WO2022029932A1 - 遠心圧縮機のインペラ及び遠心圧縮機 - Google Patents

遠心圧縮機のインペラ及び遠心圧縮機 Download PDF

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Publication number
WO2022029932A1
WO2022029932A1 PCT/JP2020/030031 JP2020030031W WO2022029932A1 WO 2022029932 A1 WO2022029932 A1 WO 2022029932A1 JP 2020030031 W JP2020030031 W JP 2020030031W WO 2022029932 A1 WO2022029932 A1 WO 2022029932A1
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WO
WIPO (PCT)
Prior art keywords
hub
centrifugal compressor
impeller
outer peripheral
peripheral portion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2020/030031
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English (en)
French (fr)
Japanese (ja)
Inventor
健一郎 岩切
豊 藤田
直志 神坂
浩範 本田
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Engine and Turbocharger Ltd
Original Assignee
Mitsubishi Heavy Industries Engine and Turbocharger Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Engine and Turbocharger Ltd filed Critical Mitsubishi Heavy Industries Engine and Turbocharger Ltd
Priority to PCT/JP2020/030031 priority Critical patent/WO2022029932A1/ja
Priority to JP2022541018A priority patent/JPWO2022029932A1/ja
Priority to US18/015,816 priority patent/US12435730B2/en
Priority to CN202080103036.6A priority patent/CN115989370A/zh
Priority to DE112020007258.4T priority patent/DE112020007258T5/de
Publication of WO2022029932A1 publication Critical patent/WO2022029932A1/ja
Anticipated expiration legal-status Critical
Priority to JP2024048841A priority patent/JP7654133B2/ja
Ceased legal-status Critical Current

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Classifications

    • 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
    • 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
    • F04D29/26—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
    • F04D29/40—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
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade

