US20070134086A1 - Impeller for compressor - Google Patents

Impeller for compressor Download PDF

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Publication number
US20070134086A1
US20070134086A1 US10/577,715 US57771504A US2007134086A1 US 20070134086 A1 US20070134086 A1 US 20070134086A1 US 57771504 A US57771504 A US 57771504A US 2007134086 A1 US2007134086 A1 US 2007134086A1
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United States
Prior art keywords
boundary layer
compressor impeller
hub
impeller
flow
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Abandoned
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US10/577,715
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English (en)
Inventor
Hirotaka Higashimori
Hiroshi Kuma
Kunio Sumida
Toru Suita
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Filing date
Publication date
Priority claimed from JP2003403957A external-priority patent/JP2005163640A/ja
Priority claimed from JP2003424283A external-priority patent/JP2005180372A/ja
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD. reassignment MITSUBISHI HEAVY INDUSTRIES, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KUMA, HIROSHI, SUITA, TORU, SUMIDA, KUNIO, HIGASHIMORI, HIROTAKA
Publication of US20070134086A1 publication Critical patent/US20070134086A1/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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D23/00—Other rotary non-positive-displacement pumps
    • 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
    • F04D29/002—Details, component parts, or accessories especially adapted for elastic fluid pumps
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/10—Kind or type
    • F05D2210/12—Kind or type gaseous, i.e. compressible
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S417/00—Pumps

Definitions

  • the present invention relates to an impeller for a centrifugal compressor or a mixed-flow compressor, for example, an impeller for a centrifugal compressor or a mixed-flow compressor employed in an aeronautical gas turbine, a marine supercharger, a motor vehicle supercharger, and the like.
  • Patent Document 1 Japanese Unexamined Patent Application, First Publication No. Sho 55-35173
  • the inventors of the present application have therefore focused on research on the surface of the hub of the rotating impeller, and as a result, have become aware of the occurrence of the following phenomenon on the hub surface.
  • centrifugal force F 1 acts upon this flow.
  • This centrifugal force F 1 can be resolved into components in a direction perpendicular to the hub surface 12 c and in a direction orthogonal to this perpendicular direction.
  • a force F 2 acting in the direction perpendicular to the hub surface 12 c acts in a direction separating the flow from the hub surface 12 c, and thus, it is known that the boundary layer is enlarged (or in extreme cases the flow is reversed in the proximity of the hub, or the flow is separated from the hub surface 12 c ), thereby increasing losses in the interior of the impeller, and inviting a reduction in the efficiency of the centrifugal compressor 100 .
  • reference symbols 12 , 12 a, 12 b, LE, TE, and B in the figure illustrate respectively the hub, the minor diameter of the hub, the major diameter of the hub, the leading edge of the blade 11 , the trailing edge of the blade 11 , and the region of marked enlargement of the boundary layer (that is to say, the region in which the thickness of the boundary layer is markedly increased).
  • the same phenomenon also occurs in the mixed-flow compressor impeller 200 shown in FIG. 14B .
  • the force F 2 tending to separate the flow from the hub surface 12 c acts up to the impeller outlet 102 where the hub surface 12 c is inclined, it is known that distortion of flow velocity remains due to enlargement of the boundary layer up to the impeller outlet 102 , and losses at the impeller outlet 102 increase, inviting a reduction in efficiency of the mixed-flow compressor 200 .
  • the compressor impeller according to the present invention has a plurality of blades, and a hub disposed at the root of this plurality of blades, and at least part of the surface of the hub on which a fluid flows is inclined in relation to an axis of rotation, and a boundary layer reduction part which induces a reduction in the thickness of a boundary layer occurring due to a flow of fluid, is provided on the surface of the hub.
  • the boundary layer reduction part is provided at a position at which the centrifugal force acting on the flow of fluid acts in a direction to separate the flow of fluid from the surface of the hub.
  • the boundary layer reduction part is preferably provided on the surface of the hub inclined at an angle in relation to the axis of rotation of the impeller, that is to say, on the surface of the inclined hub separated a certain distance from the axis of rotation of the impeller.
  • the boundary layer reduction part is provided on the downstream side from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, from the edge of the impeller inlet.
  • the start point of the boundary layer reduction part is positioned at a position separated by a prescribed distance from the edge of the impeller inlet. That is to say, the boundary layer reduction part is not provided close to the edge of the inlet on the downstream side.
  • the boundary layer reduction part is formed as a convex part projecting perpendicularly to the surface of the hub.
  • a flow (hereafter referred to as “secondary flow”) towards the flow path formed on the surface of the convex part, from the surface of the hub to the blades occurs due to the force (F 2 ) acting perpendicularly to the surface of the hub.
  • the boundary layer formed on the surface of the hub or on the surface of the convex part migrates in the direction of the flow path formed between the blades due to this secondary flow, and is dragged into the primary flow in the flow path, and is carried away downstream together with this primary flow.
  • the convex part is provided as at least one small blade formed along the surface of the blade, between the blades.
  • secondary flow occurs on the surface of the small blade which is formed so that primary flow is not hindered and losses are minimized, and which has a surface area greater than the convex part, and a greater portion of the boundary layer formed on the surface of the hub or on the surface of the small blade is carried away downstream by the primary flow in the flow path.
  • a height of the small blade is set at between approximately 1/10 and approximately 1 ⁇ 2 of the height of the blade.
  • a maximum distance between the small blades is set so as to be greater than twice the thickness of the boundary layer occurring due to the flow of fluid, on the surface of the hub.
  • the spacing of the small blades is formed so as to be greater than twice the thickness of the boundary layer occurring on the surface of the hub due to the flow of fluid, and the primary flow passes between small blade and small blade. Therefore merging of the secondary flow occurring on the surface of the small blade, and the primary flow, is promoted and the thickness of the boundary layer is further reduced.
  • the compressor impeller according to the present invention is preferably a centrifugal compressor impeller, and the boundary layer reduction part is provided up to a position at which a force acting perpendicularly to the hub surface becomes zero.
