Abstract: An athlete training device includes a first sensor pad for signaling when a first object has been removed from the first pad and a second sensor pad for signaling when an athlete's hand has been removed from the second pad. A third sensor signals when the athlete has made contact with a second object. A control device receives the signals from the pads and third sensor and determines a first elapsed time from when the first object is removed from the first pad and the athlete's hand is removed from the second pad. The control device also determines a second elapsed time from when the athlete's hand is removed from the second pad and the athlete makes contact with the second object and then outputs a signal for displaying the first and second elapsed times.

Abstract: A hydraulic seal arrangement 5 between two shafts 1, 2 rotating relatively to each other, particularly in the same sense of rotation, of especially a gas turbine engine, where the radially outer shaft 2 has an annulus 5a extending radially outwards on its circumference into which the radially inner shaft 1 projects with a fin 5b that extends radially outwards on its circumference, said annulus 5a can be filled siphon-fashion through an inlet area 5d under centrifugal effect with a hydraulic fluid in the area of the free end of the fin 5b as the shaft(s) 1, 2 rotate(s), with an opening 7 branching off from an annulus area 5e for the discharge of hydraulic fluid, the annulus 5a being formed by a first outer shell part 8 and a second outer shell part 9 situated on the shaft 2.

Abstract: In a machine tool comprising a spindle mounting slide which is driven by a linear electric motor and which runs in a vertical direction in a slideway, the slide is equipped with a counterweighting device comprising an elastic element and a roller chain, the rigidity of the chain being less than the rigidity of the elastic element.

Abstract: In an automatic machine tool (1) comprising a spindle mounting slide (4) which is driven by a linear electric motor (9) in a vertical direction (V) in a slideway (8), the slide (4) is equipped with a counterweight device (13) comprising a cylinder (19) within which there slides a piston 17. The cylinder (19) and the piston (17) form a first balancing chamber (31) and a second counterbalancing chamber (32), the second counterbalancing chamber (32) being connected to a circuit (33) for feeding a fluid (34) under pressure.

Abstract: A heat shield arrangement includes several tiles 1 and several fasteners 6 for attaching the tiles at a spaced distance to a wall 2 to form an interspace 4 between the wall and the tiles which can be supplied with cooling air. At least one sealing element 3 is positioned between adjacent tiles 1 to provide a seal between rims 5 of the adjacent tiles 1. The rims 5 of the tiles 1 which are to be sealed are maintained at a spaced distance from the wall 2 by the fasteners 6 and the sealing element 3 is positioned remotely from the wall 2 and in abutment with the rims 5 of the tiles 1, with the sealing element 3 being allowed to float over the rims 5.

Abstract: A device for the injection of fuel into the combustion chamber of a gas turbine includes at least one swirler (1) arranged in an air path with at least one swirler vane (2) and with at least one fuel injection nozzle (3), wherein the fuel injection nozzle (3) is arranged in a wake area of the swirler vane (2) and is separate from the swirler vane (2).

Abstract: Packets are overwrapped in a cellophaner unit equipped with a wheel by which the packets are directed through an assembly station together with leaves of wrapping material and toward a folding station where the leaves are bent around the packets, also a suction roller set in rotation continuously and tangentially to the wheel, on which the leaves are held by suction while advancing along a first path extending between a cutter device and the assembly station; the wheel is furnished with peripheral carriers supporting the single packets, each equipped with gripper jaws positioned to take up one end of a leaf held on the adjacent roller and detach it by degrees from the relative suction surface before effecting an initial overwrapping step of folding the leaf partly around a relative packet.

Abstract: An automatic transmission includes a stator support shaft having an internal axial bore for receiving an input shaft, a forward engagement portion for engaging a stator of a torque converter, and a central engagement portion for engaging a stator support and transferring to the stator support substantially all of a torque load imposed on the stator support shaft by the stator. A rearward portion of the stator support shaft is positioned rearward of the central engagement portion. An oil seal groove is positioned in the internal axial bore of the rearward portion to receive an oil seal to seal between the stator support shaft and the input shaft.

Abstract: A gas turbine with a compressor area has a rotor shaft 2 to carry rotor blades 1 and a casing 4 to carry stator vanes 3, with the related rotor blades 1 and stator vanes 3 forming an axial clearance space 5 between one another, wherein, in the area of the axial clearance space 5, at least one wall of the rotor shaft 2 and/or of the casing 4 is provided with an arrangement of fins 6 which are inclined against the axial direction.

Abstract: A stator vane span attachment for a gas turbine having a casing 1 in which several stator vane spans 2 are located, wherein means 3 are provided for restraining the stator vane spans 2 against the casing 1.

Abstract: An oil separator includes a casing 1 and a rotor 2, said rotor being arranged rotatably within said casing and having a flow chamber 3 through which oil-laden air 4 can pass, with porous material being arranged in the flow chamber 3. At least one unit of porous material is arranged in the flow chamber 3 which includes outer layers of a porous metal 6 and an interlaid layer 7 comprising fibre material.

Abstract: The invention relates to a turbine blade of a gas turbine with at least one cooling excavation 2 which connects an interior 3 and the surface 4 of the turbine blade 1, characterized in that a mouth 5 of the cooling excavation 2 is provided with a protrusion 6 in its downstream area.

Abstract: This invention relates to an arrangement for the cooling of the casing 1 of an aircraft gas turbine with a bypass duct 2 and at least one cooling air tube 3, this cooling air tube 3 having its inlet 4 arranged in the bypass duct 2 and entering at least one cooling air chamber 5 for the supply of cooling air to the casing 1, characterized in that a movable air deflector 6 is arranged in the bypass duct 2 upstream of the inlet 4 of the cooling air tube 3.

Abstract: An air intake system of a propeller-turbine engine with a propeller gearbox 1 in in-line arrangement, includes one or more intake units 3 arranged essentially below a nacelle fairing 2 of the propeller-turbine engine with each intake unit 3 being related to a elbow diffuser 19, a shock diffuser 4, and a rotationally symmetric attenuation chamber 5 into which the respective shock diffuser 4 issues and which is connected to the compressor inlet 6 of the propeller-turbine engine.

Abstract: The invention relates to a method for the fuel supply of an aero gas turbine installed in an aircraft and to a fuel supply system. In order to avoid negative effects by out-gassed air in the fuel lines, the invention provides for an increased flow rate of the fuel in the fuel lines and for a fuel return line (6) for the return of excess fuel to the tank.

Abstract: A shroud for the support of vane roots 1 of variable stator vanes 2 in the high-pressure compressor of a gas turbine includes a forward shroud segment 3 and a rearward shroud segment 4, each with an axially open annulus 5 forming an essentially U-shaped cross-section and with a plurality of axial assembly holes 6, wherein an annular cover 7 is arranged in the area of the opening of the annulus 5 which is provided with assembly openings 8 and tubular supports 9 are provided in the area between the assembly openings 8 of the cover 7 and the associated assembly hole 5 of the shroud segments 3, 4.