US20130094955A1 - Centrifugal compressor diffuser and centrifugal compressor provided with the same - Google Patents

Centrifugal compressor diffuser and centrifugal compressor provided with the same Download PDF

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Publication number
US20130094955A1
US20130094955A1 US13/806,384 US201113806384A US2013094955A1 US 20130094955 A1 US20130094955 A1 US 20130094955A1 US 201113806384 A US201113806384 A US 201113806384A US 2013094955 A1 US2013094955 A1 US 2013094955A1
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United States
Prior art keywords
hub
shroud
side blades
blades
top ends
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Abandoned
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US13/806,384
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English (en)
Inventor
Seiichi Ibaraki
Koichi Sugimoto
Keiichi Shiraishi
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD. reassignment MITSUBISHI HEAVY INDUSTRIES, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: IBARAKI, SEIICHI, SHIRAISHI, KEIICHI, SUGIMOTO, KOICHI
Publication of US20130094955A1 publication Critical patent/US20130094955A1/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the present invention relates to a diffuser and a centrifugal compressor provided with the same, and more specifically, it relates to a diffuser in which blades having different inlet angles are combined in a blade height direction.
  • FIG. 14 shows the relevant part of a centrifugal compressor disclosed in PTL 1, which is a known centrifugal compressor.
  • FIG. 14(A) is a vertical cross-sectional view
  • FIG. 14(B) is a side view
  • FIG. 14(C) is an enlarged perspective view of a shroud-side blade and a hub-side blade
  • FIG. 14(D) is a top view of FIG. 14(C) .
  • a centrifugal compressor 50 shown in FIG. 14 compresses fluid, such as gas or air, introduced from the outside of a housing 51 by rotating an impeller 53 having multiple blades 52 in the housing 51 .
  • the thus-formed flow of fluid (airflow) is directed outside through an impeller outlet 54 (also referred to as a “diffuser inlet”), which constitutes an outer circumferential edge of the impeller 53 ; a diffuser 55 ; and a volute 56 .
  • the reference numeral 57 in the figure represents the axis of rotation of the impeller 53 .
  • the above-mentioned diffuser 55 is an airflow path provided between the impeller outlet 54 and the volute 56 and has a function of converting dynamic pressure to static pressure by decelerating the airflow discharged from the impeller outlet 54 .
  • this diffuser 55 is formed of a pair of opposing walls. In the description below, one of the pair of opposing walls is referred to as a shroud-side wall 58 and the other as a hub-side wall 2 .
  • a plurality of diffuser blades 60 are provided between the shroud-side wall 58 and the hub-side wall 2 .
  • These diffuser blades 60 include a plurality of shroud-side blades 3 provided on the shroud-side wall 58 and a plurality of hub-side blades 4 provided on the hub-side wall 2 .
  • the shroud-side blades 3 and the hub-side blades 4 are two-dimensional blades having different blade inlet angles and combined in the blade height direction.
  • the combined shroud-side blades 3 and hub-side blades 4 may not overlap one another downstream of the leading edges of the diffuser blades 60 , and thus, gaps 63 may be formed. If the gaps 63 are formed between the shroud-side blades 3 and the hub-side blades 4 , as in this case, airflow separation and generation of vortices (represented by spiral arrows in FIGS. 14(C) and 14(D) ) occur due to the influence of the airflow passing through the gaps 63 , leading to a problem in that the performance of the diffuser 55 is lowered.
  • the present invention has been made in view of these circumstances, and an object thereof is to provide a centrifugal compressor diffuser that can be improved in performance by combining blades having different inlet angles in the blade height direction and a centrifugal compressor provided with the same.
  • the present invention provides the following solutions.
  • a centrifugal compressor diffuser includes a shroud-side wall provided downstream of a centrifugal impeller; a hub-side wall provided so as to face the shroud-side wall; a plurality of shroud-side blades fixed at base ends thereof to the shroud-side wall; and a plurality of hub-side blades fixed at base ends thereof to the hub-side wall.
  • the shroud-side blades and the hub-side blades are combined in such a state that inlet angles thereof differ from one another and that at least portions of top ends thereof in a blade height direction are abutted onto one another.