  • the boundary layer reduction part is provided at a location at which the centrifugal force acting on the flow of fluid acts in a direction to separate the flow of fluid from the surface of the hub, that is to say, the boundary layer reduction part is provided from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, from the edge of the impeller inlet, up to a position at which the force acting perpendicularly to the hub surface is zero.
  • the thickness of the boundary layer formed close to the hub surface is reduced across the entire hub surface.
  • the boundary layer reduction part is also extended downstream beyond a position at which the force acting perpendicularly to the hub surface is zero.
  • the boundary layer reduction part is also extended downstream beyond the position at which the force acting perpendicularly to the surface of the hub is zero, the boundary layer is discharged outwards in the radial direction of the impeller along the extended boundary layer reduction part, and the thickness of the boundary layer is further reduced.
  • the boundary layer reduction part is provided up to the edge of the impeller outlet.
  • the boundary layer reduction part is provided extended up to the edge of the impeller outlet, the boundary layer is discharged outwards in the radial direction of the impeller along the extended boundary layer reduction part, and the thickness of the boundary layer is further reduced.
  • the compressor impeller according to the present invention is preferably a mixed-flow compressor impeller, and the boundary layer expansion prevention part is provided up to the edge of the outlet of the impeller.
  • the boundary layer reduction part is provided at a location at which the centrifugal force acting on the flow of fluid acts in a direction to separate the flow of fluid from the surface of the hub, that is to say, the boundary layer reduction part is provided from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, from the edge of the impeller inlet, up to the edge of the impeller outlet.
  • the boundary layer reduction part is provided from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, from the edge of the impeller inlet, up to the edge of the impeller outlet.
  • the compressor impeller according to the present invention has a plurality of blades, and a hub disposed at the root of this plurality of blades, and at least part of the surface of the hub on which a fluid flows is inclined in relation to an axis of rotation, and a boundary layer expansion prevention part which prevents expansion of a boundary layer occurring due to a flow of fluid, may be provided on the surface of the hub.
  • compressors furnished with impellers having at least part of the surface of the hub on which the fluid flows inclined in relation to the axis of rotation are centrifugal compressors and mixed-flow compressors.
  • the boundary layer expansion prevention part is provided at a position at which the centrifugal force acting on the flow of fluid acts in a direction to separate the flow of fluid from the surface of the hub.
  • the boundary layer expansion prevention part is provided on the surface of the hub having an inclination angle in relation to the axis of rotation of the impeller, that is to say, on the inclined surface of the hub separated a certain distance from the axis of rotation of the impeller.
  • the boundary layer expansion prevention part is provided on the downstream side from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, from the edge of the impeller inlet.
  • the start point of the boundary layer expansion prevention part is positioned at a position separated by a prescribed distance from the edge of the impeller inlet. That is to say, the boundary layer expansion prevention part is not provided close to the edge of the inlet on the downstream side.
  • the boundary layer reduction part comprises a plurality of grooves.
  • the flow along the hub surface close to the hub surface passes over the peak of a groove and flows into the trough of the adjacent groove, or passes over the peak of a groove and proceeds diagonally towards the top of the adjacent groove, so that the flow close to the hub surface becomes turbulent.
  • the plurality of grooves are formed linearly along the surface of the blades, between the blades.
  • the flow along the hub surface close to the hub surface passes over the peak of a groove and flows into the trough of the adjacent groove, or passes over the peak of a groove and proceeds diagonally towards the top of the adjacent groove, so that turbulence occurs in the flow along the hub surface close to the hub surface, and expansion of the boundary layer or separation of the flow is prevented.
  • the linear grooves are divided into a plurality of regions between upstream and downstream.
  • the flow along the hub surface close to the hub surface passes over the peak of a groove and flows into the trough of the adjacent groove, or passes over the peak of a groove and proceeds diagonally towards the top of the adjacent groove, so that turbulence occurs in the flow along the hub surface close to the hub surface, and expansion of the boundary layer or separation of flow is prevented.
  • preferably-the plurality of grooves are formed in a wave-shape in plan view, between the blades.
  • the angle between the peak of a groove and the direction with which the flow passes over the peak of a groove and flows into the trough of the adjacent groove, or passes over the peak of a groove and proceeds diagonally towards the top of the adjacent groove can be increased in some parts. Therefore strong turbulence occurs at these parts due to the flow along the hub surface close to the hub surface, and expansion of the boundary layer or separation of flow is further prevented.
  • the plurality of grooves are formed in a sawtooth-shape in plan view, between the blades.
  • the angle between the peak of a groove and the direction with which the flow passes over the peak of a groove and flows into the trough of the adjacent groove, or passes over the peak of a groove and proceeds diagonally towards the top of the adjacent groove can be increased in some parts, and these parts can be formed in greater number. Therefore strong turbulence occurs due to the flow along the hub surface close to the hub surface, and expansion of the boundary layer or separation of flow is further prevented.
  • the plurality of grooves comprise a plurality of grooves formed between blades from one blade to another blade, so as to intersect diagonally with the flow path, and a plurality of grooves formed so as to intersect with these grooves, and formed from the other blade to the one blade, so as to intersect diagonally with the flow path.
  • a plurality of projections are formed, and the flow along the hub surface close to the hub surface collides with these projections, or passes over these projections and flows into the trough of the adjacent groove, or passes over these projections and proceeds diagonally towards the top of the adjacent groove, so that strong turbulence occurs in the flow along the hub surface close to the hub surface, and expansion of the boundary layer or separation of flow is prevented.
  • the plurality of grooves are formed concentrically with the axis of rotation of the impeller, between the blades.
  • the boundary layer reduction part comprises a plurality of concave and convex parts.
  • the flow along the hub surface close to the hub surface collides with these convex parts, or passes over these convex parts and flows into the adjacent concave part, or passes over these convex parts and proceeds diagonally towards the top of the adjacent convex or concave part, so that strong turbulence occurs due to the flow along the hub surface close to the hub surface, and expansion of the boundary layer or separation of flow is prevented.
