Return stage of a multi-staged compressor or expander with twisted guide vanes
A return stage through which a process fluid is designed to flow along a throughflow direction of a radial turbomachine, wherein the return stage extends in annular fashion about an axis and is defined radially inwardly by an inner delimiting contour and radially outwardly by an outer delimiting contour. At least one guide vane stage including guide vanes extends at least along a part of the third section and segments the return stage in the circumferential direction into flow channels, wherein in each case a profile midline of a profile cross section defines an inner track on the side of the inner delimiting contour and an outer track on the side of the outer delimiting contour. A radial turbomachine includes at least one such return stage.
1. A return stage (RTC) for throughflow by means of a process fluid along a throughflow direction of a radial turbomachine (RTM), wherein the return stage (RTC) extends about an axis (X) in a ring-shaped manner, wherein the return stage (RTC) is defined radially inwardly by an inner delimiting contour (IDC) and radially outwardly by an outer delimiting contour (ODC),
wherein the return stage (RTC) extends radially outwardly in a first section (SG 1 ) along a first throughflow direction (FD 1 ),
wherein the return stage (RTC) extends, in a manner describing an arcuate deflection, radially inward from radially outside along the first throughflow direction (FD 1 ) in a second section (SG 2 ),
wherein the return stage (RTC) extends radially inward from radially outside along the first throughflow direction (FD 1 ) in a third section (SG 3 ),
wherein the return stage (RTC) extends, in a manner describing an arcuate deflection, axially from radially inside along the first throughflow direction (FD 1 ) in a fourth section (SG 4 ),
wherein at least one guide vane stage (VST) comprising guide vanes (VNS) extends at least along a part of the third section (SG 3 ) and, in the circumferential direction, segments the return stage into flow channels,
wherein each guide vane of the guide vanes (VNS) in the guide vane stage (VST) has a respective profile midline (PML) of a respective profile cross section (PRC) that defines an inner track (ITR) on a side of the inner delimiting contour (IDC) and an outer track (OTR) on a side of the outer delimiting contour (ODC),
wherein respective progressions of the inner track (ITR) and outer track (OTR) are defined as,
θ( L )= F θ ( L )
R ( L )= F R ( L ),
with θ: circumferential position angle in a direction of rotation of the radial turbomachine (RTM), with the vertex on the axis (X),
L: profile midline path coordinate along the first throughflow direction (FD 1 ) along a mid-height of the respective guide vane (VNS), normalized to a total length of 1,
F θ (L): functional relationship between circumferential position angle θ and position L on the profile midline,
F R (L): functional relationship between radius R and position L on the profile midline,
R: radius of the position of the inner track (ITR) or outer track (OTR),
wherein the guide vanes (VNS) have three successive profile sections (PS) along the first throughflow direction (FD 1 );
a first profile section (PS 1 ),
a second profile section (PS 2 ),
a third profile section (PS 3 ),
wherein, for values of L in the profile sections, it holds that:
in the first profile section (PS 1 ):
θ OTR ( L )≠θ ITR ( L ) and (θ OTR ( L )−θ ITR ( L ))′≠0 for all but one L,
in the second profile section (PS 2 ):
θ OTR ( L )=θ ITR ( L ) and (θ OTR ( L )−θ ITR ( L ))′=0,
in the third profile section (PS 3 ):
θ OTR ( L )≠θ ITR ( L ) and (θ OTR ( L )−θ ITR ( L ))′≠0 for all but one L,
wherein it holds that:
(θ OTR ( L )−θ ITR ( L ))′=0 for exactly one L PS 1 ,
(θ OTR (L)−θ ITR (L))′=0 for exactly one L PS 3 .
2. The return stage (RTC) as claimed in claim 1 ,
wherein, in the first profile section (PS 1 ) there is a local minimum, and
wherein, in the third profile section (PS 3 ) there is a local minimum.
3. The return stage (RTC) as claimed in claim 1 , wherein the second profile section (PS 2 ) extends from L=0.4 to L=0.6.
4. The return stage (RTC) as claimed in claim 1 , wherein at least some of the guide vanes (VNS) have a cutout in the second profile section (PS 2 ), extending from a point of the inner track to a point of the outer track, for a leadthrough of a fastening element between the inner delimiting contour (IDC) and the outer delimiting contour (ODC).
5. The return stage (RTC) as claimed in claim 4 , wherein the fastening element comprises screws arranged to fasten a vane base (RR) to an intermediate base (DGP).
6. The return stage (RTC) as claimed in claim 1 , wherein the guide vanes (VNS) is each arranged with a respective inlet edge (LER) in the second section (SG 2 ), in a region of the arcuate deflection of the second section (SG 2 ) between 0° and 90° of a first deflection angle (BA 1 ).
