Radial compressor

Patent metadata

Field	Value
Publication number	US-9976566-B2
Application number	US-201414528613-A
Country	US
Kind code	B2
Filing date	Oct 30, 2014
Priority date	Oct 31, 2013
Publication date	May 22, 2018
Grant date	May 22, 2018

Abstract

A radial compressor has at least one compressor stage. The compressor stage includes: an impeller having moving blades on a rotor side arranged in a flow channel of the compressor stage. The flow channel is bounded by a hub contour and a housing contour or cover disc contour. Each moving blade has a flow inlet edge and a flow outlet edge. In the region of the compressor stage on the hub contour of the flow channel, initially a curvature change from a first concave curvature into a convex curvature and following this a curvature change from the convex curvature into a second concave curvature is formed; and/or on the housing contour or cover disc contour of the flow channel, initially a curvature change from a first convex curvature into a concave curvature and following this a curvature change from the concave curvature into a second convex curvature is formed.

First claim

What is claimed is:

1. A radial compressor, with at least one compressor stage, wherein the, or each, compressor stage comprises:
an impeller ( 10 ) having multiple moving blades ( 12 ) on a rotor side, which are arranged in a flow channel ( 11 ) of the at least one compressor stage,
wherein:
the flow channel ( 11 ) of the at least one compressor stage is bounded by a hub contour ( 13 ) and a housing contour or cover disc contour ( 14 ),
each moving blade ( 12 ) has a flow inlet edge ( 15 ) and a flow outlet edge ( 16 ),
in the region of the at least one compressor stage on the hub contour ( 13 ) of the flow channel ( 11 ), seen in a through-flow direction of the flow channel ( 11 ) initially there is arranged a curvature change from a first concave curvature into a convex curvature that is curved towards the inside into the flow channel ( 11 ) and reduces the flow cross section of the flow channel ( 11 ) and following this there is arranged a curvature change from the convex curvature into a second concave curvature; and
on the housing contour or cover disc contour ( 14 ) of the flow channel ( 11 ), seen in the through-flow direction of the flow channel ( 11 ) initially there is arranged only one curvature change from a first convex curvature into a concave curvature that is curved towards the outside out of the flow channel ( 11 ) and increases the flow cross section of the flow channel ( 11 ) and following this there is arranged only one curvature change from the concave curvature into a second convex curvature,
wherein 0% of a length L−N of the hub contour ( 13 ) in meridional projection lies upstream of the flow inlet edge ( 15 ) of the moving blades ( 12 ) and 100% of a length L−N of the hub contour ( 13 ) in meridional projection lies in a region of the flow outlet edge ( 16 ) of the moving blades ( 12 ) of the impeller wherein each curvature change is a smooth transition, and
wherein the housing contour or cover disk contour ( 14 ) changes in curvature are annular features.

2. The radial compressor according to claim 1 , wherein on the hub contour ( 13 ) of the flow channel ( 11 ) for a first concave curvature radius R1−N and a second concave curvature radius R3−N of the flow channel ( 11 ) the following relationship with an outer diameter D2 of the impeller ( 10 ) applies in each case:
0.05< R 1− N/D 2<0.60,

0.05< R 3− N/D 2<0.80.

3. The radial compressor according to claim 2 , wherein on the hub contour ( 13 ) of the flow channel ( 11 ) for a convex curvature radius R2−N of the flow channel ( 11 ) the following relationship with the outer diameter D2 of the impeller ( 10 ) applies:
0.10< R 2− N/D 2<5.00.

4. The radial compressor according to claim 3 , wherein on the hub contour ( 13 ) of the flow channel ( 11 ) the curvature change from the first concave curvature into the convex curvature lies in a range between 10.0% and 60.0% of the length of the hub contour ( 13 ) in meridional projection, and on the hub contour ( 13 ) of the flow channel ( 11 ) the curvature change from the convex curvature into the second concave curvature lies in a range between 15.0% and 75.0% of the length of the hub contour ( 13 ) in meridional projection.