  • the plurality of concave and convex parts are circular-shaped in plan view.
  • the concave and convex parts are formed in the hub surface in readily manufactured hemispherical shapes.
  • a maximum depth of the grooves or the concave and convex parts is preferably between 0.3% and 2.0% of the outside diameter of the impeller, and more preferably between 0.5% and 2.0%.
  • the grooves are formed to a maximum depth of between 0.3 mm and 2.0 mm, and more preferably to between 0.5 mm and 2.0 mm, and are formed deeper and wider than grooves being machining tracks remaining on the hub surface of the impeller manufactured by milling (generally having a width and maximum depth of approximately 0.2% of the outside diameter of the impeller).
  • the compressor impeller according to the present invention is a centrifugal compressor impeller, and the boundary layer expansion prevention part is provided up to a position at which a force acting perpendicularly to the hub surface is zero.
  • the boundary layer expansion prevention part is provided at a location at which the centrifugal force acting on the flow of fluid acts in a direction separating the flow of fluid from the surface of the hub, that is to say, the boundary layer expansion prevention part is provided from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, from the edge of the impeller inlet, up to a position at which the force acting perpendicularly to the hub surface is zero. Therefore turbulence occurs in the flow along the hub surface close to the hub surface, and expansion of the boundary layer or separation of flow is prevented over the entire hub surface.
  • the compressor impeller according to the present invention is a mixed-flow compressor impeller, and the boundary layer expansion prevention part is provided up to the edge of the outlet of the impeller.
  • the boundary layer expansion prevention part is provided at a location at which the centrifugal force acting on the flow of fluid acts in a direction separating the flow of fluid from the hub surface, that is to say, the boundary layer expansion prevention part is provided from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, from the edge of the impeller inlet, to the edge of the outlet. Therefore turbulence occurs in the flow along the hub surface close to the hub surface, and expansion of the boundary layer or separation of flow is prevented over the entire hub surface.
  • the compressor according to the present invention is furnished with one of the aforementioned impellers.
  • this is furnished with an impeller provided with a boundary layer reduction part which prevents localized concentration of the boundary layer generated on the surface of the hub, and reduces boundary layer thickness, or an impeller having a boundary layer expansion prevention part which prevents expansion of the boundary layer formed on the surface of the hub.
  • boundary layer reduction part By means of the boundary layer reduction part, localized concentration of the boundary layer generated on the surface of the hub can be prevented and boundary layer thickness can be reduced.
  • an impeller provided with a boundary layer reduction part, localized concentration of the boundary layer can be prevented, and also boundary layer thickness can be reduced, losses within the impeller can be reduced, and compression efficiency of the compressor can be improved.
  • boundary layer expansion prevention part By means of the boundary layer expansion prevention part, turbulence in the flow along the hub surface close to the hub surface can be generated, and expansion of the boundary layer or separation of flow can be prevented.
  • FIG. 1A through C are diagrams showing a first embodiment of an impeller according to the present invention, wherein FIG. 1A is a perspective view of the main parts, FIG. 1B is a cross-sectional view on I-I in FIG. 1A , and FIG. 1C is a cross-sectional view on II-II in FIG. 1A .
  • FIGS. 2A and B are diagrams showing a second embodiment according to the present invention, wherein FIG. 2A is a perspective view of the main parts, and FIG. 2B is a cross-sectional view on III-III in FIG. 2A .
  • FIG. 3 is a perspective view of the main parts showing a third embodiment of the impeller according to the present invention.
  • FIG. 4 is a perspective view of the main parts showing a fourth embodiment of the impeller according to the present invention.
  • FIG. 5 is a perspective view of the main parts showing a fifth embodiment of the impeller according to the present invention.
  • FIGS. 6A and B are diagrams showing the fifth embodiment of the impeller according to the present invention, wherein FIG. 6A is a cross-sectional view on a-a in FIG. 5 , and FIG. 6B is a cross-sectional view on b-b in FIG. 5 .
  • FIG. 7 is a perspective view of the main parts showing a sixth embodiment of the impeller according to the present invention.
  • FIGS. 8A and B are diagrams showing a seventh embodiment of the impeller according to the present invention, wherein FIG. 8A is a perspective view of the main parts, and FIG. 8B is a plan view of a boundary layer expansion prevention part.
  • FIGS. 9A and B are diagrams showing an eighth embodiment of the impeller according to the present invention, wherein FIG. 9A is a perspective view of the main parts, and FIG. 9B is a plan view of a boundary layer expansion prevention part.
  • FIGS. 10A and B are diagrams showing a ninth embodiment of the impeller according to the present invention, wherein FIG. 10A is a perspective view of the main parts, and FIG. 10B is a cross-sectional view on c-c in FIG. 10A .
  • FIG. 11 is a perspective view of the main parts showing a tenth embodiment of the impeller according to the present invention.
  • FIGS. 12A and B are diagrams showing an eleventh embodiment of the impeller according to the present invention, wherein FIG. 12A is a perspective view of the main parts, and FIG. 11B is a cross-sectional view on d-d in FIG. 12A .
  • FIGS. 13A and B are similar to FIG. 6B , and show another cross-sectional shape for the grooves being the boundary layer expansion prevention part.
  • FIGS. 14A and B are diagrams for explaining problems of a conventional impeller, wherein FIG. 14A is a cross-sectional view of a centrifugal compressor impeller, and FIG. 14B is a cross-sectional view of a mixed-flow compressor impeller.
  • a first embodiment of an impeller for a compressor according to the present invention is described below with reference to FIG. 1A through FIG. 1C .
  • the impeller of the present embodiment is a specific example of application to a centrifugal compressor.
  • FIG. 1A is a perspective view of the main parts of an impeller 10 according to the present embodiment, with the edge on the inlet side of the impeller 10 omitted.
  • FIG. 1B is a cross-sectional view on I-I in FIG. 1A
  • FIG. 1C is a cross-sectional view on II-II in FIG. 1A .
