US3778186A

US3778186A - Radial diffuser

Info

Publication number: US3778186A
Application number: US00229408A
Authority: US
Inventors: P Bandukwalla
Original assignee: Motors Liquidation Co
Current assignee: Motors Liquidation Co
Priority date: 1972-02-25
Filing date: 1972-02-25
Publication date: 1973-12-11
Anticipated expiration: 1990-12-11
Also published as: CA969148A; GB1407017A

Abstract

A diffuser for a centrifugal compressor has diffusing passages of circular or oval cross section which converge toward a throat and then diverge. The passages are of generally spiral curvature, at least in the converging portion. The entrances of the diffuser passages merge to define leading edges of generally elliptical shape between the passages.

Description

I United States Patent 11 1 1111 3,778,186 Bandukwalla Dec. 11, 1973 [54] RADIAL DIFFUSER 2,596,646 5/1952 Buchi 415/21] [75] Inventor: fhgroze Bandukwalla, Indianapolis, FOREIGN PATENTS OR APPLICATIONS 555,308 8/1943 Great Brltalm 415/2ll Assigneez General Motors Corporation, 85,754 6/1957 Netherlands HS/2H Detroit, Mich.

Primary Examiner-J-lenry F. Raduazo [22] Ffled' 1972 Attorney-Paul Fitzpatrick et al. [21] Appl. No.: 229,408

[57] ABSTRACT 52 U.S.Cl ..4l5 481,415 207,415 211 i isli 1m. (:1. 1 0411 21/06, F04d 2 1/44 A a femnfugall l i 158 Field of Search 415/181, 207, 211, Passages w 415/1316 1 verge toward a throat and then diverge. The passages are of generally spiral curvature, at least in the con- [561 1:55;?1: 3:22;2225;325:232fi'geiifzaz'21152::

UNITED STATES PATENTS sha e between the assa es. 3,333,762 8/1967 Vrana 415/181 p p g 2,708,883 5/1955 2 Claims, 5 Drawing Figures Keller et al. 415/211 RADIA'L DIFFUSER The invention described and claimed herein .was made in the course of work under a contract with the Department of Defense.

My invention is directed to diffusers for centrifugal compressors in which the flow from the rotor is supersonic.

The principal object of my invention is to improve the efficiency andsflexibility of radial flow compressors. It is a further object to provide a diffuser capable of accepting supersonic flow from. a radial flow impeller with a minimum ofnshock and a diffuser suitable for high Mach numberflows whichis of a compact structure.

A further object is to provide a diffuser having passages curvedto accord with the expanding vortical flow from the impeller.

A still furtherobject is to'provide a diffuser which is readily fabricated.

The nature of my invention and its advantages will be apparent to those skilled inthe art from the succeeding detailed description of the preferred embodiment of my invention.

FIG. 1 is apartial radial sectional view of a centrifugal compressorperpendicular to the axis of rotation of the rotor on the planes indicated by the line 1-1 in FIG. 4.

FIG. 2 is a fragmentary sectional view taken on the plane indicated by the line 2-2 in FIG. 1.

FIG. 3 is a fragmentary sectional view taken on the plane indicated by the line 3-3 in FIG. 1.

FIG. 4 isa fragmentary sectional view taken on the plane indicated by the line 4-4 in FIG. 1.

FIG. 5 is a fragmentary sectional view taken on the plane indicated by the line 5--5 in FIG. 1.

As is well known, centrifugal compressors are devicesin which a bladed rotoror impeller impels air (or other gas) in atangential and radial direction,=imparting a high velocity 'tothe air. The air delivered fromthe impeller, which is flowing radially and circumferentially of its axis ofrotatiomis delivered to a diffuser in which thezkineticenergy of the airis largely converted to potential energy of pressure. One example of a centrifugalcompressorsis disclosed in Atkinson U.S.Pat.

No. 2,819,012, Jan. 7, 1958. Another is shown in Conklin et al US. Pat. No. 3,027,717, Apr. 3, 1962. The following US. Pat. Nos. may also be of interest: Buchi No. 2,596-,646,May 13, 1952; Dallenbach et al. No. 2,967,0l3..lan..-3, 1961; and Vrana No. 3,333,762, Aug. 1, 1967. I

Since the general arrangement of centrifugal compressors is wellknown, there is no needhere to provide overall drawings of such a device. As illustrated in FIGS. 1 and 4,.the compressor 2 includes a rotor or impeller 3 havingtanannular disk 4 andblades 6 extending from theface of the disk. The rotor turns clockwise as illustrated inFIGQl. It dischargesair with a substantial radial component, and normally a greater circumferential component,.of velocity from the perimeter of .the rotor 3 intoa stationary diffuser 7.

