Centrifugal compressor and turbocharger

Abstract

An annular diffuser is formed on an outlet side of a wheel in a housing. A shroud-side wall surface and a hub-side wall surface of the diffuser are parallel to a radial direction, respectively. A plurality of annular steps is formed on the shroud-side wall surface of the diffuser. Each step is formed so as to expand a flow passage width of the diffuser along a flow direction of a main flow.

Claims

1. A centrifugal compressor configured to compress a fluid utilizing a centrifugal force, comprising: a housing having a shroud thereinside; a wheel rotatably provided in the housing; a diffuser formed outside in a radial direction of an outlet side of the wheel in the housing; and a scroll formed on an outlet side of the diffuser in the housing, wherein a shroud-side wall surface and a hub-side wall surface of the diffuser extend in the radial direction, respectively, wherein a plurality of steps is formed on the shroud-side wall surface of the diffuser so as to expand a flow passage width of the diffuser along a flow direction of a main flow, and wherein a step amount of each step is set to be 5 to 30% of a flow passage width of an outlet of the diffuser.

2. The centrifugal compressor according to claim 1, wherein a radial direction length of a portion continuous with an outside in a radial direction of each step in the shroud-side wall surface of the diffuser is set to be 5 to 30 times of a step amount of each step.

3. The centrifugal compressor according to claim 2, wherein the plurality of steps is formed annularly.

4. The centrifugal compressor according to claim 1, wherein the plurality of steps is formed annularly.

5. A turbocharger comprising the centrifugal compressor according to claim 1.

6. The centrifugal compressor according to claim 1, wherein the plurality of steps is integrally formed with the shroud-side wall surface of the diffuser.

7. A centrifugal compressor configured to compress a fluid utilizing a centrifugal force, comprising: a housing having a shroud thereinside; a wheel rotatably provided in the housing; a diffuser formed outside in a radial direction of an outlet side of the wheel in the housing; and a scroll formed on an outlet side of the diffuser in the housing, wherein a shroud-side wall surface and a hub-side wall surface of the diffuser extend in the radial direction, respectively, wherein a plurality of steps is formed on the shroud-side wall surface of the diffuser so as to expand a flow passage width of the diffuser along a flow direction of a main flow, and wherein a radial direction length of a portion continuous with an outside in a radial direction of each step in the shroud-side wall surface of the diffuser is set to be 5 to 30 times of a step amount of each step.

8. The centrifugal compressor according to claim 7, wherein the plurality of steps is formed annularly.

9. A turbocharger comprising the centrifugal compressor according to claim 7.

10. The centrifugal compressor according to claim 7, wherein the plurality of steps is integrally formed with the shroud-side wall surface of the diffuser.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is an enlarged view of an arrow part I in FIG. 3.

(2) FIG. 2A is an enlarged view of an arrow part II in FIG. 1, and FIGS. 2B and 2C are views showing different aspects of a step.

(3) FIG. 3 is a front cross-sectional view showing a centrifugal compressor etc. according to an embodiment of the present disclosure.

(4) FIG. 4A is a schematic view showing a configuration around a diffuser according to an inventive example, and FIG. 4B is a schematic view showing a configuration around a diffuser according to a comparative example.

(5) FIGS. 5A and 5B are views each showing a region where a low pressure part is generated in an actuating region of a large flow rate side (a choke side). FIG. 5A shows a case of the inventive example, FIG. 5B shows a case of the comparative example.

(6) FIGS. 6A and 6B are views each showing static pressure distribution in a scroll and the diffuser in an actuating region near a peak of compressor efficiency. FIG. 6A shows the case of the inventive example, FIG. 6B shows the case of the comparative example.

(7) FIG. 7 is a graph showing relations between flow rates and compressor efficiency in the inventive example and the comparative example.

DESCRIPTION OF THE EMBODIMENTS

(8) The present disclosure is based on a new knowledge mentioned below.

