Abstract: A variable geometry turbocharger is provided. The turbocharger improves efficiency by controlling flow to the rotor (230) via movable vanes (260). The vanes (260) can be rotated using a pin (380, 480) and groove (385, 485) system. The vanes (260) can be multiple structures (710, 730) that are movable with respect to each other to increase the length of each of the vanes (260). The turbocharger also improves efficiency by creating a better seal in the area between the vanes (260) and the adjustment ring (240). The seal can be provided by biasing the adjustment ring (240) towards each of the vanes (260). The seal can be provided by expanding each of the vanes (260). The seal can be provided by having a movable portion (1150) of the adjustment ring (240) that is actuated by a pressure source or the like and axially moves towards the vanes (260). The plurality of vanes (260) can be low solidity vanes.

Abstract: A spiral casing for a turbine of a turbocharger is made from thin (0,2 to 2 mm thick) sheet metal. The spiral casing can be made from two matching parts and can be insulated.

Abstract: A pre-whirl generating apparatus (26) is provided that employs deformable air deflecting vanes (46) adjacent the inlet (18) of a radial air compressor (12-22), which vanes (46) can be mechanically deformed to generate positive, neutral, or negative pre-whirl flow to the compressor. A minimum number of parts are used to position one or more thin, deformable vanes (46) in the intake channel (34) leading to the compressor inlet (18). In their undeformed position, the vanes (46) do not deflect the incoming air, thereby causing little or no flow restriction. To achieve the desired positive or negative pre-whirl of flow to the compressor (12-22), the trailing edge (62) of the vanes (46) are deflected transverse to the direction of flow in the channel (34) in either the positive or negative direction.

Abstract: The invention concerns a casing aggregate for the turbine of an exhaust turbocharger. The invention is identified by the following characteristics: a spiral casing adapted for surround the running wheel of the turbine; a tongue-like wall part (tongue) in the inside of the spiral casing; an inlet connection; an outlet connection; a flange to connect to a bearing casing; wherein the casing aggregate is manufactured of thin-walled precision casting; wherein the casing aggregate is made of at least two parts, so that at least one separation joint is present; and the separation joint is arranged as follows: it runs in an axially perpendicular level; it runs along the apex line of the spiral casing; it extends over an arc of a circle of approximately 270 degrees; it lies outside of the area of the tongue.

Abstract: A novel blade configuration does not exceed the permitted stresses for particular loads, especially as a result of centrifugal forces and which at the same time, allows the turbomachine to function with a high degree of efficiency. To this end, a moving blade for the turbomachine contains at least partially a cellular material, especially a foamed metal. The cellular material can be provided e.g. in the hollowed-out part of the moving blade.

Abstract: A pre-whirl generating apparatus (26) is provided that employs deformable air deflecting vanes (46) adjacent the inlet (18) of a radial air compressor (12-22), which vanes (46) can be mechanically deformed to generate positive, neutral, or negative pre-whirl flow to the compressor. A minimum number of parts are used to position one or more thin, deformable vanes (46) in the intake channel (34) leading to the compressor inlet (18). In their undeformed position, the vanes (46) do not deflect the incoming air, thereby causing little or no flow restriction. To achieve the desired positive or negative pre-whirl of flow to the compressor (12-22), the trailing edge (62) of the vanes (46) are deflected transverse to the direction of flow in the channel (34) in either the positive or negative direction.

Abstract: To allow a simplified manufacture by casting the spiral casing for a turbine is divided into two matching parts which can be joined by welding or the like. The separation line between the parts runs along the apex of the spiral casing and lies essentially in a plane perpendicular to the turbine axis.

Abstract: A spiral casing for a turbine of a turbocharger is made from thin (0,2 to 2 mm thick) sheet metal. The spiral casing can be made from two matching parts and can be insulated.

Abstract: A novel blade configuration does not exceed the permitted stresses for particular loads, especially as a result of centrifugal forces and which at the same time, allows the turbomachine to function with a high degree of efficiency. To this end, a moving blade for the turbomachine contains at least partially a cellular material, especially a foamed metal. The cellular material can be provided e.g. in the hollowed-out part of the moving blade.

Abstract: A turbo machine, especially a steam turbine, has a main axis, an inner housing, an outer housing, a top region, and a bottom region. Between the outer housing and the inner housing a radial gap is formed, which has a narrow part in the bottom region.

Abstract: A steam turbine has a turbine shaft directed along a turbine axis. A plurality of turbine stages, each include a guide-blade structure and a moving-blade configuration located axially downstream of the guide-blade structure. The guide-blade structure and the moving-blade configuration are provided along the turbine shaft. Each stage has an average reaction degree achievable between 5% and 70%. The reaction degree of at least two turbine stages is of different values.

Abstract: A steam turbine has a high-pressure turbine section and a medium-pressure turbine section fluidically connected to the high-pressure turbine section. The high-pressure turbine section is a chamber configuration and the medium-pressure turbine section is a drum configuration. Alternatively, the high-pressure turbine section is a drum configuration and the medium-pressure turbine section is a chamber configuration. Alternatively, or additionally, the high-pressure turbine section is a double-flow configuration and the medium-pressure turbine section is a double-flow configuration.

Abstract: The invention relates to a steam turbine (1) which has a flow duct (2) with a wall (3). Blading (5) is arranged in blading rings (55) in the flow duct (2). The wall (3) of the flow duct (2) has a grooved structure (6) which purposefully influences the flow of an active fluid (13) through the flow duct (2). In particular, a spacing surface (31) with a grooved structure (6) is located between each two blades or vanes (5) of a blading ring (55). The invention also relates to a blade or vane for a steam turbine.