Radial compressor and compressor arrangement with such a radial compressor

Patent metadata

Field	Value
Publication number	US-9790945-B2
Application number	US-201414573916-A
Country	US
Kind code	B2
Filing date	Dec 17, 2014
Priority date	Dec 18, 2013
Publication date	Oct 17, 2017
Grant date	Oct 17, 2017

Abstract

A radial compressor for a compressor arrangement comprising the radial compressor and an axial compressor includes an inlet flow channel bounded by a radially inner hub contour and a radially outer housing contour, in which inlet guide blades are arranged. Via the inlet flow channel a medium to be compressed is supplied to an impeller having moving blades. The inlet flow channel runs diagonally to an axis of rotation of the impeller.

First claim

What is claimed is:

1. A radial compressor for a compressor arrangement having the radial compressor and an axial compressor, the radial compressor comprising:
an impeller ( 11 ) having an axis of rotation ( 16 ), the impeller ( 11 ) having moving blades ( 15 );
an inlet flow channel ( 10 ) bounded by a continuously curved radially inner hub contour ( 12 ) and a radially outer housing contour ( 13 ); and
inlet guide blades ( 14 ) arranged in the inlet flow channel ( 10 ),
wherein a medium to be compressed is supplied to the impeller ( 11 ) via the inlet flow channel ( 10 ), and
wherein the inlet flow channel ( 10 ) runs diagonally to the axis of rotation ( 16 ) of the impeller ( 11 ).

2. A compressor arrangement comprising an axial compressor and the radial compressor according to claim 1 .

3. The radial compressor according to claim 1 , wherein the inlet guide blades ( 14 ) have a stacking axis ( 26 ) and the stacking axis ( 26 ) includes an angle (β) with respect to the axis of rotation ( 16 ) of the impeller between 38.25° and 51.75°.

4. The radial compressor according to claim 1 , wherein the inlet guide blades ( 14 ) have a stacking axis ( 26 ) and the stacking axis ( 26 ) includes an angle (β) with respect to the axis of rotation ( 16 ) of the impeller between 42.75° and 47.25°.

5. A radial compressor for a compressor arrangement having the radial compressor and an axial compressor, the radial compressor comprising:
an impeller ( 11 ) having an axis of rotation ( 16 ), the impeller ( 11 ) having moving blades ( 15 );
an inlet flow channel ( 10 ) bounded by a radially inner hub contour ( 12 ) and a radially outer housing contour ( 13 ); and
inlet guide blades ( 14 ) arranged in the inlet flow channel ( 10 ),
wherein a medium to be compressed is supplied to the impeller ( 11 ) via the inlet flow channel ( 10 ),
wherein the inlet flow channel ( 10 ) runs diagonally to the axis of rotation ( 16 ) of the impeller ( 11 ), and
wherein the radially inner hub contour ( 12 ) has a start ( 17 ) and an end ( 18 ) and is continuously curved between the start ( 17 ) and the end ( 18 ).

6. A radial compressor for a compressor arrangement having the radial compressor and an axial compressor, the radial compressor comprising:
an impeller ( 11 ) having an axis of rotation ( 16 ), the impeller ( 11 ) having moving blades ( 15 );
an inlet flow channel ( 10 ) bounded by a radially inner hub contour ( 12 ) and a radially outer housing contour ( 13 ); and
inlet guide blades ( 14 ) arranged in the inlet flow channel ( 10 ),
wherein a medium to be compressed is supplied to the impeller ( 11 ) via the inlet flow channel ( 10 ),
wherein the inlet flow channel ( 10 ) runs diagonally to the axis of rotation ( 16 ) of the impeller ( 11 ), and
wherein the radially outer housing contour ( 13 ) has a start ( 19 ) and an end ( 20 ), and wherein the part of the radially outer housing contour ( 13 ) adjacent to the start ( 19 ) comprises a linearly running section ( 22 ) and the part of the radially outer housing contour ( 13 ) adjacent to the end ( 20 ) comprises a curved section ( 23 ).

7. The radial compressor according to claim 6 , wherein the inlet guide blades ( 14 ) have flow inlet edges ( 24 ) and flow outlet edges ( 25 ), and wherein radially outer ends of the flow inlet edges ( 24 ) and radially outer ends of the flow outlet edges ( 25 ) each merge into the linearly running section ( 22 ) of the radially outer housing contour ( 13 ).

8. The radial compressor according to claim 6 , wherein the linearly running section ( 22 ) of the radially outer housing contour ( 13 ) includes an angle (α) with respect to the axis of rotation ( 16 ) of the impeller ( 11 ) between 42.75° and 71.25°.