Definitions

  • This disclosure relates to an impeller of a centrifugal compressor and a centrifugal compressor.
  • Patent Document 1 discloses a configuration of a centrifugal compressor possessed by a turbo machine for the purpose of suppressing a secondary flow and improving the performance of the turbo machine.
  • the impeller has a hub plate and a plurality of blades arranged on one surface side of the hub plate at intervals in the circumferential direction.
  • the plurality of blades have blade spans such that the blade spans in the blade span height direction of each blade in a reference impeller having blades composed of linear elements at which the hub plate and the blades are orthogonal to each other become blades of curved elements. It has a shape formed by laminating in the height direction.
  • the amount of tangential lean and sweep imparted to the blade cross section from at least one end face of the hub plate side end and the anti-hub plate side end of the blade toward the middle part of the span. To increase.
  • a centrifugal compressor if the outer diameter of the impeller is reduced, the weight of the impeller can be reduced and the inertia of the impeller can be reduced.
  • the response of the turbocharger can be improved by reducing the inertia of the impeller.
  • the pressure ratio tends to decrease when the outer diameter of the impeller is reduced, so that it is not easy to suppress the decrease in the pressure ratio with a low-weight impeller.
  • a clearance flow is generated in which a part of the air compressed by the rotation of the impeller flows from the outlet of the impeller to the clearance between the back surface of the impeller and the housing. If this clearance flow increases, the efficiency of the centrifugal compressor will decrease.
  • Patent Document 1 does not disclose the knowledge for solving these problems in the centrifugal compressor.
  • centrifugal compressor impeller and a centrifugal compressor capable of suppressing a decrease in pressure ratio with a low weight and further improving efficiency by suppressing a clearance flow.
  • the impeller of the centrifugal compressor is An impeller of a centrifugal compressor comprising a hub and at least one blade provided on the hub surface of the hub.
  • the hub-side end of the trailing edge of at least one wing It is located radially outside the outer peripheral portion of the hub, and It is located on either a first line extending the hub surface of the hub radially outward or a second line extending the back surface of the hub radially outward.
  • an impeller of a centrifugal compressor and a centrifugal compressor capable of suppressing a decrease in pressure ratio with a low weight and further improving efficiency by suppressing a clearance flow.
  • expressions such as “same”, “equal”, and “homogeneous” that indicate that things are in the same state not only represent exactly the same state, but also have tolerances or differences to the extent that the same function can be obtained. It shall also represent the existing state.
  • the expression representing a shape such as a quadrangular shape or a cylindrical shape not only represents a shape such as a quadrangular shape or a cylindrical shape in a geometrically strict sense, but also an uneven portion or a chamfer within the range where the same effect can be obtained. It shall also represent the shape including the part and the like.
  • the expressions “equipped”, “equipped”, “equipped”, “included”, or “have” one component are not exclusive expressions excluding the existence of other components.
  • FIG. 1 is a schematic cross-sectional view taken along the axial direction of the centrifugal compressor 4 of the turbocharger 2 according to the embodiment.
  • the centrifugal compressor 4 includes an impeller 6, a casing 7 that houses the impeller 6, and a housing 10 that houses a bearing (not shown) that pivotally supports the impeller 6.
  • the impeller 6 includes a hub 12 and at least one wing 15 provided on the hub surface 13 of the hub 12.
  • the impeller 6 includes a plurality of blades 15 provided on the hub surface 13 at intervals in the circumferential direction of the impeller 6.
  • the hub surface 13 is a surface of the hub 12 facing the casing 7, and means a curved surface that is smoothly curved in a concave shape along the blade 15.
  • the circumferential direction of the impeller 6 is simply described as “circumferential direction”
  • the axial direction of the impeller 6 (direction along the rotation axis of the impeller 6) is simply described as “axial direction”
  • the radial direction of the impeller 6 is simply described. It shall be described as "diameter direction”.
  • the casing 7 includes a shroud portion 8 that surrounds a plurality of blades 15 of the impeller 6, and a scroll portion 9 that forms a scroll flow path 20 on the outer peripheral side of the impeller 6.
  • An air flow path 18 is formed between the impeller 6 and the shroud portion 8.
  • the air (fluid) that has flowed into the air flow path 18 from the air inlet 5 of the centrifugal compressor 4 is compressed by the impeller 6 and flows to the scroll flow path 20 through the diffuser flow path 19 on the downstream side of the air flow path 18. ..
  • the diffuser flow path 19 through which the air compressed by the impeller 6 flows is defined by the shroud side wall surface 50 of the casing 7 and the hub side wall surface 26 of the housing 10.
  • a clearance 22 is formed between the hub 12 of the impeller 6 and the housing 10.
  • the position closest to the shroud portion 8 on the trailing edge 16 of the wing 15 is the shroud side end 16a of the trailing edge 16, and the position closest to the hub 12 on the trailing edge 16 of the wing 15 is the hub of the trailing edge 16.
  • the hub side end 16b of the trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12.
  • the entire trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12.
  • the outer peripheral portion 12e of the hub 12 means an outer end portion of the hub 12 in the radial direction, that is, a portion connecting the hub surface 13 of the hub 12 and the back surface 14 of the hub 12.
