Return stage
A recirculation stage of a radial turbomachine, the recirculation stage has an inner delimiting contour and an outer delimiting contour. The stator vane stage has stator vanes, wherein a difference between a vane construction angle at the leading edge and a vane construction angle at a downstream position defines a redirection angle for each point on the camber line of a respective profile cross section, wherein the stator vanes extend at least along part of the third section, wherein the trailing edges are arranged in the third section, wherein at the trailing edges in the center of the span width the redirection angle is in each case greater than the average overall redirection angle, wherein at both ends of the span width at in each case at least 10% of the span width in each case the redirection angle is smaller than the average overall redirection angle.
1. A return stage of a radial turbomachine having at least one guide blade stage, wherein the return stage extends annularly around an axis,
wherein the return stage is defined radially inwards by an inner delimiting contour and radially outwards by an outer delimiting contour,
wherein, along a first flow direction, the return stage extends radially outwards in a first section,
wherein the return stage extends from radially outwards to radially inwards, describing an arcuate deflection, in a second section along the first flow direction,
wherein the return stage extends from radially outwards to radially inwards in a third section along the first flow direction,
wherein the return stage extends from radially inwards to axially, describing an arcuate deflection, in a fourth section along the first flow direction,
wherein the return stage comprises guide blades,
wherein the guide blades each comprise a turbine blade which extends along a span width and whereof the surfaces around which the flow circulates extend from a leading edge, located upstream, as a pressure side and as a suction side, spaced from one another along a camber line by profile cross-sections, to a trailing edge,
wherein a tangent at the camber line of each profile cross-section to a radial-axial reference plane encloses a blade construction angle for each point of the camber line,
wherein a difference between a blade construction angle at the leading edge and a blade construction angle at a downstream position defines a deflection angle for each point of the camber line of each profile cross-section,
wherein a mean total deflection angle is a deflection angle at the trailing edge which is determined via the span width,
wherein the guide blades extend at least along part of the third section and the return stage is segmented into flow channels in the circumferential direction,
wherein the trailing edges are arranged in the third section,
wherein, at the trailing edges in the center of the span width, the deflection angle is greater in each case than the mean total deflection angle,
wherein, at the two ends of the span width to at least 10% of the span width in each case, the deflection angle is smaller in each case than the mean total deflection angle.
2. The return stage according to claim 1 ,
wherein the leading edges are each arranged in the third section.
3. The return stage according to claim 1 ,
wherein the trailing edges each describe a straight line.
4. The return stage according to claim 1 ,
wherein the leading edges are designed to be curved or angled.
5. The return stage according to claim 1 ,
wherein, at the two ends of the span width to at least 7% of the span width in each case, the camber lines of the profile cross-sections there are shorter than a mean camber line length.
6. The return stage according to claim 1 ,
wherein the guide blades have a linear leading edge and are designed to be substantially cylindrical up to the region at the two ends of the span width,
wherein, at the trailing edges to at least 7% of the span width in each case, the camber lines of the profile cross-sections there are designed to be shorter than a mean camber line length.