Abstract: The invention relates to a compressor module that forms a compressor gas duct for guiding a compressor gas that is to be compressed, wherein a flow bypass structure extends radially through the compressor gas duct between an inner housing wall and an outer housing wall, and wherein, in a wall surface of the inner housing, with which the inner housing wall bounds the compressor gas duct radially inward, an exhaust orifice for partial exhaust of the compressor gas guided in the compressor gas duct is arranged, wherein, for guiding the exhaust gas that is discharged through the exhaust orifice, an exhaust duct adjoins the exhaust orifice, and wherein the exhaust duct extends through the flow bypass structure radially outside of the compressor gas duct.

Abstract: A gas turbine compressor including a guide vane (1), a moving vane (2), in particular downstream, and a bleed channel (3) having an upstream channel wall (3.1), which merges into an annular space (5), an axially opposite downstream channel wall (3.2) having an inlet edge (3.3), which is rounded in particular, and a bleed channel outlet, the downstream channel wall enclosing with an axis of rotation of the compressor a first angle (?) which increases in the flow direction (x).

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.

Abstract: A continuous-flow machine, especially an axial compressor, having at least one guide vane ring that includes at least one row of adjustable guide vanes, whereby each guide vane is tapered relative to its vane body in the direction of its longitudinal axis as seen in a side view of the guide vane. In order to increase the stability of the flow in the continuous-flow machine, each row of guide vanes comprises first guide vanes and second guide vanes, whereby, as seen in a combined side view of a first guide vane and of a second guide vane, each first guide vane is tapered along its vane body in the lengthwise direction, and each second guide vane is tapered in the opposite direction.

Abstract: A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed.

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.

Abstract: A gas turbine compressor including a guide vane (1), a moving vane (2), in particular downstream, and a bleed channel (3) having an upstream channel wall (3.1), which merges into an annular space (5), an axially opposite downstream channel wall (3.2) having an inlet edge (3.3), which is rounded in particular, and a bleed channel outlet, the downstream channel wall enclosing with an axis of rotation of the compressor a first angle (?) which increases in the flow direction (x).

Abstract: A continuous-flow machine, especially an axial compressor, having at least one guide vane ring that includes at least one row of adjustable guide vanes, whereby each guide vane is tapered relative to its vane body in the direction of its longitudinal axis as seen in a side view of the guide vane. In order to increase the stability of the flow in the continuous-flow machine, each row of guide vanes comprises first guide vanes and second guide vanes, whereby, as seen in a combined side view of a first guide vane and of a second guide vane, each first guide vane is tapered along its vane body in the lengthwise direction, and each second guide vane is tapered in the opposite direction.