The diffuser 7 is made up ofa back plate8 and a front plate 9, preferablymeeting on a plane surface. So

far as the diffuser portions of these plates are concerned, they arespreferablysymmetrical. The diffuser plates may continuetoward the axis of rotation to definea housing forithe compressor rotor or they may be fixedto such a housing. The diffuser may be machined from two annular plates having plane mating surfaces indicated by the line 11. The forward surface of the rearplate and the rear surface of the front plate are machined or otherwise formed to provide diffusing passages 12 with half of each passage in the back plate and half in the front plate, defined by grooves 13 in each plate. A cross-section of each passage 12, as will be apparent from FIGS. 4 and 5, is preferably elliptical, it being understood that a circle is a special case of an ellipse. The faces of the front and back plate immediately adjacent to the periphery of the rotor indicated at 14 and 15, respectively, in FIG. 4, andat 14 in FIG.;1 may be plane. The diffusing passages begin at the cylindrical surface indicated by broken line 16 in FIG. 1.

Each passage 12 has a curved generally logarithmic spiral centerline indicated by the broken line 18 in FIG. 1. The initial portions of these passages merge due to the intersection of the grooves 13, the passages intersecting in such manner as to provide a generally elliptical leading edge 20 (see particularly FIGS. 2 and 3) which constitutes the beginning of a dividing rib 22- having a flat upper surface corresponding to the junction plane 11 of FIGS. 2 and 3.

The diffusing passages 12 have an initial converging portion 23 which terminates at a throat 24. The section of FIG. 4 is taken near the throat of the passage indicated by the numeral 12 in that figure. Beyond the throat, the passage diverges as indicated by the successively

larger cross sections

30, 31,. and 32 in FIG. 5, the passages ultimately terminating in the exterior periphery 34 of the annular diffuser 7. The relatively slowly moving flow of air is then supplied from a suitable plenumsurrounding the diffuser (not illustrated) to the point of use.

The supersonic flow entering the diffuser is diffused in the initial converging portion 23 of the diffuser up to the throat 24. Since the centerlines 18 of the diffuser passages are curved to accord with the naturally vortexing flow coming off the impeller, diffusion is effectively and smoothly handled and no shock is experienced at the entrance to the throat 24 because the throat curves with the flow.

While the diffusing passages inthe diverging part of the diffuser may have a straight centerline, I prefer that the centerline still curve in a spiral as indicated in the drawing to avoid unnecessary deflection of a diffusing gas flow through the passage.

It will be noted that the diffusing passages as illustrated start off as a circular cross section and become elliptical towards their outer ends as illustrated in FIG. 5. Theentire cross section of the passage might be elliptical if desired, and the long axis of the ellipse inight be in a radial direction relative to the axisrather than parallel to the axis of rotation as illustrated in FIG. 5.

By virtue of the gradual entrance of the gas into the diffusing passages, and the conformity of the passages to the natural approximately logarithmic spiral of flow of the vortexing gas, there is no forced turning of the gas and smooth outlet conditions from the impeller and through the diffuser are obtained. a While I have referred to the mating surfaces of the sections of the diffuser as flat, obviously these surfaces could depart somewhat from a flat condition; for example, they might be in the shape of a very blunt cone or follow a spherical surface of large radius.

It will be apparentthat the passages can be formed by milling with a sphericalmill in a numerically controlled machine, for example. Also, the diffuser may be precision cast in the two pieces shown, or as a unit.

If in two pieces, the plates 8 and 9 may be bolted, cemented, or brazed together to provide the complete annular diffuser.

The detailed description of the preferred embodiment of the invention for the purpose of explaining the principles thereof is not to be considered as limiting or restricting the invention, since many modifications may be made by the exercise of skill in the art.

I claim:

1. A centrifugal compressor including a rotor discharging radially and tangentially of the axis of the rotor and a diffuser body defining diffuser passages having entrances adjacent the periphery of the rotor, the passages having arcuate cross-sections and merging adjacent the rotor so that the body defines approximately elliptical leading edges at the intersections of the passage boundaries, each passage including a first converging portion with a spiral centerline terminating at a throat and a second diverging portion beginning at and extending in a continuous spiral downstream from the throat.

2. A centrifugal compressor including a rotor discharging radially and tangentially of the axis of the rotor and a diffuser body defining diffuser passages having entrances adjacent the periphery of the rotor, the passages having arcuate cross-sections and merging adjacent the rotor so that the body defines approximately elliptical leading edges at the intersections of the passage boundaries, each passage including a first converging portion terminating at a throat and a second diverging portion beginning at and extending downstream from the throat, both portions having continuous spiral centerlines meeting at the throat.

Claims

1. A centrifugal compressor including a rotor discharging radially and tangentially of the axis of the rotor and a diffuser body defining diffuser passages having entrances adjacent the periphery of the rotor, the passages having arcuate crosssections and merging adjacent the rotor so that the body defines approximately elliptical leading edges at the intersections of the passage boundaries, each passage including a first converging portion with a spiral centerline terminating at a throat and a second diverging portion beginning at and extending in a continuous spiral downstream from the throat.