  • a connecting member that connects the top ends so as to fill at least portions of the gaps is provided.
  • a centrifugal compressor diffuser including shroud-side blades and hub-side blades combined in such a state that inlet angles thereof differ from one another and that at least portions of top ends thereof in a blade height direction are abutted onto one another, gaps where the top ends of the combined shroud-side blades and hub-side blades are not abutted onto one another are sometimes formed.
  • gaps where the top ends of the shroud-side blades and hub-side blades are not abutted onto one another are formed, the performance of the diffuser is lowered due to separation of flow passing through the gap portions and generation of vortices.
  • a connecting member which connects the top ends so as to fill at least portions of the gaps formed due to the top ends of the combined shroud-side blades and hub-side blades not being abutted onto one another.
  • the gaps formed between the top ends of the shroud-side blades and the top ends of the hub-side blades are covered by the connecting member.
  • the connecting member because the gaps formed between the top ends of the shroud-side blades and hub-side blades are connected by the connecting member, the rigidity of the blades can be increased. Accordingly, it is possible to improve the vibration strength of the blades.
  • the connecting member may have a ring-like shape that continuously connects all of the top ends of the plurality of shroud-side blades and hub-side blades in a circumferential direction.
  • the connecting member may have a ring-like shape and may continuously connect all of the top ends of the shroud-side blades and hub-side wall blades.
  • the connecting member has a simple, ring-like shape, the performance of the diffuser can be improved at low cost.
  • the inside diameter of the ring-like connecting member may be smaller than the inside diameter of the shroud-side wall and hub-side wall.
  • the inventors found that, also in the case where the inside diameter of the ring-like connecting member is smaller than the inside diameter of the shroud-side wall and hub-side wall, similarly to the case where the inside diameter of the ring-like connecting member is equal to the inside diameter of the shroud-side wall and hub-side wall, it is possible to eliminate a flow passing through the gaps formed between the top ends of the shroud-side blades and hub-side blades when combined and to improve the performance of the diffuser.
  • the connecting member may be provided so as to fill an area from leading edges of the top ends of at least one of the combined shroud-side blades and hub-side blades to 60% positions in the length of the blades on the downstream side.
  • the inventors found that the gaps formed from the leading edges of the top ends of at least one of the shroud-side blades and the hub-side blades to 60% positions in the length of the blades on the downstream side cause a notable deterioration in performance due to flow separation and generation of vortices caused by the flow in the gaps.
  • the connecting member is provided in the circumferential direction so as to fill the gaps between the tip ends from the leading edges of the top ends of at least one of the shroud-side blades and the hub-side blades to 60% positions in the length of the blades on the downstream side.
  • the combined shroud-side blades and hub-side blades may be arranged such that their leading edges are shifted from one another in the circumferential direction.
  • the shroud-side blades and the hub-side blades combined therewith may be provided such that their leading edges are shifted from one another in the circumferential direction.
  • gaps are not formed between the leading edges of the top ends of the shroud-side blades and hub-side blades. Accordingly, it is possible to prevent flow separation and generation of vortices caused by the flow in the gaps and to improve the performance of the diffuser.
  • the combined shroud-side blades and hub-side blades may be arranged so as to be shifted from one another in the circumferential direction such that they do not overlap one another from the leading edges to 60% positions in the entire length of the blades.
  • the shroud-side blades and the hub-side blades combined therewith may be provided so as to be shifted from one another in the circumferential direction such that they do not overlap one another from the leading edges to 60% positions in the entire length of the blades.
  • gaps are not formed from the leading edges of the shroud-side blades and hub-side blades to 60% positions in the entire length of the blades. Accordingly, it is possible to suppress flow separation and generation of vortices caused by the flow in the gaps and to improve the performance of the diffuser.
  • a centrifugal compressor diffuser includes a shroud-side wall provided downstream of a centrifugal impeller; a hub-side wall provided so as to face the shroud-side wall; a plurality of shroud-side blades fixed at base ends thereof to the shroud-side wall; and a plurality of hub-side blades fixed at base ends thereof to the hub-side wall.
  • the shroud-side blades and the hub-side blades are combined in such a state that inlet angles thereof differ from one another and that top ends thereof in a blade height direction are abutted onto one another, with portions thereof in a thickness direction overlapping one another over the blade lengths.
