and having aerofoils, arranged radically in the flow duct, of a blade ring, the aerofoil tips of which lie opposite the boundary wall, with a gap formed in each case, wherein the aerofoils are movable in a predetermined rotation direction along the circumference of the boundary wall. Furthermore, a compressor which is insensitive to pumping and flow separations, as viewed in rotation direction, the bleed position of each return flow passage lies upstream of the corresponding feed position.

Abstract: A ring diffuser for an axial turbomachine is provided. The ring diffuser includes an outer wall and an inner wall coaxial thereto, between which a diffuser channel extends in a ring shape along an axial extension from an inflow-side end diverging to an outflow-side end, wherein the inner wall and the outer wall each include a wall surface bounding the diffuser channel. In order to specify a diffuser channel that is tailored to an inflow that is uneven along the circumference and that facilitates a particularly efficient conversion of kinetic energy into static energy, a rotationally asymmetric wall surface bounding the diffuser channel on the inlet side is provided.

Abstract: An axial turbomachine including a rotor blade cascade is provided. The rotor blade cascade includes rotor blades each including front edge, a radially outer free blade tip and an annular enclosure enclosing the rotor blade cascade with an annulus inner side by means of which the annular enclosure is arranged directly adjacent to the blade tips to give a radial gap between the enveloping ends of the blade tips and the annulus inner side. The rotor blades include a radial projection in the region of the front edge on the blade tip and the annular enclosure has an annular radial recess in the annulus inner side, arranged at a radial distance from the ends of the blade tips, such that in the main flow direction of the axial turbomachine the line of the radial projections on the side facing the radial gap matches the line of the radial recess.

Abstract: An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.

Abstract: The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.

Abstract: A system includes a board having opposing surfaces and at least one leg connected to one surface of the board through a first pivotable fitting to allow the board and the leg to move between a first position wherein the board and the leg are substantially parallel and a second position wherein the board and the leg are substantially perpendicular. The system also includes a locking mechanism secured to the board through a second pivotable fitting at a first end and configured to rotate at a second end opposite the first end between a storage position extending parallel with the board and a work position extending perpendicular to the board.

Abstract: The invention relates to a gas turbine, comprising an annular combustion chamber and an upstream diffuser, with a throughflow essentially parallel to a turbine longitudinal axis, at a distance from said axis at least partly less than the annular combustion chamber, in which a compressed gas may be divided into several partial flows at a branching point, whereby at least one of the partial flows is a cooling gas flow. A main deflection region is provided in said diffuser, directed at an angle to the turbine longitudinal axis towards the annular combustion chamber.

Abstract: A pivotable board with at least one leg is provided. The leg is connected to the board with a pivotable fitting. The pivotable fitting has a pivoting axis which is disposed in a slanted position with respect to the board and on which the leg or the board are pivotally mounted.

Abstract: Disclosed is an annular flow duct for a turbomachine, the flow duct arranged concentrically about a machine axis running in the axial direction and defined by a boundary wall of circular cross section for directing a main flow, wherein the boundary wall has a plurality of return flow passages distributed over its circumference and through which in each case a partial flow is detached from the main flow at a bleed position and returned to the main flow at a feed position situated upstream of the bleed position, and having aerofoils, arranged radically in the flow duct, of a blade ring, the aerofoil tips of which lie opposite the boundary wall, with a gap formed in each case, wherein the aerofoils are movable in a predetermined rotation direction along the circumference of the boundary wall. Furthermore, a compressor which is insensitive to pumping and flow separations, as viewed in rotation direction, the bleed position of each return flow passage lies upstream of the corresponding feed position.

Abstract: The invention relates to a pivotable board 1, preferably of a table, provided with at least one leg 2. The leg 2 is connected to the board 1 by means of a pivotable fitting 5. The pivotable fitting 5 has a pivoting axis which is disposed in a slanted position with respect to the board and on which the leg 2 or the board 1 are pivotally mounted.

Abstract: Apparatus for generating an additional voltage drop to reduce the dangerously high voltage drop across an ESD-sensitive ultra-thin gate oxide of a MOS input device. The apparatus are designed to minimally interfere with the circuit requirements for normal operation. Specifically, The MOS input device is coupled between a pad and the logic core circuitry of the IC. In one embodiment, a voltage-drop element, such as a resistive element, inductor, or pass-gate MOS device, is coupled between the source of the MOS input device and a voltage line. Alternatively, the voltage-drop element may be coupled to the bulk, gate, and/or drain of the MOS input device. In another embodiment, the voltage-drop device may be an active device, which pumps up the potential at least one of the source, bulk, or drain regions of the input device from the ESD clamp.

Abstract: An ESD protection circuit includes a SCR and a switching means, such as a MOS transistor connected to the SCR so that the SCR is turned on by the switching means to allow an ESD pulse to pass from a Pad line to a grounded VSS line and thereby dissipate the ESD pulse. The SCR is connected between the Pad line and the VSS line. One MOS switching means is connected between the Pad line and the SCR and has a gate which is connected to a VDD line which maintains the switch in open condition during normal VDD bias conditions. An ESD pulse applied to the Pad line, the switch is preconditioned in ON mode allowing the SCR to be predisposed to conduction to allow the ESD pulse to flow to the VSS line.

Abstract: A current ballasting circuit for an ESD protection device couples nonintersecting conductive strips between a common contact pad and the contact electrodes of the ESD protection device. The connecting strips form respective electrically isolated ballasting resistors between the external contact pad and the contact electrodes of the ESD device. In addition, lateral resistances are formed between the contact strips which enhance the operation of the multiple ballasting resistors. The conductive strips may be made from metal, polysilicon or by a vertically meandering series connection of polysilicon layers, metal layers and interconnecting vias. The lateral resistance between the parallel conductive paths may be enhanced by segmenting both the drain and source electrodes. In one example, the gate electrode of an MOS ESD device extends locally between each pair of strips to segment the drain and source regions.

Abstract: Apparatus for providing electrostatic discharge protection having an nMOS transistor with bias simultaneously applied to the gate and the p-well of the nMOS transistor. A bias circuit is fabricated using a plurality of the Zener diodes. The double bias allows for a relatively high gate voltage to be applied to the nMOS transistor enabling the nMOS transistor to be biased to optimum conditions for bipolar snapback.