Multistage centrifugal compressor

• US 4,938,661 A
• Filed: 09/08/1989
• Issued: 07/03/1990
• Est. Priority Date: 09/14/1988
• Status: Expired due to Term

• Current Assignee: Hitachi, Ltd.
• Original Assignee: Hitachi, Ltd.
• Inventors: Nishida, Hideo, Kobayashi, Hiromi, Miura, Haruo
• Primary Examiner(s): Garrett, Robert E.
• Assistant Examiner(s): NGUYEN, HOANG M
• Application Number:
  US07/404,597
• Time in Patent Office: 298 Days
• Field of Search: 415/199.1, 415/199.2, 415/199.3, 415/199.6, 415/208.1, 415/208.2, 415/208.3, 415/211.1, 415/211.2, 416/201 R, 416/201 A
• US Class Current: 415/199.1
• CPC Class Codes: F04D 17/122 the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
• CPC Class Codes: F04D 29/444 Bladed diffusers

Abstract

A multistage centrifugal compressor has a shaft rotatable on an axis and a plurality of centrifugal impellers fixed on the shaft and having outlets at outer peripheries thereof. Conduits connect the impellers to from a path for fluid undergoing multi-stage compression by the impellers from a suction side to a delivery side. The conduits including a plurality of diffusers arranged radially outwardly from the impellers, each impeller and associated diffuser constituting a stage. At least two of the diffusers are vaned diffusers provided with vanes having leading edges at their inlet ends. To provide high efficiency combined with low risk of rotating stalls, among the vaned diffusers, the ratio of diffuser vane leading edge radius to impeller outlet radius increases along the fluid path from the delivery of the compressor to the suction side.

Claims

1. A multistage centrifugal compressor comprising a shaft rotatably on an axis, a plurality of centrifugal impeller means fixed on said shaft each having an outlet at a periphery thereof, conduit means for connecting said impeller means to form a fluid compression path for fluid undergoing multi-stage compression by said impeller means from a suction side to a delivery side of the compressor, said conduit means including a plurality of diffuser means arranged radially outwardly from impeller means, each impeller means and associated diffuser means constituting a stage of the centrifugal compressor, said diffuser means including at least two vaned diffusers provided with vanes having leading edges at inlet ends thereof a first one of said at least two vaned diffusers has a ratio of diffuser vane leading edge radius to impeller outlet radius larger than a ratio of diffuser vane leading radius to impeller outlet radius ratio of a second of said at least two vaned diffusers, and wherein the second of said at least two vaned diffusers is closer along said fluid compression path to the delivery side of the compressor than said first one of said at least two vaned diffusers.

2. A compressor according to claim 1, wherein at least four centrifugal impeller means and at least four vaned diffusers are provided, and wherein said ratio of diffuser vane leading edge radius to impeller outlet radius increases from each of said vaned diffusers to the next vaned diffuser along the fluid compression path in the direction from the delivery side of the compressor to the suction side of the compressor.

3. A compressor according to claim 1, wherein in at least one stage a ratio of an axial height of the vanes of the vaned diffuser to the impeller outlet radius is less than 0.04.

4. A compressor according to claim 3, wherein the ratio of the axial height of the vanes of the vaned diffuser to the impeller outlet radius is less than 0.04 in each stage having a vaned diffuser.

5. A compressor according to claim 1, wherein the ratio of diffuser vane leading edge radius to impeller outlet radius in each stage having a vaned diffuser is determined in accordance with the following relationship:

space="preserve" listing-type="equation">r/R≦

1+3.3 h/R,

wherein;

h=an axial height of the vanes,

R=impeller outlet radius, and

r=diffuser vane leading edge radius.

6. A compressor according to claim 1, wherein in at least one stage a ratio of an axial height of the vanes to the impeller outlet radius is less than 0.03, and wherein in each stage having a vaned diffuser the ratio of diffuser vane leading edge radius to the impeller outlet radius is determined in accordance with the following relationship:

space="preserve" listing-type="equation">r/R≦

1+3.3 h/R

wherein;

h=the axial height of the vanes,

R=the impeller outlet radius, and

r=the diffuser vane leading edge radius.

7. A compressor according to claim 1, wherein said diffuser means further includes a vaneless diffuser provided in at least one stage of the centrifugal compressor at a position closer to the suction side of the compressor than the at least two vaned diffusers.

8. A compressor according to claim 1, wherein the compressor has an operating delivery pressure of at least 50 atmospheres.

9. A compressor according to claim 1, wherein a ratio of the outlet radius of the vanes of the vaned diffuser to an inlet radius of the vanes in not more than 1.2.

10. A compressor according to claim 1, a maximum thickness of each of the vaned diffuser is in a range of 5-12% of a chord length of the vane.

11. A compressor according to claim 1, wherein the number of vanes in a range of 10 to 30.

12. A multi-stage centrifugal compressor comprising a plurality of centrifugal impeller means fixed on a rotary shaft to provide a plurality of compression stages and a diffuser means at each of said stages with at least two of said diffuser means being vaned diffusers, and wherein at least at one of adjacent pairs of stages having vaned diffusers, a ratio of a vane of the vaned diffusers leading edge radius to an outlet radius of the impeller means is larger at a stage of said adjacent pairs which is closer to the a suction side of the compressor.

13. A multi-stage centrifugal compressor having a shaft rotatable on an axis, a plurality of centrifugal impeller means fixed on said shaft and having outlets at outer peripheries thereof, conduit means for connecting said impeller means to form a path for fluid undergoing multi-stage compression by said impeller means from a suction side to a delivery side of the compressor, said conduit means including a plurality of diffuser means arranged radially outwardly from the impeller means, each of said impeller means and associated diffuser means constituting a stage of the compressor, said diffuser means including at least two vaned diffusers provided with vanes having leading edges at inlet ends thereof, and wherein each of said vaned diffusers and associated impeller means have the following relationships:

space="preserve" listing-type="equation">h/R≦

0.04, and

space="preserve" listing-type="equation">r/R≦

1+3.3 h/R,

wherein;

h=an axial height of the vanes,

R=an impeller means outlet radius, and

r=a diffuser vane leading edge radius.

14. A compressor according to claim 13, wherein said diffuser means further includes a vaneless diffuser provided in at least one stage of the centrifugal compressor at a position closer to the delivery side of the compressor than the at least two vaned diffusers.

15. A compressor according to claim 13, wherein the compressor has an operating delivery pressure of at least 50 atmospheres.

16. A compressor according to claim 13, wherein a ratio of the outlet radius of the vanes of the vaned diffusers to an inlet radius of the vanes is not more than 1.2.

17. A compressor according to claim 13, wherein a maximum thickness of each vane of the vaned diffuser is in a range of 5 to 12% of a chord length of the vane.

18. A compressor according to claim 13, wherein the number of vanes in a range of 10 to 30.