  • the shroud-side blades and the hub-side blades have different inlet angles and their top ends in the blade height direction are abutted onto one another such that portions thereof in the thickness direction overlap one another over the blade lengths.
  • gaps are not formed between the top ends of the shroud-side blades and hub-side blades when the shroud-side blades and the hub-side blades are combined. Accordingly, it is possible to prevent flow separation and generation of vortices caused by the flow in the gaps and to improve the performance of the diffuser.
  • the rigidity of the blades can be increased. Accordingly, it is possible to improve the vibration strength of the blades.
  • the thicknesses of the shroud-side blades and hub-side blades are smaller at the trailing edges than at middle portions in the length direction.
  • the thicknesses of the shroud-side blades and hub-side blades may be smaller at the trailing edges than at the middle portions in the length direction. Thus, it is possible to reduce the wake of the shroud-side blades and hub-side blades. Accordingly, it is possible to improve the performance of the diffuser.
  • either the shroud-side blades or the hub-side blades may be thick blades and the other may be thin blades.
  • Either the shroud-side blades or the hub-side blades may be thick blades (for example, blades having a wedge shape or a channel shape in cross-section perpendicular to the blade height direction) and the other may be thin blades.
  • the shroud-side blades and the hub-side blades are abutted onto one another, the top ends of the thin blades overlap portions of the top ends of the thick blades.
  • gaps are not formed between the top ends of the shroud-side blades and the top ends of the hub-side blades. Accordingly, it is possible to prevent flow separation and generation of vortices caused by the flow in the gaps and to improve the performance of the diffuser.
  • the width of the thick blades in cross-section perpendicular to the blade height direction be about two or more times greater than that of the thin blades.
  • a centrifugal compressor diffuser includes the centrifugal compressor diffuser according to any one of the above-described aspects.
  • a diffuser whose performance can be improved by suppressing flow separation and generation of vortices in the gaps where the top ends of the combined shroud-side blades and hub-side blades are not abutted onto one another is used.
  • it is possible to efficiently convert the speed energy of the flow passing through the diffuser into pressure. Accordingly, it is possible to improve the efficiency of the centrifugal compressor and to expand the operability thereof.
  • a connecting member which connects the top ends so as to fill at least portions of gaps formed due to the top ends of the combined shroud-side blades and hub-side blades not being abutted onto one another.
  • the gaps formed between the top ends of the shroud-side blades and the top ends of the hub-side blades are covered by the connecting member.
  • the rigidity of the blades can be increased. Accordingly, it is possible to improve the vibration strength of the blades.
  • FIG. 1 shows a shroud-side blade and a hub-side blade provided in a centrifugal compressor diffuser according to a first embodiment of the present invention, in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 2 shows a second modification of the blades shown in FIG. 1 , in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 3 shows a shroud-side blade and a hub-side blade provided in a centrifugal compressor diffuser according to a second embodiment of the present invention, in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 4 is a top view of a first modification of the blades shown in FIG. 3 .
  • FIG. 5 is a top view of a second modification of the blades shown in FIG. 3 .
  • FIG. 6 shows a shroud-side blade and a hub-side blade of a centrifugal compressor diffuser according to a fourth embodiment of the present invention, in which (A) is a perspective view thereof, (B) is a top view of (A), and (C) is a cross-sectional view taken along line A-A in (A) and (B).
  • FIG. 7 shows a shroud-side blade and a hub-side blade provided in a centrifugal compressor diffuser according to a fifth embodiment of the present invention, in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 8 shows a shroud-side blade and a hub-side blade provided in a centrifugal compressor diffuser according to a sixth embodiment of the present invention, in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 9 shows a modification of the blades shown in FIG. 8 , in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 10 shows a shroud-side blade and a hub-side blade provided in a centrifugal compressor diffuser according to a seventh embodiment of the present invention, in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 11 shows a modification of the blades shown in FIG. 10 , in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 12 shows a shroud-side blade and a hub-side blade provided in a centrifugal compressor diffuser according to an eighth embodiment of the present invention, in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 13 shows a modification of the blades shown in FIG. 12 , in which (A) is a perspective view thereof, and (B) is a top view of (A).
