Abstract: A blower unit for a portable handheld blower apparatus has a housing section and a tubular receiving space, formed in the housing section, with a first axial end and a second axial end and with a longitudinal center axis. Arranged in the receiving space of the housing section is an axial blower for generating a blower air flow, the axial blower being driven by a drive motor. The receiving space has an intake opening at its first axial end and a discharge opening at its second axial end. In order to reduce operating noise, an air guide plate is arranged at an axial distance in front of the intake opening, the air guide plate having external dimensions that are greater than the external dimensions of the intake opening. An annular gap that supplies intake air is formed between the air guide plate and an outer periphery of the housing section.

Abstract: A blower unit for a portable handheld blower apparatus has a housing section and a tubular receiving space, formed in the housing section, with a first axial end and a second axial end and with a longitudinal center axis. Arranged in the receiving space of the housing section is an axial blower for generating a blower air flow, the axial blower being driven by a drive motor. The receiving space has an intake opening at its first axial end and a discharge opening at its second axial end. In order to reduce operating noise, an air guide plate is arranged at an axial distance in front of the intake opening, the air guide plate having external dimensions that are greater than the external dimensions of the intake opening. An annular gap that supplies intake air is formed between the air guide plate and an outer periphery of the housing section.

Abstract: A turbocharger with at least one axial turbine stage. Separate circumferential sections of the turbine are fed by separate exhaust system runners. The turbine is designed to harness pulse energy. Corresponding engine having cylinders comprising such a turbocharger.

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 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 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.