7. The return stage (RTC) as claimed in claim 1 , wherein the guide vanes (VNS) is each arranged with a respective outlet edge (VTE) in the fourth section (SG 4 ), in a region of the arcuate deflection of the fourth section (SG 4 ) between 0° and 60° of a second deflection angle (BA 2 ).
8. The return stage (RTC) as claimed in claim 1 , wherein the return stage (RTC) is a radial turbocompressor return stage (RCC).
9. A radial turbomachine (RTM) comprising:
a rotor (ROT) which is rotatable about an axis (X);
at least two impellers (IP 1 , IP 2 ) connected to the rotor; and
a return stage (RTC) arranged to guide flow of a process fluid from one impeller (IP 1 , IP 2 ) to a downstream impeller (IP 1 , IP 2 ) along a first throughflow direction (FD 1 ),
wherein the return stage (RTC) extends about the axis (X) in a ring-shaped manner, wherein the return stage (RTC) is defined radially inwardly by an inner delimiting contour (IDC) and radially outwardly by an outer delimiting contour (ODC),
wherein the return stage (RTC) extends radially outwardly in a first section (SG 1 ) along the first throughflow direction (FD 1 ),
wherein the return stage (RTC) extends, in a manner describing an arcuate deflection, radially inwardly from radially outside along the first throughflow direction (FD 1 ) in a second section (SG 2 ),
wherein the return stage (RTC) extends radially inwardly from radially outside along the first throughflow direction (FD 1 ) in a third section (SG 3 ),
wherein the return stage (RTC) extends, in a manner describing an arcuate deflection, axially from radially inside along the first throughflow direction (FD 1 ) in a fourth section (SG 4 ),
wherein at least one guide vane stage (VST) comprising guide vanes (VNS) extends at least along a part of the third section (SG 3 ) and, in the circumferential direction, segments the return stage into flow channels,
wherein each guide vane of the guide vanes (VNS) in the guide vane stage (VST) has a respective profile midline (PML) of a respective profile cross section (PRC) that defines an inner track (ITR) on a side of the inner delimiting contour (IDC) and an outer track (OTR) on a side of the outer delimiting contour (ODC),
wherein respective progressions of the inner track (ITR) and outer track (OTR) are defined as:
θ( L )= F θ ( L )
R ( L )= F R ( L ),
with θ: circumferential position angle in a direction of rotation of the radial turbomachine (RTM), with the vertex on the axis (X),
L: profile midline path coordinate along the first throughflow direction (FD 1 ) along a mid-height of the respective guide vane (VNS), normalized to a total length of 1,
F θ (L): functional relationship between circumferential position angle θ and position L on the profile midline,
F R (L): functional relationship between radius R and position L on the profile midline,
R: radius of the position of the inner track (ITR) or outer track (OTR), wherein the guide vanes (VNS) have three successive profile sections (PS) along the first throughflow direction (FD 1 ):
a first profile section (PS 1 ),
a second profile section (PS 2 ),
a third profile section (PS 3 ),
wherein, for values of L in the profile sections, it holds that:
in the first profile section (PS 1 ):
θ OTR ( L )≠θ ITR ( L ) and (θ OTR ( L )−θ ITR ( L ))′≠0 for all but one L,
in the second profile section (PS 2 ):
θ OTR ( L )=θ ITR ( L ) and (θ OTR ( L )−θ ITR ( L ))′=0,
in the third profile section (PS 3 ):
θ OTR ( L )≠θ ITR ( L ) and (θ OTR ( L )−θ ITR ( L ))′≠0 for all but one L,
wherein it holds that:
(θ OTR ( L )−θ ITR ( L ))′=0 for exactly one L PS 1 ,
(θ OTR ( L )−θ ITR ( L ))′=0 for exactly one L PS 3 .
10. The radial turbomachine (RTM) as claimed in claim 9 , wherein the impellers (IP 1 , IP 2 ) have an outlet diameter (D 2 ) upstream of the return stage (RTC), wherein a transition cross section of the return stage from the first section (SG 1 ) to the second section (SG 2 ) is arranged at an intermediate diameter (DRR), wherein it holds that:
DRR/D 2<1.5,
with:
D 2 : outlet diameter of impellers (IP 1 , IP 2 )
DRR: intermediate diameter of the transition cross section of the return stage from the first section (SG 1 ) to the second section (SG 2 ).
11. The radial turbomachine (RTM) as claimed in claim 10 , wherein it holds that:
DRR/D 2<1.4.
12. The radial turbomachine (RTM) as claimed in claim 9 , wherein the radial turbomachine (RTM) is a radial turbocompressor.