  • FIG. 14 shows the relevant part of a known centrifugal compressor, in which (A) is a vertical cross-sectional view, (B) is a side view, (C) is an enlarged perspective view of the shroud-side blade and the hub-side blade, and (D) is a top view of (C).
  • Shroud-side blades and hub-side blades provided in a centrifugal compressor diffuser according to a first embodiment of the present invention will be described with reference to FIGS. 1 and 14 .
  • a diffuser 1 shown in FIG. 1 converts dynamic pressure of an airflow to static pressure by decelerating the airflow (flow) discharged from an outer circumferential edge of an impeller 53 (see FIG. 14 ) rotating inside a housing 51 (see FIG. 14 ) of a centrifugal compressor 50 (see FIG. 14 ).
  • This diffuser 1 includes a shroud-side wall 58 provided downstream of the impeller (centrifugal impeller) 53 , a hub-side wall 2 provided so as to face the shroud-side wall 58 , a plurality of shroud-side blades 3 ( FIG. 1 shows only one of them) fixed at base ends thereof to the shroud-side wall 58 , and a plurality of hub-side blades 4 ( FIG. 1 shows only one of them) fixed at base ends thereof to the hub-side wall 2 .
  • the shroud-side blades 3 and the hub-side blades 4 are two-dimensional thin blades provided with the same length.
  • the shroud-side blades 3 and the hub-side blades 4 are combined in such a state that inlet angles thereof differ from one another and that the leading edges (at least portions thereof) of their top ends in the blade height direction are abutted onto one another. Their trailing edges are separated in the circumferential direction.
  • connecting walls (connecting members) 5 connecting the top ends are provided so as to fill the gaps 63 .
  • the connecting walls 5 are provided along the entire length, from the leading edges to the trailing edges, of the shroud-side blades 3 and hub-side blades 4 .
  • the connecting walls 5 in the gaps 63 between the shroud-side blades 3 and the hub-side blades 4 By providing the connecting walls 5 in the gaps 63 between the shroud-side blades 3 and the hub-side blades 4 , the airflow guided from the leading edges of the shroud-side blades 3 flows along the top surfaces of the connecting walls 5 (upper side in FIG. 1(A) ). Thus, it is possible to suppress airflow separation and generation of vortices caused by the flow in the gaps.
  • the diffuser 1 of a centrifugal compressor and the centrifugal compressor provided with the same according to the first embodiment provide the following advantages.
  • the connecting walls (connecting members) 5 connecting the top ends of the shroud-side blades 3 and hub-side blades 4 are provided so as to fill the gaps 63 (see FIG. 14 ) where the top ends of the combined shroud-side blades 3 and hub-side blades 4 are not abutted onto one another.
  • the gaps 63 formed between the top ends of the shroud-side blades 3 and hub-side blades 4 are covered by the connecting walls 5 .
  • the rigidity of the shroud-side blades 3 and hub-side blades 4 can be increased. Accordingly, it is possible to improve the vibration strength of the shroud-side blades 3 and hub-side blades 4 .
  • the connecting walls 5 are provided over the entire blade length, from the leading edges to the trailing edges, of the shroud-side blades 3 and hub-side blades 4 in the first embodiment, the present invention is not limited thereto.
  • the connecting walls 5 may cover the gaps 63 from the leading edges of the shroud-side blades 3 and hub-side blades 4 to some midpoint (for example, 60% of the blade length) in the length of the blades.
  • the inventors found that the gaps 63 formed from the leading edges of at least one of the shroud-side blades 3 and the hub-side blades 4 to 60% positions in the length of the blades cause a notable deterioration in performance due to flow separation and generation of vortices caused by the flow in the gaps.
  • the gaps 63 between the tips from the leading edges of the shroud-side blades 3 and hub-side blades 4 to 60% positions in the length of the blades are connected by the connecting walls 5 , similarly to the case where the connecting walls 5 are provided so as to fill the gaps 63 over the entire blade length from the leading edges to the trailing edges, it is possible to suppress flow separation and generation of vortices caused by the flow in the gaps. Accordingly, it is possible to improve the performance of the diffuser 1 .