(9) Namely, the new knowledge is that development of flow separation (a separation vortex) is suppressed in an outlet 27o side of a shroud-side wall surface 27s of a diffuser 27 during operation of a centrifugal compressor, in a case where an annular step 35 is formed on the shroud-side wall surface 27s of the diffuser 27 under predetermined conditions (refer to FIG. 4A), compared with a case where the annular step 35 is not formed (refer to FIG. 4B), and that thereby, a low pressure part LP by the separation is reduced (refer to FIGS. 5A and 5B). The reason is considered as follows. The separation vortex was locally generated near the annular step 35 to generate the low pressure part LP near the shroud-side wall surface 27s of the diffuser 27, and thereby a flow of a main flow became easy to move along the shroud-side wall surface 27s of the diffuser 27 in a front side of an outlet 27o of the diffuser 27. In addition, the predetermined conditions are the following: the shroud-side wall surface 27s and a hub-side wall surface 27h of the diffuser 27 are parallel to a radial direction of a wheel, respectively; and the annular step 35 is formed so as to expand a flow passage width of the diffuser 27 along a flow direction of the main flow. Note that a symbol 27i in FIGS. 4A and 4B denotes an inlet of the diffuser 27 that communicates with a housing chamber (refer to FIG. 1) of a wheel (an impeller) 13.

(10) Here, FIG. 4A is a schematic view showing a configuration around the diffuser 27 according to an inventive example. FIG. 4B is a schematic view showing a configuration around the diffuser 27 according to a comparative example. FIGS. 5A and 5B are views each showing a region where a low pressure part is generated in an actuating region of a large flow rate side (a choke side). FIG. 5A shows the case of the inventive example, FIG. 5B shows the case of the comparative example. In addition, the region where the low pressure part LP was generated was determined by CFD (Computational Fluid Dynamics) analysis. Further, although illustration is omitted, similar analysis results could be obtained not only in the actuating region of the large flow rate side but also in actuating regions of a small flow rate side (a surge side) and near a peak of compressor efficiency.

(11) An embodiment of the present disclosure will be explained with reference to FIGS. 1 to 3. Note that L is a left direction, and R is a right direction as shown in the drawings.

(12) As shown in FIGS. 1 and 3, a centrifugal compressor 1 according to the embodiment of the present disclosure is used for a turbocharger 3, and compresses air utilizing a centrifugal force.

(13) The centrifugal compressor 1 includes a housing (a compressor housing) 5. The housing 5 includes a housing body 7 having a shroud 7s thereinside, and a seal plate 9 provided on a right side of the housing body 7. Note that the seal plate 9 is coupled integrally with another housing (a bearing housing) 11 in the turbocharger 3.

(14) In the housing 5, the wheel (the compressor wheel) 13 is rotatably provided around an axial center C thereof. The wheel 13 is coupled integrally with a left end of a rotation shaft 19. The rotation shaft 19 is rotatably provided in the housing 11 through a plurality of thrust bearings 15 and a plurality of (only one is shown) radial bearings 17. In addition, the wheel 13 includes a disk 21. The disk 21 has a hub surface 21h. The hub surface 21h extends outside in a radial direction (a radial direction of the wheel 13) from a left direction (one side in an axial direction of the wheel 13). Further, on the hub surface 21h of the disk 21, a plurality of blades 23 with a same axial length is integrally formed spaced apart from each other in a peripheral direction. A tip edge 23t of each blade 23 extends along the shroud 7s of the housing body 7. Note that plural types of blades (illustration is omitted) with different axial lengths may be used instead of using the plurality of blades 23 with the same axial length.

(15) An introducing port (an introducing flow passage) 25 is formed on an inlet side of the wheel 13 in the housing body 7. The introducing port 25 introduces air into the housing 5. In addition, the introducing port 25 is connected to an air cleaner (illustration is omitted) that purifies the air. The diffuser (the diffuser flow passage) 27 is formed on an outlet side of the wheel 13 in the housing 5. The diffuser 27 decreases a velocity of compressed air (compression air) to thereby raise a pressure thereof. The diffuser 27 is, for example, formed annularly. A throttle part (a throttle flow passage) 29 is formed between the wheel 13 and the diffuser 27 in the housing 5. A flow passage width of the throttle part 29 becomes gradually smaller along the flow direction of the main flow. The throttle part 29 is, for example, formed annularly. The throttle part 29 communicates with the diffuser 27.

