Abstract: A flow-guiding body is designed as a pointed, substantially conical molded shell. The projection of its base surface is formed by a straight line and by a curve that interconnects the ends of the straight line. The curve forms no significant angles. The molded shell faces with its point the fluid flow that hits its outer side and may be used as a mixing element for gaseous fuel and air, as an air sprayer with flame-holder, as a mixing element for admixed air in combustion chambers, as a swirling element or as a shell-shaped air sprayer combined with a fuel film generator or a fuel pressure spraying nozzle.

Abstract: A heat shield for a gas turbine annular combustion chamber having a plurality of effusion holes (5), the central axes of which are inclined towards the heat shield surface and over which cooling air can penetrate from the rear to apply a film of cooling air to the hot surface. The surface is subdivided into sectors (7) and transition areas (10) between the sectors, the central axes of the effusion holes essentially being arranged in parallel to each other in a given sector or transition area. In addition, the central axes (6) of the effusion holes (5) located in each surfaces sector (7) are parallel to one another and extend substantially toward the associated corner area (8) and, in sections, extending approximately in a direction the same as the fuel combustion air swirl (4) in this sector (7).

Abstract: In order to cool the hot surface of the heat shield that surrounds the burner of a gas turbine annular combustion chamber as efficiently as possible, especially in the vicinity of the burner throughflow opening, a cooling air stream that escapes through a ridge that runs around the edge of the throughflow opening is guided by a guide rib in the direction of the throughflow opening. This guide rib is aligned essentially parallel to the ridge and on the combustion chamber side has an end that is bent in such fashion that the cooling air stream that flows into the gap between the ridge and the guide rib is deflected thereby in the direction of the hot surface of the heat shield.

Abstract: The boundary layer stimulation by blowing flow fluid into the proximity of the separation region on turbine blades is disclosed. In order to prevent a laminar boundary layer separation, the blowing-in takes place in the form of intermittent fluid pulses. A particularly advantageous arrangement for an axial turbomachinery rotor disk is provided for this purpose, on the end face of which a stationary ring is provided which has at least one passage opening with which inlet openings for the blade fluid ducts which are provided in the disk which passes by and by way of which the blowing into the proximity of the separation region takes place, become periodically congruent.

Abstract: A fixed bearing for a radial or diagonal flow compressor is guided in a damping bush whose axial position can be fixed by means of a reconciling plate to establish a desired running gap with respect to the compressor housing. The damping bush has a receiving device for a supporting element which rests against the reconciling plate, such that the supporting element and the reconciling plate are removable when the damping bush is disposed in the compressor housing. When the rotor is mounted, the required thickness of the reconciling disk can be determined and this reconciling disk can then be inserted without removing the rotor or the damping bush for the adjustment of the desired running gap.

Abstract: An aircraft gas turbine has a barrier air flow produced by the fan or a low-pressure compressor which passes continuously through the compressor bearing chamber, while the turbine bearing chamber is supplied with barrier air by the high-pressure compressor. The barrier air flow drawn from the turbine bearing chamber passes into an ejector which is also connected to the compressor bearing chamber so that, when the pressure is insufficient, the barrier air flow is drawn-off by the ejector.

Abstract: A cooled turbine blade is described that has shroud band segment in which three cooling air branch ducts extend essentially perpendicularly to the longitudinal axis of the blade as well as in the circumferential direction of the blade reinforcing band. Cooling air bores branch off the cooling air branch ducts and lead out on the surface of the shroud band segment and form film cooling holes there. A first branch duct is supplied with cooling air by a blade cooling duct which is situated in the leading area, while a second branch duct is connected with another blade cooling duct 13 and the third branch duct is connected with the second branch duct 14.

Abstract: An arrangement for holding of assembly that can be mounted on structural parts, particularly of a radiator module on the body of motor vehicles. Connecting elements used for holding the assembly are constructed to be guided to the structural part while interacting in a self-locking manner with the structural part.

Abstract: The invention is directed to a method of checking the tightness of a tank-venting apparatus for a motor vehicle having a fuel tank and an internal combustion engine including a lambda controller and an air intake pipe. The tank-venting apparatus includes an adsorption filter, a supply line interconnecting the adsorption filter and the fuel tank, a connecting line interconnecting the adsorption filter and the intake pipe and a tank-venting valve mounted in the connecting line between the adsorption filter and the intake pipe. The method includes the steps of: measuring the pressure difference between pressure in the tank and ambient pressure; when the tank-venting valve is opened, determining whether the pressure difference increases above a threshold value and whether a lean correction by the lambda controller is required; and, drawing the conclusion that the tank-venting apparatus leaks when neither a lean correction is determined nor the pressure difference exceeds the threshold value.

Abstract: The invention concerns an aerodynamic plain bearing for shafts (1) rotating at high speeds, with a bearing housing (4) having a cylindrical bore (3) and with a tangentially attached, elastic and damping structure (2) having segments (2" or 2a), which is supported at a plurality of circumferential points (2') in bearing housing (4) and forms a multiple converging running gap (6) with shaft (1) and damping gap (5) with bearing housing (4). A minimum number of components are used and radial installation space is also minimized. Segments (2" or 2a) of the structure are thin-walled, elastic sleeve sections with a uniform or profiled wall thickness and a low coefficient of friction, as from titanium nitrite, and simultaneously act as damping and spring elements.

Abstract: A liquid cooling circulation system for power and working machines (especially internal combustion engines) contains an air-separating tank (17) in a by-pass vent line (14) which is arranged at the high point (5') of the radiator inflow (5). A fill inlet (19) with connecting openings (5" and 17') to the radiator inflow (5) and air-separating tank (17) have a closure cover (20) which closes off these connecting openings with respect to one another. Excess pressure, vacuum and vent valves (21 and 22) are contained in the closure cover 20 which controls a line connection (25) to an atmospheric, or to an excess pressure expansion tank (27). A highly effective venting function in conjunction with an engine operation at strong rotational speed changes exists, since the line connection (25) is opened at least at low cooling medium temperature by means of a temperature-controlled vent valve (22).