  • hub-side blades 6 may have a smaller length than the shroud-side blades 3 , as shown in FIG. 2 .
  • FIG. 2(A) shows a perspective view of the second modification of the first embodiment, and (B) shows a top view of (A).
  • the hub-side blades 6 have a smaller length than the shroud-side blades 3 .
  • the leading edges of the hub-side blades 6 are located at some midpoint, on the downstream side, in the length of the shroud-side blades 3 .
  • connecting walls (connecting members) 7 substantially parallel to the shroud-side wall 58 and the hub-side wall are provided. Because the leading edges of the hub-side blades 6 are located at some midpoint, on the downstream side, in the shroud-side blades 3 , the connecting walls 7 are provided over the entire length of the hub-side blades 6 from the leading edges to the trailing edges of the hub-side blades 6 .
  • connecting walls 7 according to the second modification may cover the gaps from the leading edges of the hub-side blades 6 to some midpoint (for example, 60% of the blade length) in the length of the hub-side blades 6 .
  • a diffuser according to a second embodiment differs from that according to the first embodiment in that a disc connecting all of the top ends of the shroud-side blades and hub-side blades is provided; the other configurations are the same. Therefore, the same structures will be denoted by the same reference numerals, and descriptions thereof will be omitted.
  • a disc (connecting member) 8 continuously connects top ends of a plurality of (only one in FIG. 3 ) shroud-side blades 3 and hub-side blades 4 in a circumferential direction.
  • the disc 8 has a ring-like shape and is provided substantially parallel to the shroud-side wall 58 and the hub-side wall (not shown).
  • the disc 8 has a ring-like shape similarly to the shroud-side wall 58 and the hub-side wall.
  • the ring-like disc 8 is provided from the leading edges to the trailing edges of the shroud-side blades 3 and hub-side blades 4 .
  • the airflow does not pass through the gaps where the top ends of the combined shroud-side blades 3 and hub-side blades 4 are not abutted onto one another, and hence, it is possible to suppress airflow separation and generation of vortices caused by the flow in the gaps.
  • the diffuser 1 of a centrifugal compressor and the centrifugal compressor provided with the same according to the second embodiment provide the following advantages.
  • the disc (connecting member) 8 has a ring-like shape and continuously connects all of the top ends of the shroud-side blades 3 and hub-side blades 4 .
  • the gaps formed between the shroud-side blades 3 and the hub-side blades 4 are covered by the disc 8 , whereby the flow in the gaps can be eliminated.
  • the disc 8 has a simple, ring-like shape, the performance of the diffuser 1 can be improved at low cost.
  • the present invention is not limited thereto.
  • the hub-side blades 6 may have a smaller length than the shroud-side blades 3 , as shown in FIG. 4 .
  • the hub-side blades 6 may have a smaller length than the shroud-side blades 3 , and the circumferential phases of the hub-side blades 3 and shroud-side blades 6 may be differentiated, as shown in FIG. 5 .
  • shroud-side blades 3 and the hub-side blades 6 having a smaller length than the shroud-side blades 3 are provided such that their leading edges and trailing edges are located at different positions in the circumferential direction, and hence, they do not overlap one another.
  • a diffuser according to a third embodiment differs from that according to the second embodiment in the inside diameter of the disc connecting all of the top ends of the shroud-side blades and hub-side blades; the other configurations are the same. Accordingly, descriptions of the same structures will be omitted.
  • the ring-like disc (connecting member) continuously connecting all of the top ends of the plurality of shroud-side blades and hub-side blades in the circumferential direction has a smaller inside radius than a radius defined by the leading edges of the shroud-side blades and hub-side blades.
  • the inner circumferential edge of the ring-like disc extends in the inside diameter direction beyond the leading edges of the shroud-side blades and hub-side blades; that is, the leading edges of the shroud-side blades and hub-side blades are provided at some midpoint in the disc in the radial direction.
  • the centrifugal compressor diffuser and the centrifugal compressor provided with the same according to the third embodiment provide the following advantages.
