Liquid tolerant impeller for centrifugal compressors

Patent metadata

Field	Value
Publication number	US-10920788-B2
Application number	US-201415021154-A
Country	US
Kind code	B2
Filing date	Sep 11, 2014
Priority date	Sep 12, 2013
Publication date	Feb 16, 2021
Grant date	Feb 16, 2021

Abstract

In order to reduce erosion of an impeller due to liquid droplets in an incoming flow of gas, the impeller comprises converging-diverging bottlenecks; the incoming flow passes through the bottlenecks so that the speed of the gas at the inlet of the impeller first suddenly and substantially increases and then suddenly and substantially decreases; furthermore, the impeller is configured so that, internally after its inlet, the incoming flow is deviated gradually in the meridional plane.

First claim

What is claimed is:

1. A closed impeller for a rotary machine comprising:
an inlet and an outlet;
a hub having a hub contour;
a shroud having a shroud contour;
a plurality of blades, each blade comprising an upstream portion having a thickness that first increases and then decreases and a downstream portion having a substantially constant thickness; and
a plurality of passages fluidly connecting the inlet to the outlet, each passage defined by the hub, the shroud, and two associated blades of the plurality of blades, and each passage comprising a converging-diverging bottleneck between the respective upstream and downstream portions of the two associated blades that is configured to first increases and then decrease a speed of a gas flowing in the passage, the converging-diverging bottleneck created by the thickness of each of the two associated blades that first increases and then decreases,
wherein at any point along the hub contour in a meridional plane a curvature radius of the hub contour is approximately 2.5 times a height of a respective passage of the plurality of passages measured perpendicularly to the hub contour.

2. The impeller according to claim 1 , wherein the thickness decrease immediately follows the thickness increase.

3. The impeller according to claim 1 , wherein the thickness decrease ends at a distance from a leading edge of each blade, the distance being more than 2 times and less than 6 times the maximum thickness of each blade.

4. The impeller according to claim 3 , wherein the thickness increase starts at the leading edge of each blade.

5. The impeller according to claim 1 , wherein a maximum thickness of each the blade is located between 25% and 75% of a length of the increasing and decreasing thickness.

6. The impeller according to claim 1 , wherein at the inlet a lean angle of a leading edge of each blade with respect to a radial direction is approximately 30° so that the shroud profile lags behind the hub profile.

7. The impeller according to claim 1 , wherein the thickness increase and the thickness decrease are identically distributed on both sides of each blade.

8. A centrifugal compressor having a plurality of compressor stages, the compressor being tolerant to liquid at its inlet, wherein at least the first stage comprises an impeller according to claim 1 .

9. A closed impeller for a rotary machine comprising:
an inlet and an outlet;
a hub having a hub contour;
a shroud having a shroud contour;
a plurality of blades, each blade comprising an upstream portion having a thickness that first increases and then decreases and a downstream portion having a substantially constant thickness; and
a plurality of passages fluidly connecting the inlet to the outlet, each passage defined by the hub, the shroud, and two associated blades of the plurality of blades, and each passage comprising a converging-diverging bottleneck between the respective upstream and downstream portions of the two associated blades that is configured to first increases and then decrease a speed of a gas flowing in the passage, the converging-diverging bottleneck created by the thickness of each of the two associated blades that first increases and then decreases,
wherein at any point along the shroud contour in a meridional plane a curvature radius of the shroud contour is approximately 1.5 times a height of a respective passage of the plurality of passages measured perpendicularly to the shroud contour.

10. The impeller according to claim 9 , wherein the thickness decrease immediately follows the thickness increase.

11. The impeller according to claim 9 , wherein the thickness decrease ends at a distance from a leading edge of each blade, the distance being more than 2 times and less than 6 times the maximum thickness of each blade.

12. The impeller according to claim 11 , wherein the thickness increase starts at the leading edge of each blade.

13. The impeller according to claim 9 , wherein a maximum thickness of each the blade is located between 25% and 75% of a length of the increasing and decreasing thickness.

14. The impeller according to claim 9 , wherein at the inlet a lean angle of a leading edge of each blade with respect to a radial direction is approximately 30° so that the shroud profile lags behind the hub profile.

15. The impeller according to claim 9 , wherein the thickness increase and the thickness decrease are identically distributed on both sides of each blade.

16. A centrifugal compressor having a plurality of compressor stages, the compressor being tolerant to liquid at its inlet, wherein at least the first stage comprises an impeller according to claim 9 .

Assignees

• Nuovo Pignone Srl

Inventors

• Scotti Del Greco Alberto
• Arnone Andrea
• Checcucci Matteo
• Rubechini Filippo

Classifications

• F04D29/28 Primary

  for centrifugal or helico-centrifugal pumps {for radial-flow or helico-centrifugal pumps} · CPC title

• F04D29/284 Primary

  for compressors · CPC title

• F04D29/30

  Vanes · CPC title

• F04D29/289

  having provision against erosion or for dust-separation · CPC title

• F04D29/286

  multi-stage rotors · CPC title