Abstract: A cooled component, such as a turbine blade for gas turbines is provided, having efficient internal cooling, with an interior cooling passageway having a round cross-section. A row of feeding holes for the coolant are arranged spaced from each other in the direction of the longitudinal axis of the cooling passageway and originating from a common coolant channel. Each of the feeding holes intersects the cooling passageway tangentially. The ease of manufacturing the cooling component is improved in that the majority of the feeding holes have a hole diameter that is smaller than half of the hydraulic diameter of the cooling passageway, and selected feeding holes have a hole diameter that is greater than half of the hydraulic diameter of the cooling channel.

Abstract: In a hollow-cast component, a core opening (13) created during manufacturing is closed with a closure piece (14). This closure piece is located inside a recess (15) in the component, whereby the recess is arranged so that it is imbedded completely in the cast material, and completely covers the core opening. Because of this installation, the closure piece is fixed in a form-fitting manner in the direction of two spatial axes, so that the closure piece only needs to be secured with an additional joint in the installation direction. It is preferred that the installation direction is normal in relation to the direction of maximal stress of the closure piece, so that a joint is subject to a relatively small stress and therefore can be produced with little expenditure and a high degree of operational safety.

Abstract: In an air-cooled turbine blade (10) which has a shroud-band element (11) at the blade tip, the shroud-band element (11) extending transversely to the blade longitudinal axis, hollow spaces (16, 16′, 17, 17′) for cooling being provided in the interior of the shroud-band element (11), which hollow spaces (16, 16′, 17, 17′) are connected on the inlet side to at least one cooling-air passage (18) passing through the turbine blade (10) to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade (10), the hollow spaces (16, 16′, 17, 17′) and the shroud-band element (11) are matched to one another in shape and dimensions in order to reduce the weight of the shroud-band element (11).

Abstract: A cooled component, such as a turbine blade for gas turbines is provided, having efficient internal cooling, with an interior cooling passageway having a round cross-section. A row of feeding holes for the coolant are arranged spaced from each other in the direction of the longitudinal axis of the cooling passageway and originating from a common coolant channel. Each of the feeding holes intersects the cooling passageway tangentially. The ease of manufacturing the cooling component is improved in that the majority of the feeding holes have a hole diameter that is smaller than half of the hydraulic diameter of the cooling passageway, and selected feeding holes have a hole diameter that is greater than half of the hydraulic diameter of the cooling channel.

Abstract: In an air-cooled turbine blade which, at the blade tip, has a shroud-band element extending transversely to the longitudinal axis of the blade, a plurality of cooling bores passing through the shroud-band element for the purpose of cooling, which cooling bores are connected on the inlet side to at least one cooling-air passage running through the turbine blade to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade, improved and assured cooling is achieved owing to the fact that the cooling bores run from inside to outside in the shroud-band element at least approximately parallel to the direction of movement of the blade and in each case open upstream of the outer margin of the shroud-band element into a surface recess open toward the exterior space.

Abstract: In an air-cooled turbine blade (10) which has a shroud-band element (11) at the blade tip, the shroud-band element (11) extending transversely to the blade longitudinal axis, hollow spaces (16, 16′, 17, 17′) for cooling being provided in the interior of the shroud-band element (11), which hollow spaces (16, 16′, 17, 17′) are connected on the inlet side to at least one cooling-air passage (18) passing through the turbine blade (10) to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade (10), the hollow spaces (16, 16′, 17, 17′) and the shroud-band element (11) are matched to one another in shape and dimensions in order to reduce the weight of the shroud-band element (11).

Abstract: In a hollow-cast component, a core opening (13) created during manufacturing is closed with a closure piece (14). This closure piece is located inside a recess (15) in the component, whereby the recess is arranged so that it is imbedded completely in the cast material, and completely covers the core opening. Because of this installation, the closure piece is fixed in a form-fitting manner in the direction of two spatial axes, so that the closure piece only needs to be secured with an additional joint in the installation direction. It is preferred that the installation direction is normal in relation to the direction of maximal stress of the closure piece, so that a joint is subject to a relatively small stress and therefore can be produced with little expenditure and a high degree of operational safety.

Abstract: In a free-running pressure wave supercharger driven by the gas forces, nozzles (27) are provided in the gas casing (6) and possibly also in the air casing (5), which nozzles are connected--via a drive line (26)--with a position in the air casing (5), preferably with the high-pressure air port (2), at which position a surplus pressure relative to the nozzle entry occurs during the run-up phase of the pressure wave supercharger. A control device 15 actuates a supercharge air flat (14) in the port (2) and a valve device (23+25) in the drive line (26) in the opposite sense, i.e. if the supercharge air flap (14) holds the port (2) closed, the valve device (23+25) frees the flow through the drive line (26) to the nozzle (27) and vice versa. The diaphragm capsule (17) of the control device (15) is subjected, on one side, to the pressure in a compression pocket (11) via a control pressure line (19) and, on the other side, to the pressure before the supercharge air flap (14) in the port (2).

Abstract: A pressure-wave machine for supercharging internal combustion engines having a cellular wheel with surfaces coated with catalyst material.

Abstract: Provision is made in the induced air duct and/or in the exhaust duct of the pressure wave supercharger for butterfly valves, by the control of which the exhaust gas proportion to be returned to the charge air is matched to the load condition of the engine. The adjustment of the butterfly valve or butterfly valves occurs through a linkage as a function of the load condition of the engine. A correction link acts on the linkage being provided to compensate for pressure alterations in the induced air duct and/or exhaust duct.