  • the inventors found that, also in the case where the inside diameter of the ring-like disc (connecting member) is smaller than the radius defined by the leading edges of the shroud-side blades and hub-side blades, it is possible to eliminate a flow passing through the gaps formed between the shroud-side blades and the hub-side blades and to improve the performance of the diffuser, similarly to the case where the inside diameter of the ring-like disc is the same as the radius defined by the leading edges of the shroud-side blades and hub-side blades.
  • a diffuser according to a fourth embodiment differs from that according to the first embodiment in that the leading edges of the shroud-side blades and hub-side blades are located at positions shifted from one another in the circumferential direction; the other configurations are the same. Therefore, the same structures will be denoted by the same reference numerals, and descriptions thereof will be omitted.
  • FIG. 6 A fourth embodiment of the present invention will be described below using FIG. 6 .
  • the combined shroud-side blades 3 and hub-side blades 4 are arranged such that their leading edges are shifted from one another in the circumferential direction, and such that their trailing edges are shifted from one another in the circumferential direction.
  • the shroud-side blades 3 and the hub-side blades 4 are shifted from one another in the circumferential direction such that they do not overlap one another at least from the leading edges to 60% positions in the length of the blades.
  • FIG. 6(C) which is the cross-section taken along line A-A in FIG. 6(B)
  • the shroud-side blades 3 and the hub-side blades 4 are separated over the entire blade length from the leading edges to the trailing edges of the shroud-side blades 3 and hub-side blades 4 .
  • the shroud-side blades 3 and the hub-side blades 4 may overlap one another beyond the 60% positions in the length of the blades from the leading edges.
  • the shroud-side blades 3 and the hub-side blades 4 may overlap one another beyond the 60% positions in the length of the blades from the leading edges”, which allows gaps to be formed after those positions.
  • the diffuser 1 of a centrifugal compressor and the centrifugal compressor provided with the same according to the fourth embodiment provide the following advantages.
  • the leading edges and the trailing edges of the combined shroud-side blades 3 and hub-side blades 4 are provided at positions shifted from one another in the circumferential direction. Thus, gaps are not formed between the top ends of the leading edges of the shroud-side blades 3 and hub-side blades 4 when the shroud-side blades 3 and the hub-side blades 4 are combined. Accordingly, it is possible to prevent flow separation and generation of vortices caused by the flow in the gaps, improving the performance of the diffuser 1 .
  • a diffuser according to a fifth embodiment differs from that according to the fourth embodiment in that a disc connecting top ends of the shroud-side blades and hub-side blades is provided; the other configurations are the same. Therefore, the same structures will be denoted by the same reference numerals, and descriptions thereof will be omitted.
  • the disc (connecting member) 8 has a ring-like shape similarly to the shroud-side wall 58 and the hub-side wall (not shown), and is provided substantially parallel to the shroud-side wall 58 and the hub-side wall.
  • the ring-like disc 8 is provided from the leading edges to the trailing edges of the shroud-side blades 3 and hub-side blades 4 .
  • the diffuser 1 of a centrifugal compressor and the centrifugal compressor provided with the same according to the fifth embodiment provide the following advantages.
  • the disc (connecting member) 8 has a ring-like shape and continuously connects all of the top ends of the shroud-side blades 3 and hub-side blades 4 .
  • the gaps formed between the top ends of the shroud-side blades 3 and hub-side blades 4 are covered by the disc 8 , whereby a flow in the gaps can be eliminated.
  • the disc 8 has a simple shape, i.e., a ring-like shape, the performance of the diffuser 1 can be improved at low cost.
  • a diffuser according to a sixth embodiment differs from that according to the first embodiment in that the top ends of the shroud-side blades and hub-side blades are abutted onto one another such that portions of their thicknesses overlap one another over the blade lengths; the other configurations are the same. Therefore, the same structures will be denoted by the same reference numerals, and descriptions thereof will be omitted.
  • Shroud-side blades 11 and hub-side blades 12 are thick blades having a wedge shape in cross-section perpendicular to the blade height direction.
  • the shroud-side blades 11 and the hub-side blades 12 which are wedge-shaped thick blades, have substantially triangular shapes in cross-section perpendicular to the blade height direction and gradually widen from their leading edges toward their trailing edges.
  • the wedge-shaped shroud-side blades 11 and hub-side blades 12 are combined in such a state that inlet angles thereof differ from one another and that top ends thereof in the blade height direction are abutted onto one another, with portions thereof in a thickness direction overlapping one another over the blade lengths.