  • the impeller 10 As shown in FIG. 1A through FIG. 1C , the impeller 10 according to the present embodiment comprises a plurality of blades 11 , and a hub 12 disposed at a root R of this plurality of blades 11 , as the primary elements.
  • Each blade 11 is provided so that the leading edge LE is positioned at the minor diameter end 12 a of the hub 12 , and the trailing edge TE is positioned at the major diameter end 12 b of the hub 12 (see FIG. 14A ).
  • three small blades are provided in a region on the hub surface 12 c in which the centrifugal force F 1 (see FIG. 14A ) acts perpendicularly to the hub surface 12 c, for example, a region from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side (the upstream-most position of the small blade 13 a positioned at the center in FIG. 1A (the start point)), to a position at which the force F 2 acting perpendicularly to the hub surface 12 c is zero (the downstream-most position of the small blades 13 a and 13 b in FIG.
  • the small blade 13 a positioned at the center (that is to say, the small blade positioned in the middle), is provided in the region from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side, to a position at which the force F 2 acting perpendicularly to the hub surface 12 c is zero, and approximately midway between the blades 11 .
  • the small blades 13 b positioned at both sides of the small blade 13 a are provided in the region from a position approximately 1 ⁇ 2 of the distance from the edge of the impeller inlet to the edge of the outlet on the inlet side, to a position at which the force F 2 acting perpendicularly to the hub surface 12 c is zero, and approximately midway between the blade 11 and the small blade 13 a.
  • the cross-sectional shape of these small blades 13 a and 13 b becomes gradually thinner as the distance from the hub surface 12 c increases. Moreover, the leading edges and trailing edges of these small blades 13 a and 13 b also become gradually thinner towards the upstream and downstream ends.
  • a height h of these small blades 13 a and 13 b (that is to say, the minimum distance from the hub surface 12 c to the tip of the small blades 13 a and 13 b ) is between approximately 1/10 and approximately 1 ⁇ 2 of a height of the blade 11 at the same radial position.
  • a space W between the small blades 13 a and 13 b (that is to say, the minimum distance between the tip of the small blade 13 a and the tip of the small blade 13 b ) is greater than twice a thickness ⁇ of a boundary layer BL occurring on the hub surface 12 c due to the flow of fluid.
  • the boundary layer BL on the hub surface 12 c and the small blades 13 a and 13 b is dragged into (onto) the secondary flow and is guided into the flow path formed between the blades 11 , that is to say, is guided in the direction of the primary flow of fluid passing between the blades 11 , and finally merges with the primary flow of fluid and flows downstream. Therefore localized concentration of the boundary layer BL can be prevented, and the thickness ⁇ of the boundary layer BL can be reduced.
  • the height h of the small blades 13 a and 13 b is between approximately 1/10 and approximately 1 ⁇ 2 of the height of the blade 11 at the same radial position. Therefore the secondary flow occurring on the surface of the small blades 13 a and 13 b can be guided reliably and effectively into the primary flow passing between the blades 11 , and the thickness ⁇ of the boundary layer BL can be further reduced.
  • the space W between the small blades 13 a and 13 b is greater than twice the thickness ⁇ of the boundary layer BL occurring on the hub surface 12 c due to the flow of fluid, and is such that the primary flow of fluid passes between the small blades 13 a and 13 b. Therefore merging of the secondary flow occurring on the surface of the small blades 13 a and 13 b, and the primary flow of fluid is accelerated, and the thickness ⁇ of the boundary layer BL can be even further reduced.
  • leading edges and trailing edges of the small blades 13 a and 13 b become gradually thinner towards the upstream and downstream ends. Therefore vortex losses occurring when the primary flow of fluid collides with the leading edges of the small blades 13 a and 13 b, or when the primary flow of fluid separates from the trailing edges of these small blades 13 a and 13 b, can be minimized.
  • the tips of the small blades 13 a and 13 b become gradually thinner as the distance from the hub surface 12 c increases. Therefore vortex losses occurring when the secondary flow occurring on the surface of the small blades 13 a and 13 b separates from the leading edges of the small blades 13 a and 13 b can be minimized.
  • FIG. 2A is a similar diagram to FIG. 1A , with the edge on the inlet side of the impeller 20 omitted.
  • FIG. 2B is a cross-sectional view on III-III in FIG. 2A .
  • all the start points of the small blades 23 being the boundary layer reduction part (convex parts), are provided at the same position as the start point of the small blade 13 a of the first embodiment, and all end points of the small blades 23 are further downstream than the end points of the small blades 13 a and 13 b of the first embodiment. That is to say, the present embodiment differs from the first embodiment in that the end points are provided extended towards the edge of the outlet. Since other elements of the configuration are the same as for the first embodiment, a description of these elements of the configuration is omitted here, and only the small blades 23 are described.
  • three small blades 23 are provided in a region on the hub surface 12 c from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side (the upstream-most position of the small blades 23 in FIG. 2A (the start point)), to a position approximately 1 ⁇ 5 of the distance from the edge of the impeller inlet to the edge of the outlet, on the outlet side (the downstream-most position of the small blades 23 in FIG. 2A (the end point)), and along the surface of the blade 11 (or the root R of the blade 11 ) in a region positioned between the blades 11 .
  • the cross-sectional shape of these small blades 23 becomes gradually thinner as the distance from the hub surface 12 c increases.
  • leading edges and trailing edges of these small blades 23 also become gradually thinner towards the upstream and downstream ends (see FIG. 1B and FIG. 1C ).
  • the height h of these small blades 23 (that is to say, the minimum distance from the hub surface 12 c to the tip of the small blades 23 ) is between approximately 1/10 and approximately 1 ⁇ 2 of the height of the blade 11 at the same radial position.
  • the space W between the small blades 23 and 23 (that is to say, the minimum distance between the tip of one small blade 23 and the tip of the adjacent small blade 23 ) is greater than twice the thickness ⁇ of the boundary layer BL occurring on the hub surface 12 c due to the flow of fluid.