(16) A scroll (a scroll flow passage) 31 is formed on an outlet side of the diffuser 27 in the housing 5. The scroll 31 is formed spirally. The scroll 31 communicates with the diffuser 27. A cross-sectional area of a winding end side (a downstream side) of the scroll 31 is larger than that of a winding start side (an upstream side) thereof. A discharge port (a discharge flow passage) 33 is formed in an appropriate position of the housing body 7. The discharge port 33 discharges compressed air outside the housing 5. The discharge port 33 communicates with the scroll 31, and is connected to an intake pipe (illustration is omitted) of an engine side, such as an intake manifold or an intercooler of an engine.

(17) As shown in FIGS. 1 and 2A, the shroud-side wall surface 27s and the hub-side wall surface 27h of the diffuser 27 are provided extending in the radial direction (radial direction of the wheel 13). For example, they can be parallel to the radial direction, respectively. Note that the shroud-side wall surface 27s means a wall surface located on a side of a surface in which the shroud 7s of the housing body 7 has extended outside in the radial direction. The hub-side wall surface 27h means a wall surface located on a side of a surface in which the hub surface 21h of the disk 21 has extended outside in the radial direction. Here, the above-mentioned parallelism need not be strict. Namely, the shroud-side wall surface 27s and the hub-side wall surface 27h may incline in the radial direction at angles of approximately several degrees.

(18) The plurality of annular steps 35 is formed in an intermediate part of the shroud-side wall surface 27s of the diffuser 27 (between the inlet 27i and the outlet 27o of the diffuser 27). Each step 35 is formed so as to expand the flow passage width of the diffuser 27 along the flow direction of the main flow. Each step 35 locally generates a separation vortex. Each step 35 is parallel to a flow passage width direction (a horizontal direction) of the diffuser 27. However, each step 35 may linearly or curvedly incline to the flow passage width direction of the diffuser 27 as shown in FIG. 2B. Further, the number of the steps 35 may be a single (one) as shown in FIG. 2C. Here, the above-mentioned parallelism need not be strict.

(19) The steps 35 need not be a continuous annular shape. For example, the step 35 may be provided only in a particular region in the peripheral direction, such as a vicinity of a tongue of the scroll winding end side. However, machining becomes easy when the step 35 is formed annularly.

(20) The number of the steps 35 may be arbitrarily selected according to engine specifications. However, for example, an effect can be exerted at a pinpoint in a particular actuating region by providing the single step 35, and an effect can be exerted in a wider actuating region compared with a case of providing the single step 35, by providing the plurality of steps 35. Here, two steps 35 can be provided as one example of providing the plurality of steps 35. Time and effort required for machining work of the steps are suppressed as much as possible by providing the two steps 35, and an effect can be exerted in a wider range compared with the case of providing the single step 35.

(21) A step amount of the step 35 is set to be 5 to 30% of a flow passage width of the outlet 27o of the diffuser 27, and is preferably set to be 10 to 20% (0.05 to 0.30 times, and preferably, 0.10 to 0.20 times). It is because if the step amount is less than 5%, it might become difficult to locally generate a separation vortex with sufficient strength (vorticity) near the step 35 that the step amount is made to be set to be not less than 5% of the flow passage width . Meanwhile, it is because if the step amount exceeds 30%, the separation vortex (separation) generated by the step 35 might increase that the step amount is set to be less than 30% of the flow passage width .

(22) The shroud-side wall surface 27s of the diffuser 27 has a portion continuous with (adjacent to) an outside in a radial direction of the step 35. A length in the radial direction of the portion is set to be 5 to 30 times of the step amount of the step 35, and is preferably set to be 10 to 20 times thereof. It is because if the length is less than 5 times, it might become difficult to make the flow of the main flow move along the shroud-side wall surface 27s of the diffuser 27 in the front side of the outlet 27o of the diffuser 27 that the length is made to be set to be not less than 5 times of the step amount . Meanwhile, it is because if the length exceeds 30 times, a separation vortex (separation) of a new flow might be generated on the front side of the outlet 27o of the diffuser 27 in the shroud-side wall surface 27s of the diffuser 27, and an effective flow passage area in the diffuser 27 might decrease that the length is set to be not more than 30 times of the step 35.