  • these top ends have overlapping portions 13 (see FIG. 8(B) ) where portions thereof in the thickness direction overlap one another over the blade length.
  • the diffuser 1 of a centrifugal compressor and the centrifugal compressor provided with the same according to the sixth embodiment provide the following advantages.
  • the shroud-side blades 11 and the hub-side blades 12 are abutted onto one another such that their inlet angles differ from one another and such that portions, in the thickness direction, of their top ends in the blade height direction overlap one another over the blade lengths.
  • gaps are not formed between the top ends of the shroud-side blades 11 and hub-side blades 12 when the shroud-side blades 11 and the hub-side blades 12 are combined. Accordingly, it is possible to prevent flow separation and generation of vortices caused by the flow in the gaps and to improve the performance of the diffuser 1 .
  • shroud-side blades 11 and the hub-side blades 12 are abutted onto one another such that portions, in the thickness direction, of their top ends in the blade height direction overlap one another over the blade lengths, it is possible to increase the rigidity of the shroud-side blades 11 and hub-side blades 12 . Accordingly, it is possible to improve the vibration strength of the shroud-side blades 11 and hub-side blades 12 .
  • hub-side blades 14 may have a smaller length than the shroud-side blades 11 , as shown in FIG. 9 .
  • the hub-side blades 14 have a smaller length than the shroud-side blades 11 , and the shroud-side blades 11 and the hub-side blades 14 are combined such that portions in the thickness direction have the overlapping portions 13 along the blade lengths and such that the leading edges of the hub-side blades 14 are located at some midpoint in the length of the shroud-side blades 11 .
  • a diffuser according to a seventh embodiment differs from that according to the sixth embodiment in that the thicknesses of the trailing edges of the combined shroud-side blades and hub-side blades are small; the other configurations are the same. Therefore, the same structures will be denoted by the same reference numerals, and descriptions thereof will be omitted.
  • Shroud-side blades 15 and hub-side blades 16 are thick blades having substantially wedge shapes in cross-section perpendicular to the blade height direction.
  • the substantially wedge-shaped shroud-side blades 15 and hub-side blades 16 are shaped such that they gradually widen from the leading edges toward the trailing edges and such that they gradually decrease in thickness from certain points downstream of the middle portions in the blade length toward the trailing edges.
  • the shroud-side blades 15 and the hub-side blades 16 that decrease in thickness toward the trailing edges are combined in such a state that inlet angles thereof differ from one another and that top ends thereof in the blade height direction are abutted onto one another, with portions thereof in a thickness direction overlapping one another over the blade lengths.
  • these top ends have overlapping portions 17 (see FIG. 10(B) ) where portions thereof in the thickness direction overlap one another over the blade length.
  • the blade length of the hub-side blades 16 on the suction pressure surface side is substantially the same as the blade length of the shroud-side blades 15 on the pressure surface side, and the hub-side blades 16 and the shroud-side blades 15 form the overlapping portions 17 .
  • the diffuser 1 of a centrifugal compressor and the centrifugal compressor provided with the same according to the seventh embodiment provide the following advantages.
  • the thicknesses of the shroud-side blades 15 and hub-side blades 16 are smaller at the trailing edges than at the middle portions in the length direction. Thus, it is possible to reduce the wake of the shroud-side blades 15 and hub-side blades 16 . Accordingly, it is possible to improve the performance of the diffuser 1 .
  • hub-side blades 18 may have a smaller length than the shroud-side blades 15 , as shown in FIG. 11 .
  • a diffuser according to an eighth embodiment differs from that according to the sixth embodiment in that thick shroud-side blades and thin hub-side blades are combined; the other configurations are the same. Therefore, the same structures will be denoted by the same reference numerals, and descriptions thereof will be omitted.
  • the shroud-side blades 11 are thick blades having a wedge shape in cross-section perpendicular to the blade height direction.
  • the wedge-shaped shroud-side blades 11 have a substantially triangular shape and gradually widen from the leading edges toward the trailing edges.
  • the hub-side blades 4 are thin blades.