  • all start points of the small blades 23 are at a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side, that is to say, at the same position as the start point of the small blade 13 a of the first embodiment. Therefore the surface area of the small blades 23 is increased beyond that of the first embodiment, and secondary flow is increased accordingly, concentration of the boundary layer BL can be further prevented, and the thickness ⁇ of the boundary layer BL can be further reduced.
  • all end points of the small blades 23 are at a position approximately 1 ⁇ 5 of the distance from the edge of the impeller inlet to the edge of the outlet, on the outlet side, that is to say, are provided extended downstream (towards the outlet) beyond the end points of the small blades 13 a of the first embodiment. Therefore the boundary layer BL is discharged outwards in the radial direction of the impeller 20 along the surface of these extended small blades 23 , and the thickness ⁇ of the boundary layer can be even further reduced.
  • FIG. 3 is a similar diagram to FIG. 1A and FIG. 2A , with the edge on the inlet side of the impeller 30 omitted.
  • the impeller 30 of the present embodiment differs from the second embodiment in that all end points of the small blades 33 being the boundary layer reduction part (convex parts), are provided extended to the edge of the outlet of the impeller 30 . Since other elements of the configuration are the same as for the second embodiment, a description of these elements of the configuration is omitted here, and only the small blades 33 are described.
  • three small blades 33 are provided in a region on the hub surface 12 c from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side (the upstream-most position of the small blades 33 in FIG. 3 (the start point)) to the outlet edge, and along the surface of the blade 11 (or the root R of the blade 11 ) in a region positioned between the blades 11 .
  • the cross-sectional shape of these small blades 33 becomes gradually thinner as the distance from the hub surface 12 c increases.
  • leading edges and trailing edges of the small blades 33 also become gradually thinner towards the upstream and downstream ends (see FIG. 1B and FIG. 1C )
  • the height h of these small blades 33 (that is to say, the minimum distance between the hub surface 12 c and the tip of the small blades 33 ) is between approximately 1/10 and approximately 1 ⁇ 2 of the height H of the blade 11 at the same radial position.
  • the space W between the small blades 33 and 33 (that is to say, the minimum distance between the tip of one small blade 33 and the tip of the adjacent small blade 33 ) is greater than twice the thickness ⁇ of the boundary layer BL occurring on the hub surface 12 c due to the flow of fluid.
  • the boundary layer is discharged outwards in the radial direction of the impeller 30 along the surface of these extended small blades 33 , and the thickness ⁇ of the boundary layer can be even further reduced.
  • FIG. 4 is a similar diagram to FIG. 1A , FIG. 2A , and FIG. 3 , with the edge on the inlet side of the impeller 40 omitted.
  • the impeller 40 of the present embodiment is applied to a mixed-flow compressor, and small blades similar to the small blades 13 a and 13 b serving as the boundary layer reduction part (convex parts) shown in FIG. 1A through FIG. 1C , are formed on the hub surface 12 c.
  • the impeller 40 As shown in FIG. 4 , the impeller 40 according to the present embodiment comprises a plurality of blades 11 , and a hub 12 disposed at the root R of this plurality of blades 11 , as the primary elements.
  • Each blade 11 is provided so that the leading edge LE is positioned at the minor diameter end 12 a of the hub 12 , and the trailing edge TE is positioned at the major diameter end 12 b of the hub 12 (see FIG. 14B ).
  • three small blades are provided in a region on the hub surface 12 c in which the centrifugal force F 1 (see FIG. 14B ) acts perpendicularly to the hub surface 12 c, for example, a region from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side (the upstream-most position of the small blades in FIG. 4 ) (the start point)), to the edge of the impeller outlet (the downstream-most position of the small blades in FIG. 4 (the end point)), and in which the small blades 43 a and 43 b are along the surface of the blade 11 (or the root R of the blades 11 ) in a region positioned between the blades 11 .
  • the small blade 43 a positioned in the center (that is to say, the small blade positioned in the middle), is provided in a region from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side, to the edge of the impeller outlet, and approximately midway between the blades 11 .
  • the small blades 43 b positioned at both sides of the small blade 43 a are provided in a region from a position approximately 1 ⁇ 2 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side, to the edge of the impeller outlet, and approximately midway between the blade 11 and the small blade 13 a.
  • the cross-sectional shape of these small blades 43 a and 43 b becomes gradually thinner as the distance from the hub surface 12 c increases.
  • leading edges and trailing edges of the small blades 43 a and 43 b also become gradually thinner towards the upstream and downstream ends (see FIG. 1B and FIG. 1C .
  • the height h of these small blades 43 a and 43 b (that is to say, the minimum distance from the hub surface 12 c to the tip of the small blades 43 a and 43 b ) is between approximately 1/10 and approximately 1 ⁇ 2 of the height of the blade 11 at the same radial position.
  • the space w between the small blades 43 a and 43 b (that is to say, the minimum distance between the tip of the small blade 43 a and the tip of the small blade 43 b ) is greater than twice the thickness ⁇ of the boundary layer BL occurring on the hub surface 12 c due to the flow of fluid.
  • the boundary layer on the hub surface 12 c and the small blades 43 a and 43 b is dragged into (onto) the secondary flow and is guided into the flow path formed between the blades 11 , that is to say, is guided in the direction of the primary flow of fluid passing between the blades 11 , and finally merges with the primary flow of fluid and flows downstream. Therefore localized concentration of the boundary layer BL can be prevented, and the thickness ⁇ of the boundary layer BL can be reduced.
  • the height h of the small blades 43 a and 43 b is between approximately 1/10 and approximately 1 ⁇ 2 of the height of the blade 11 at the same radial position. Therefore the secondary flow occurring on the surface of the small blades 43 a and 43 b can be guided reliably and effectively into the primary flow passing between the blades 11 , and the thickness ⁇ of the boundary layer BL can be further reduced.