(23) Subsequently, actions and effects of the embodiment of the present disclosure will be explained.

(24) The wheel 13 is rotated integrally with the rotation shaft 19 around the axial center of the wheel 13 by drive of a radial turbine (illustration is omitted) in the turbocharger 3, and thereby air introduced into the housing 5 from the introducing port 25 can be compressed. A pressure of the compressed air (compression air) is then raised, while a velocity thereof is decreased by the diffuser 27, and the air whose pressure has been raised is discharged outside the housing 5 from the discharge port 33 via the scroll 31.

(25) The shroud-side wall surface 27s and the hub-side wall surface 27h of the diffuser 27 are parallel to the radial direction, respectively. In addition, the annular step 35 is formed in the intermediate part of the shroud-side wall surface 27s of the diffuser 27 so as to expand the flow passage width of the diffuser 27 along the flow direction of the main flow. Therefore, when the above-mentioned new knowledge is applied, development of the flow separation (separation vortex) in the outlet 27o side of the diffuser 27 in the shroud-side wall surface 27s is suppressed during operation of the centrifugal compressor 1 (operation of the turbocharger 3), and a low pressure part (a blockage, a low pressure region, or a block region) due to the separation can be reduced.

(26) Accordingly, according to the embodiment of the present disclosure, development of the flow separation of the outlet 27o side of the diffuser 27 in the shroud-side wall surface 27s can be suppressed during the operation of the centrifugal compressor 1. Therefore, decrease of an effective flow passage area of the outlet 27o side of the diffuser 27 can be suppressed. Accordingly, a velocity of the flow of the main flow can be sufficiently decreased by the diffuser 27. In addition, the low pressure part LP due to the flow separation of the outlet 27o side of the diffuser 27 in the shroud-side wall surface 27s can be reduced during the operation of the centrifugal compressor 1. Therefore, collision (interference) of the low pressure part LP and the flow of the main flow in the scroll 31 can be lessened to thereby suppress occurrence of turbulence in the flow of the main flow in the discharge port 33 located on a downstream side of the scroll 31. Consequently, according to the embodiment of the present disclosure, improvement in compressor efficiency of the centrifugal compressor 1 can be achieved, while enhancing static pressure recovery performance of the diffuser 27.

(27) Note that the present invention is not limited to the above-mentioned disclosure of the embodiment, and that it can be carried out in other various aspects, such as applying a technical idea applied to the centrifugal compressor 1 to a gas turbine, an industrial air facility, etc., or arranging a plurality of diffuser vanes (illustration is omitted) spaced apart from each other in a peripheral direction in the diffuser 27. In addition, the scope of right encompassed in the present invention is not limited to these embodiments.

EXAMPLES

(28) Examples of the present disclosure will be explained with reference to FIGS. 6A, 6B, and 7.

(29) CFD analysis of static pressure distribution in a scroll and a diffuser in an actuating region near a peak of compressor efficiency was performed to the inventive example (refer to FIG. 4A) and the comparative example (refer to FIG. 4B). As a result, it could be confirmed that a static pressure in the scroll could be made to be higher as a whole in the inventive example shown in FIG. 6A, compared with the comparative example shown in FIG. 6B. In other words, it could confirm that static pressure recovery performance of the diffuser could be made to be higher in the inventive example. In addition, although illustration is omitted, similar analysis results could be obtained not only in the actuating region near the peak of the compressor efficiency but also in actuating regions of a small flow rate side and a large flow rate side. Note that numerical values in FIGS. 6A and 6B denote dimensionless static pressures in the scroll.

(30) In addition, there was performed CFD analysis of a relation between a flow rate and compressor efficiency in the inventive example (refer to FIG. 4A) and the comparative example (refer to FIG. 4B). As a result, as shown in FIG. 7, it was confirmed that compressor efficiency was more improved in a wide actuating region from the small flow rate side to the large flow rate side in the inventive example compared with the comparative example.