  • the width of the shroud-side blades 11 in cross-section perpendicular to the blade height direction is about two or more times greater than that of the thin hub-side blades 4 .
  • the thick shroud-side blades 11 and the thin hub-side blades 4 are combined such that their inlet angles differ from one another. Furthermore, they are combined in such a state that the top ends, in the blade height direction, of the thick shroud-side blades 11 and the top ends, in the blade height direction, of the thin hub-side blades 4 are abutted onto one another. Thus, as shown in FIG. 12(B) , in top view, the entire top ends of the thin hub-side blades 4 overlap portions of the top ends of the thick shroud-side blades 11 .
  • the diffuser 1 of a centrifugal compressor and the centrifugal compressor provided with the same according to the eighth embodiment provide the following advantages.
  • the thick shroud-side blades 11 and the thin hub-side blades 4 are abutted onto one another such that their inlet angles differ from one another and such that the entire top ends, in the blade height direction, of the hub-side blades 4 overlap portions, in the thickness direction, of the shroud-side blades 11 over the blade lengths.
  • gaps are not formed between the shroud-side blades 11 and the hub-side blades 4 . Accordingly, it is possible to prevent flow separation and generation of vortices caused by the flow in the gaps and to improve the performance of the diffuser 1 .
  • the present invention is not limited thereto.
  • the hub-side blades 6 may have a smaller length than the shroud-side blades 11 .
  • the cross-section of the thick shroud-side blades 11 perpendicular to the blade height direction is wedge-shaped in the eighth embodiment, the cross-section thereof may be channel-shaped.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/806,384 2010-08-31 2011-08-17 Centrifugal compressor diffuser and centrifugal compressor provided with the same Abandoned US20130094955A1 (en)

Applications Claiming Priority (3)

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JP2010193623A JP5010722B2 (ja) 2010-08-31 2010-08-31 遠心圧縮機のディフューザおよびこれを備えた遠心圧縮機
JP2010-193623 2010-08-31
PCT/JP2011/068611 WO2012029543A1 (ja) 2010-08-31 2011-08-17 遠心圧縮機のディフューザおよびこれを備えた遠心圧縮機

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EP3396173A1 (en) * 2017-04-25 2018-10-31 Honeywell International Inc. Turbocharger compressor assembly with vaned divider
US20190271328A1 (en) * 2018-03-02 2019-09-05 Ingersoll-Rand Company Centrifugal compressor system and diffuser
EP3505770A4 (en) * 2016-12-07 2019-09-11 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. CENTRIFUGAL COMPRESSORS AND TURBOCHARGER
US10774842B2 (en) 2015-04-30 2020-09-15 Concepts Nrec, Llc Biased passages for turbomachinery
US11035380B2 (en) 2018-03-09 2021-06-15 Mitsubishi Heavy Industries, Ltd. Diffuser vane and centrifugal compressor
US11313384B2 (en) 2017-09-20 2022-04-26 Siemens Energy Global GmbH & Co. KG Flow-through arrangement

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JP6388772B2 (ja) * 2014-02-25 2018-09-12 三菱重工業株式会社 遠心圧縮機およびディフューザ製造方法
US11067098B2 (en) 2018-02-02 2021-07-20 Carrier Corporation Silencer for a centrifugal compressor assembly
CN110878768A (zh) * 2019-12-20 2020-03-13 中国北方发动机研究所(天津) 一种具有变进口叶片角型导流叶片的有叶扩压器结构
JP7643214B2 (ja) * 2021-07-02 2025-03-11 株式会社Ihi 遠心式回転装置

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US11313384B2 (en) 2017-09-20 2022-04-26 Siemens Energy Global GmbH & Co. KG Flow-through arrangement
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CN103097741A (zh) 2013-05-08
KR20130045280A (ko) 2013-05-03
KR101454100B1 (ko) 2014-10-22
KR101437319B1 (ko) 2014-09-02
CN103097741B (zh) 2015-11-25
JP5010722B2 (ja) 2012-08-29
EP2613056A4 (en) 2014-04-09
JP2012052432A (ja) 2012-03-15
KR20140049052A (ko) 2014-04-24
EP2613056A1 (en) 2013-07-10
EP2613056B1 (en) 2016-01-20

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