  • the space W between the small blades 43 a and 43 b is greater than twice the thickness ⁇ of the boundary layer BL occurring on the hub surface 12 c due to the flow of fluid, and is such that the primary flow of fluid passes between the small blades 43 a and 43 b. Therefore merging of the secondary flow occurring on the surface of the small blades 43 a and 43 b, and the primary flow of fluid is accelerated, and the thickness ⁇ of the boundary layer BL can be even further reduced.
  • leading edges and trailing edges of the small blades 43 a and 43 b become gradually thinner towards the upstream and downstream ends. Therefore vortex losses occurring when the primary flow of fluid collides with the leading edges of the small blades 43 a and 43 b, or when the primary flow of fluid separates from the trailing edges of the small blades 43 a and 43 b, can be minimized.
  • the tips of the small blades 43 a and 43 b become gradually thinner as the distance from the hub surface 12 c increases. Therefore vortex losses occurring when the secondary flow occurring on the surface of the small blades 43 a and 43 b separates from the tips of the small blades 43 a and 43 b can be minimized.
  • the present invention is not limited to the aforementioned embodiments, and for example, the start points of the-small blades 43 b shown in FIG. 4 can also be positioned at a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side as in FIG. 2A and FIG. 3 .
  • the number of small blades is not limited to three, and any number is possible provided the primary flow between the small blades has a velocity.
  • a fifth embodiment of the impeller for a compressor according to the present invention is described with reference to FIG. 5 , and FIG. 6A and FIG. 6B .
  • the impeller of the embodiment described below is applied to a centrifugal compressor.
  • FIG. 5 is a perspective view of the main parts of an impeller 310 according to the present embodiment, and omits approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side. Furthermore, FIG. 6A is a cross-sectional view on a-a in FIG. 5 , and FIG. 6B is a cross-sectional view on b-b in FIG. 5 .
  • the impeller 310 comprises a plurality of blades 11 , and a hub 12 disposed at the root R of this plurality of blades 11 , as the primary elements.
  • Each blade 11 is provided so that the leading edge LE is positioned at the minor diameter end 12 a of the hub 12 , and the trailing edge TE is positioned at the major diameter end 12 b of the hub 12 (see FIG. 14A ).
  • a plurality of linear grooves (boundary layer expansion prevention part) 313 (five grooves in FIG. 5 ) along the surface of the blade 11 (or the root R of the blades 11 ) are provided in a region on the hub surface (surface of the hub) 12 c in which the centrifugal force F 1 (see FIG. 14A ) acts perpendicularly to the hub surface 12 c, for example, a region from a position approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side (the position shown by hatching in FIG. 5 ), to the position at which the force F 2 acting perpendicularly to the hub surface 12 c is zero, and in a region positioned between the blades 11 .
  • Reference symbol 314 in FIG. 5 denotes machining tracks for the case where the impeller 310 is manufactured by machining with a ball-end mill, and shows twelve small grooves provided in a region of the hub surface 12 c in which the force F 2 acting perpendicularly to the hub surface 12 c is zero.
  • the maximum depth and width of these grooves is generally 0.2% of the outside diameter of the impeller. Therefore for an impeller with an outside diameter of 100 mm, the maximum depth and width are approximately 0.2 mm.
  • the grooves 313 provided as the boundary layer expansion prevention part are formed deeper than the machining tracks formed during manufacture of the impeller. That is to say, are formed so that H 1 >h 1 .
  • H 1 is the maximum depth of the grooves 313
  • h 1 is the depth of the machining tracks formed during milling of the hub surface 12 c.
  • the maximum depth H 1 of the grooves 313 is preferably set to approximately the thickness of the removed boundary layer on the hub surface. More specifically, H 1 is preferably between 0.3% and 2.0%, of the outside diameter of the impeller, and most preferably between 0.5% and 2.0%. That is to say, for an impeller of an outside diameter of 100 mm, the maximum depth H 1 of the grooves 313 is preferably between 0.3 mm and 2.0 mm, and most preferably between 0.5 mm and 2.0 mm.
  • the grooves 313 are formed linearly, the grooves 313 can be readily machined, and manufacturing costs can be kept down.
  • FIG. 7 is a similar diagram to FIG. 5 , being a perspective view of the main parts, omitting approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side.
  • An impeller 320 of the present embodiment differs from the fifth embodiment in that the plan view shape of grooves 323 serving as the boundary layer expansion prevention part, is formed in a wave-shape. Since other elements of the configuration are the same as for the fifth embodiment, a description of these elements of the configuration is omitted here, and only the plan view shape of the grooves 323 is described.
  • the grooves 323 serving as the boundary layer expansion prevention part are wave-shaped in plan view. That is to say, the peaks and troughs are formed in smooth curves in plan view, and these peaks and troughs are formed contiguously.
  • the depth of the grooves 323 is the same as for the grooves 313 in the fifth embodiment, and a description is therefore omitted here.
  • the angle between the peak of the grooves 323 and the direction in which the flow passes over the peak of a groove 323 and flows into the trough of the adjacent groove 323 , or passes over the peak of a groove 323 and proceeds diagonally towards the top of the adjacent groove 323 can be greater than in the fifth embodiment in some parts. Therefore, strong turbulence occurs at these parts due to the flow of fluid along the hub surface 12 c close to the hub surface 12 c, and expansion of the boundary layer or separation of flow can be prevented.
  • FIG. 8A is a similar diagram to FIG. 5 and FIG. 7 , being a perspective view of the main parts omitting approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side.
  • An impeller 330 of the present embodiment differs from the aforementioned embodiments in that the plan view shape of grooves 333 serving as the boundary layer expansion prevention part is formed in a sawtooth-shape. Since other elements of the configuration are the same as for the aforementioned embodiments, a description of these elements of the configuration is omitted here, and only the plan view shape of the grooves 333 is described.
  • the grooves 333 serving as the boundary layer expansion prevention part of the present embodiment are sawtooth-shaped in plan view. That is to say, the peaks and troughs in plan view are formed by two straight lines, and these peaks and troughs are formed contiguously, and these peaks and troughs are formed so as to be joined by straight lines.