5. A radial compressor, with at least one compressor stage, wherein the, or each, compressor stage comprises:
an impeller ( 10 ) having multiple moving blades ( 12 ) on a rotor side, which are arranged in a flow channel ( 11 ) of the at least one compressor stage,
wherein:
the flow channel ( 11 ) of the at least one compressor stage is bounded by a hub contour ( 13 ) and a housing contour or cover disc contour ( 14 ),
each moving blade ( 12 ) has a flow inlet edge ( 15 ) and a flow outlet edge ( 16 ),
in the region of the at least one compressor stage on the hub contour ( 13 ) of the flow channel ( 11 ), seen in a through-flow direction of the flow channel ( 11 ) initially there is arranged a curvature change from a first concave curvature into a convex curvature that is curved towards the inside into the flow channel ( 11 ) and reduces the flow cross section of the flow channel ( 11 ) and following this there is arranged a curvature change from the convex curvature into a second concave curvature; and
on the housing contour or cover disc contour ( 14 ) of the flow channel ( 11 ), seen in the through-flow direction of the flow channel ( 11 ) initially there is arranged only one curvature change from a first convex curvature into a concave curvature that is curved towards the outside out of the flow channel ( 11 ) and increases the flow cross section of the flow channel ( 11 ) and following this there is arranged only one curvature change from the concave curvature into a second convex curvature,
wherein on the hub contour ( 13 ) of the flow channel ( 11 ) for a first concave curvature radius R1−N and a second concave curvature radius R3−N of the flow channel ( 11 ) the following relationship with an outer diameter D2 of the impeller ( 10 ) applies in each case:
0.05< R 1− N/D 2<0.60,

0.05< R 3− N/D 2<0.80,

wherein on the hub contour ( 13 ) of the flow channel ( 11 ) for a convex curvature radius R2−N of the flow channel ( 11 ) the following relationship with the outer diameter D2 of the impeller ( 10 ) applies:
0.10< R 2− N/D 2<5.00,

wherein on the hub contour ( 13 ) of the flow channel ( 11 ) the curvature change from the first concave curvature into the convex curvature lies in a range between 10.0% and 60.0% of the length of the hub contour ( 13 ) in meridional projection, and on the hub contour ( 13 ) of the flow channel ( 11 ) the curvature change from the convex curvature into the second concave curvature lies in a range between 15.0% and 75.0% of the length of the hub contour ( 13 ) in meridional projection, and
wherein on the housing contour or cover disc contour ( 14 ) of the flow channel ( 11 ) for a first convex curvature radius R1−D and a second convex curvature radius R3−D of the flow channel ( 11 ) the following relationship with the outer diameter D2 of the impeller ( 10 ) applies in each case:
0.03< R 1− D/D 2<0.11,

0.05< R 3− D/D 2<0.52.

6. The radial compressor according to claim 5 , wherein on the housing contour or cover disc contour ( 14 ) of the flow channel ( 11 ) for a concave curvature radius R2−D of the flow channel ( 11 ) the following relationship with the outer diameter D2 of the impeller ( 10 ) applies:
0.05< R 2− D/D 2<0.84.

7. The radial compressor according to claim 6 , wherein on the housing contour or cover disc contour ( 14 ) of the flow channel ( 11 ) the curvature change from the first convex curvature into the concave curvature lies in a range between 0.0% and 25% of the length of the housing contour or cover disc contour ( 14 ) in meridional projection, and on the housing contour or cover disc contour ( 14 ) of the flow channel ( 11 ) the curvature change from the concave curvature into the second convex curvature lies in a range between 10.0% and 60.0% of the length of the housing contour or cover disc contour ( 14 ) in meridional projection.

8. The radial compressor according to claim 7 , wherein in the region of the respective compressor stage at least two of the following relationships apply:
0.15< D 1/ D 2<0.60,
0.20< D 3/ D 2<0.94,
0.05< L 1/ D 2<0.35,
0.01< L 2/ D 2<0.15,
−20°<α<+90°,

wherein D1 is a hub diameter of the impeller ( 10 ), D3 is a suction mouth diameter of the impeller ( 10 ), D2 is the outer diameter of the impeller ( 10 ), L1 is an axial length of the housing contour ( 14 ) or cover disc contour of the flow channel ( 11 ) on the stator side, L2 is an axial length of the flow outlet edge ( 16 ) of the moving blades ( 12 ) of the impeller ( 10 ) and a is an angle of inclination of the

Assignees

• Hildebrandt Andre
• Ceyrowsky Thomas
• Man Diesel & Turbo Se

Inventors

• Hildebrandt André
• Ceyrowsky Thomas

Classifications

• F05B2250/712

  concave · CPC title

• F05D2250/712

  concave · CPC title

• F04D29/681

  especially adapted for elastic fluid pumps · CPC title

• F05B2250/711

  convex · CPC title

• F04D29/4206

  especially adapted for elastic fluid pumps · CPC title