9. The radial compressor according to claim 6 , wherein the following relationships apply on the radially outer housing contour ( 13 ):
0.285< s 1/( s 3+ s 4)<0.475,
0.555< s 2/( s 3+ s 4)<0.925,
2.52< s 3/ s 4<4.20,
wherein s1 is the edge length of the radially outer housing contour between the start of the radially outer housing contour and the end of the flow inlet edges of the inlet guide blades merging into the same, wherein s2 is the edge length of the radially outer housing contour between the start of the radially outer housing contour and the end of the flow outlet edges of the inlet guide blades merging into the same, wherein s3 is the edge length of the linearly running section of the radially outer housing contour, wherein s4 is the edge length of the curved running section of the radially outer housing contour, and wherein s1/(s3+s4)<s2/(s3+s4).

10. The radial compressor according to claim 9 , wherein in the region of the radially outer housing contour ( 13 ) the following relationships apply:
0.323< s 1/( s 3+ s 4)<0.437,
0.629< s 2/( s 3+ s 4)<0.851,
2.856< s 3/ s 4<3.864.

11. The radial compressor according to claim 9 , wherein in the region of the radially outer housing contour ( 13 ) the following relationships apply:
0.361< s 1/( s 3+ s 4)<0.399,
0.703< s 2/( s 3+ s 4)<0.777,
3.192< s 3/ s 4<3.528.

12. The radial compressor according to claim 6 , wherein the linearly running section ( 22 ) of the radially outer housing contour ( 13 ) includes an angle (α) with respect to the axis of rotation ( 16 ) of the impeller ( 11 ) between 48.45° and 65.55°.

13. The radial compressor according to claim 6 , wherein the linearly running section ( 22 ) of the radially outer housing contour ( 13 ) includes an angle (α) with respect to the axis of rotation ( 16 ) of the impeller ( 11 ) between 54.15° and 59.85°.

14. A radial compressor for a compressor arrangement having the radial compressor and an axial compressor, the radial compressor comprising:
an impeller ( 11 ) having an axis of rotation ( 16 ), the impeller ( 11 ) having moving blades ( 15 );
an inlet flow channel ( 10 ) bounded by a radially inner hub contour ( 12 ) and a radially outer housing contour ( 13 ); and
inlet guide blades ( 14 ) arranged in the inlet flow channel ( 10 ),
wherein a medium to be compressed is supplied to the impeller ( 11 ) via the inlet flow channel ( 10 ),
wherein the inlet flow channel ( 10 ) runs diagonally to the axis of rotation ( 16 ) of the impeller ( 11 ), and
wherein the inlet guide blades ( 14 ) have a stacking axis ( 26 ) and the stacking axis ( 26 ) includes an angle (β) with respect to the axis of rotation ( 16 ) of the impeller between 33.75° and 56.25°.

15. A radial compressor for a compressor arrangement having the radial compressor and an axial compressor, the radial compressor comprising:
an impeller ( 11 ) having an axis of rotation ( 16 ), the impeller ( 11 ) having moving blades ( 15 );
an inlet flow channel ( 10 ) bounded by a radially inner hub contour ( 12 ) and a radially outer housing contour ( 13 ); and
inlet guide blades ( 14 ) arranged in the inlet flow channel ( 10 ),
wherein a medium to be compressed is supplied to the impeller ( 11 ) via the inlet flow channel ( 10 ),
wherein the inlet flow channel ( 10 ) runs diagonally to the axis of rotation ( 16 ) of the impeller ( 11 ),
wherein the following relationships apply on the radially inner hub contour ( 12 ):
0.383< h 1/ h 3<0.638,
0.518< h 2/ h 3<0.863,

wherein h1 is the arc length of the radially inner hub contour between the start of the radially inner hub contour and the end of the flow inlet edges of the inlet guide blades merging into the same, wherein h2 is the arc length of the radially inner hub contour between the start of the radially inner hub contour and the end of the flow outlet edges of the inlet

Assignees

• Tiedtke Alf-Peter
• Hildebrandt Andre
• Ceyrowsky Thomas
• Strohmeyer Hauke
• Man Diesel & Turbo Se

Inventors

• Tiedtke Alf-Peter
• Hildebrandt Andre
• Ceyrowsky Thomas
• Strohmeyer Hauke

Classifications

• F04D25/16

  Combinations of two or more pumps {; Producing two or more separate gas flows} · CPC title

• F04D29/44

  Fluid-guiding means, e.g. diffusers · CPC title

• F04D29/444

  Bladed diffusers · CPC title

• F04D17/025 Primary

  comprising axial flow and radial flow stages · CPC title

• F04D17/10 Primary

  for compressing or evacuating · CPC title