  • the width and depth of the grooves 333 is the same as for the aforementioned embodiments, and a description is therefore omitted here.
  • the angle between the peaks of the grooves 333 and the direction in which the flow passes over the peak of a groove 333 and flows into the trough of the adjacent groove 333 , or passes over the peak of a groove 333 and proceeds diagonally towards the top of the adjacent groove 333 can be greater than in the fifth embodiment in some parts, and such parts can be formed in greater numbers than in the sixth embodiment. Therefore strong turbulence occurs at these parts due to the flow of fluid along the hub surface 12 c close to the hub surface 12 c, and expansion of the boundary layer or separation of flow can be prevented.
  • FIG. 9A is a similar diagram to FIG. 5 , FIG. 7 , and FIG. 8A , being a perspective view of the main parts omitting approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side.
  • An impeller 340 of the present embodiment differs from the aforementioned embodiments in that grooves 343 serving as the boundary layer expansion prevention part are formed so that they mutually intersect. Since other elements of the configuration are the same as for the aforementioned embodiments, a description of these elements of the configuration is omitted here, and only the grooves 343 are described.
  • the grooves 343 serving as the boundary layer expansion prevention part of the present embodiment are formed from a plurality of grooves 343 a formed so as to cut diagonally across the flow path formed between the blade 11 and the blade 11 from one side to the other side, and a plurality of grooves 343 b formed so as to intersect with the grooves 343 a and so as to cut diagonally across the flow path formed between the blade 11 and the blade 11 from the other side to the former side. That is to say, formed so that the grooves 343 a extending from bottom-left to top-right, and the grooves 343 b extending from bottom-right to top-left mutually intersect.
  • the solid lines indicating the grooves 343 a and 343 b in FIG. 9A and FIG. 9B are lines indicating the deepest part of the grooves.
  • reference symbol 343 c indicates the parts remaining after the grooves 343 a and 343 b have been inscribed. That is to say, the projections where the machining tracks formed at the time of machining of the impeller remain on the apex surface.
  • the width and depth of the grooves 343 a and 343 b is the same as for the aforementioned embodiments, and a description is therefore omitted here.
  • a plurality of projections 343 c is formed, and the flow along the hub surface 12 c close to the hub surface 12 c collides with these projections 343 c, or passes over these projections 343 c and flows into the troughs of the adjacent grooves 343 a and 343 b, or passes over the peak of the projection 343 c and proceeds diagonally towards the top of the adjacent grooves 343 a and 343 b, so that turbulence occurs in the flow along the hub surface 12 c close to the hub surface 12 c, and expansion of the boundary layer or separation of flow can be prevented.
  • FIG. 10A is a similar diagram to FIG. 5 , FIG. 7 , FIG. 8A , and FIG. 9A , being a perspective view of the main parts omitting approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side.
  • An impeller 350 of the present embodiment differs from the aforementioned embodiments in that grooves 353 serving as the boundary layer expansion prevention part are formed concentrically with the axis of rotation of the impeller 350 . Since other elements of the configuration are the same as for the aforementioned embodiments, a description of these elements of the configuration is omitted here, and only the grooves 353 are described.
  • FIG. 10A the grooves 353 serving as the boundary layer expansion prevention part of the present embodiment are formed concentrically with the axis of rotation of the impeller 350 . That is to say, so as to intersect at right angles radial lines extending from the axis of rotation of the impeller 350 to the outer periphery of the impeller 350 .
  • FIG. 10B is a cross-sectional view on c-c in FIG. 10A .
  • the width and depth of the grooves 353 is the same as for the aforementioned embodiments, and a description is therefore omitted here.
  • the grooves 353 serving as the boundary layer expansion prevention part concentrically with the axis of rotation of the impeller 350 , the entire flow flowing along the hub surface 12 c close to the hub surface 12 c passes over the peak of a groove 353 and flows into the trough of the adjacent groove 353 , or passes over the peak of a groove 353 and proceeds diagonally towards the top of the adjacent groove 353 , so that strong turbulence occurs in the flow along the hub surface 12 c close to the hub surface 12 c, and expansion of the boundary layer or separation of flow can be prevented.
  • the grooves 353 are formed linearly, the grooves 353 can be readily machined, and manufacturing costs can be kept down.
  • the concentric grooves may be formed in a wave-shape as in the sixth embodiment, or in a sawtooth shape as in the seventh embodiment.
  • FIG. 11 is a similar diagram to FIG. 5 , FIG. 7 , FIG. 8A , FIG. 9A , and FIG. 10A , being a perspective view of the main parts omitting approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side.
  • An impeller 360 of the present embodiment differs from the aforementioned embodiments in that grooves 363 serving as the boundary layer expansion prevention part are formed over a plurality of regions (three regions 363 a, 363 b, and 363 c in the present embodiment). Since other elements of the configuration are the same as for the aforementioned embodiments, a description of these elements of the configuration is omitted here, and only the grooves 363 are described.
  • the grooves 363 serving as the boundary layer expansion prevention part of the present embodiment are fundamentally the same as in the fifth embodiment shown in FIG. 5 .
  • the grooves 363 differ from those in the fifth embodiment in that they are divided into three regions 363 a, 363 b, and 363 c from upstream to downstream. That is to say, a plurality of linear grooves 363 (in FIG.
  • the width and depth of the grooves 363 is the same as for the aforementioned embodiments, and a description is therefore omitted here.
  • FIG. 12A is a similar diagram to FIG. 5 , FIG. 7 , FIG. 8A , FIG. 9A , FIG. 10A , and FIG. 11 , being a perspective view of the main parts omitting approximately 1 ⁇ 4 of the distance from the edge of the impeller inlet to the edge of the outlet, on the inlet side.
  • An impeller 370 of the present embodiment differs from the aforementioned embodiments in that a plurality of convex parts 373 a and a plurality of concave parts (dimples) 373 b are provided instead of the grooves previously described as the boundary layer expansion prevention part. Since other elements of the configuration are the same as for the aforementioned embodiments, a description of these elements of the configuration is omitted here, and only the convex parts 373 a and concave parts 373 b are described.
  • the convex parts 373 a and concave parts 373 b serving as the boundary layer expansion prevention part of the present embodiment are each circular in plan view, and as shown in FIG. 12B , are semi-circular in cross-sectional view.
  • the diameter and depth of the convex parts 373 a and concave parts 373 b are similar to in the aforementioned embodiments, and are preferably between 0.3% and 2.0% of the outside diameter of the impeller, and most preferably between 0.5% and 2.0%.
  • the flow along the hub surface 12 c close to the hub surface 12 c collides with the convex parts 373 a, or passes over the convex parts 373 a and flows into the adjacent concave parts 373 b, or passes over the convex parts 373 a and proceeds diagonally towards the top of the adjacent convex parts 373 a or concave part 373 b, so that turbulence occurs in the flow along the hub surface 12 c close to the hub surface 12 c, and expansion of the boundary layer or separation of flow is prevented.
  • the present invention is not only applied to centrifugal compressors, and may also be applied to mixed-flow compressors.
  • the mixed-flow compressor differs from the centrifugal compressor in that, since the centrifugal force F 1 up to the edge of the impeller outlet acts perpendicularly to the hub surface 12 c, when the present invention is applied to a mixed-flow compressor, the region in which the aforementioned boundary layer expansion prevention part is provided extends to the edge of the impeller outlet. That is to say, the boundary layer expansion prevention part is also provided for the part of the grooves 314 shown in FIG. 5 , FIG. 7 , FIG. 8A , FIG. 9A , FIG. 10A , FIG. 11 , and FIG. 12A .
  • the cross-sectional shape of the grooves 313 , 323 , 333 , 343 a, 343 b, 353 , and 363 is not limited to that shown in FIG. 6B , and for example may also be of a cross-sectional shape as shown in FIG. 13A or FIG. 13B .
  • the cross-section can be a sawtooth-shape as in FIG. 13A in which the trough of a groove is formed as a curve, and the apexes of the trough and peak of the grooves are joined by straight lines, or the initial impeller machining tracks 314 can be left unchanged on the apex of the groove as in FIG. 13B .
  • the present invention is not only applicable to an impeller manufactured by milling, and can also be applied to a cast impeller manufactured by casting. In this case, modifications need only be implemented beforehand to form the aforementioned boundary layer expansion prevention part on the surface of the mold.
  • boundary layer expansion prevention part of the present invention is not limited to the aforementioned grooves, convex parts, concave parts and the like, and similar effects to the aforementioned effects can be obtained by merely having the surface coarser than the hub surface normally used.
US10/577,715 2003-12-03 2004-12-02 Impeller for compressor Abandoned US20070134086A1 (en)

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JP2003403957A JP2005163640A (ja) 2003-12-03 2003-12-03 圧縮機のインペラ
JP2003424283A JP2005180372A (ja) 2003-12-22 2003-12-22 圧縮機のインペラ
PCT/JP2004/017916 WO2005054681A1 (ja) 2003-12-03 2004-12-02 圧縮機のインペラ
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US20150218949A1 (en) * 2012-09-06 2015-08-06 Mitsubishi Heavy Industries, Ltd. Mixed flow turbine
DE102014222877A1 (de) * 2014-11-10 2016-05-12 Siemens Aktiengesellschaft Laufrad einer Radialturbofluidenergiemaschine, Stufe
EP2620651A4 (en) * 2010-12-28 2017-12-13 Mitsubishi Heavy Industries, Ltd. Centrifugal compressor
US20180135643A1 (en) * 2015-05-19 2018-05-17 Hitachi, Ltd. Centrifugal Compressor
US20180156239A1 (en) * 2016-12-05 2018-06-07 Safran Aircraft Engines Turbine engine part with non-axisymmetric surface
US10323518B2 (en) 2013-01-23 2019-06-18 Kabushiki Kaisha Toyota Jidoshokki Turbocharger impeller, method of manufacturing the same, turbocharger, and turbocharger unit
CN113931873A (zh) * 2020-07-14 2022-01-14 株式会社丰田自动织机 叶轮及其制造方法
US20230193922A1 (en) * 2021-12-18 2023-06-22 Borgwarner Inc. Compressor wheel
US11933314B2 (en) 2021-12-18 2024-03-19 Borgwarner Inc. Compressor wheel

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JP2015031180A (ja) * 2013-07-31 2015-02-16 三菱重工業株式会社 回転機械
CN106499665A (zh) * 2016-11-23 2017-03-15 西安交通大学 一种避免叶轮振动中靶向能量传递现象发生的叶轮优化设计方法
EP3712438B1 (en) * 2017-11-15 2023-09-06 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Compressor impeller, compressor, and turbocharger
KR102537524B1 (ko) * 2018-07-06 2023-05-30 엘지전자 주식회사 팬
WO2021234863A1 (ja) * 2020-05-20 2021-11-25 三菱重工エンジン＆ターボチャージャ株式会社 遠心圧縮機のインペラ及び遠心圧縮機

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EP2620651A4 (en) * 2010-12-28 2017-12-13 Mitsubishi Heavy Industries, Ltd. Centrifugal compressor
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US20180156239A1 (en) * 2016-12-05 2018-06-07 Safran Aircraft Engines Turbine engine part with non-axisymmetric surface
US10690149B2 (en) * 2016-12-05 2020-06-23 Safran Aircraft Engines Turbine engine part with non-axisymmetric surface
CN113931873A (zh) * 2020-07-14 2022-01-14 株式会社丰田自动织机 叶轮及其制造方法
US11473429B2 (en) * 2020-07-14 2022-10-18 Kabushiki Kaisha Toyota Jidoshokki Impeller and method of manufacturing the same
US20230193922A1 (en) * 2021-12-18 2023-06-22 Borgwarner Inc. Compressor wheel
US11933314B2 (en) 2021-12-18 2024-03-19 Borgwarner Inc. Compressor wheel

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