  • FIG. 2 is a schematic cross-sectional view of the centrifugal compressor 4 (4A) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the first line L1 is a linear virtual line extending radially outward from the outer peripheral end 13a of the hub surface 13 along the tangential direction of the hub surface 13.
  • the wing 15 includes a wing root outer peripheral portion 24 that connects the hub side end 16b of the trailing edge 16 and the outer peripheral portion 12e of the hub 12.
  • the wing root outer peripheral portion 24 extends along the first line L1 so as to connect the hub side end 16b of the trailing edge 16 and the outer peripheral end 13a of the hub surface 13.
  • the trailing edge 16 is formed along the axial direction and extends parallel to the axial direction.
  • the housing 10 is axially connected to the hub side wall surface 26 facing the wing root outer peripheral portion 24, the back side wall surface 28 facing the back surface 14 of the impeller 6, and the hub side wall surface 26 and the back side wall surface 28.
  • the step surface 30 is a facing wall surface facing the outer peripheral portion 12e of the hub 12.
  • the wing root outer peripheral portion 24 is formed along the hub side wall surface 26 and extends parallel to the hub side wall surface 26.
  • the hub side end 16b of the trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12 (outer peripheral end of the hub 12). Therefore, it has the same outer diameter of the impeller 6 as the configuration shown in FIG. 2, and the radial position of the outer peripheral end 13a of the hub surface 13 is expanded to the radial position of the hub side end 16b of the trailing edge 16. Compared with the configuration, the weight of the impeller 6 can be reduced while suppressing the decrease in the pressure ratio of the centrifugal compressor 4. Further, it has the same outer diameter of the hub 12 as the configuration shown in FIG.
  • the hub side end 16b of the trailing edge 16 is located on the first line L1 in which the hub surface 13 extends radially outward. Therefore, the wing 15 of the impeller 6 covers the clearance 22 between the hub 12 and the housing 10, and the inlet of the clearance 22 (the gap between the outer peripheral portion 12e of the hub 12 and the housing 10) as the impeller 6 rotates. Centrifugal force acts on the air in the vicinity, and the effect of suppressing the inflow of the clearance flow into the clearance 22 can be further enhanced.
  • the decrease in the pressure ratio of the centrifugal compressor 4 can be suppressed with a low weight, and the efficiency of the centrifugal compressor 4 is improved by further suppressing the clearance flow. can do.
  • FIG. 3 is a schematic cross-sectional view of the centrifugal compressor 4 (4B) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 2 shall indicate the same configuration as each configuration shown in FIG. 2 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 3 is different from the configuration shown in FIG. 2 in that the trailing edge 16 is inclined inward in the radial direction toward the hub 12 side. That is, in the impeller 6 of the centrifugal compressor 4 (4B), the trailing edge 16 is inclined with respect to the axial direction and linear so that the shroud side end 16a is located outside the hub side end 16b in the radial direction. It is extended to. The shroud portion 8 side of the trailing edge 16 projects radially outward from the hub 12 side of the trailing edge.
  • FIG. 4 is a schematic cross-sectional view of the centrifugal compressor 4 (4C) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 2 shall indicate the same configuration as each configuration shown in FIG. 2 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 4 is different from the configuration shown in FIG. 2 in that the trailing edge 16 is inclined outward in the radial direction toward the hub 12 side. That is, in the impeller 6 of the centrifugal compressor 4 (4C), the trailing edge 16 is inclined with respect to the axial direction and linear so that the shroud side end 16a is located inside the hub side end 16b in the radial direction. It is extended to. The hub 12 side of the trailing edge 16 projects radially outward from the shroud portion 8 side of the trailing edge 16.
  • FIG. 5 is a schematic cross-sectional view of the centrifugal compressor 4 (4D) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 2 shall indicate the same configuration as each configuration shown in FIG. 2 unless otherwise specified, and the description thereof will be omitted.
  • the trailing edge 16 is radially outward as it is directed from the shroud side edge 16a toward the central portion 16c of the trailing edge 16, and radially outward as it is directed from the central portion 16c toward the hub side edge 16b of the trailing edge 16. It differs from the configuration shown in FIG. 2 in that it is smoothly curved toward the inside. That is, in the impeller 6 of the centrifugal compressor 4 (4D), the trailing edge 16c is located radially outward from each of the shroud side end 16a and the hub side end 16b of the trailing edge 16. 16 is smoothly curved.
  • the hub side end 16b of the trailing edge 16 is radially outside the outer peripheral portion 12e of the hub 12 (outer peripheral end of the hub 12).
  • the hub-side end 16b of the trailing edge 16 is located on the first line L1 extending the hub surface 13 radially outward. Therefore, for the same reason as the configuration shown in FIG. 2, it is possible to suppress a decrease in the pressure ratio of the centrifugal compressor 4 with a low weight, and further improve the efficiency of the centrifugal compressor 4 by suppressing the clearance flow. can.
  • the trailing edge 16 is located on the outer side in the radial direction from the outer peripheral portion 12e of the hub 12, the total pressure increases due to the expansion of the outer diameter of the impeller 6. Therefore, as shown in FIGS. 3 to 5, by adjusting the shape of the portion of the blade 15 that protrudes from the outer peripheral portion 12e of the hub 12, the non-uniform total pressure distribution generated by the impeller 6 can be adjusted. It is possible to suppress the occurrence of peeling in the diffuser flow path 19. In particular, in the centrifugal compressor 4 (4B) shown in FIG. 3 and the centrifugal compressor 4 (4D) shown in FIG. 5, the mass of the hub 12 is reduced, and as a result, the centrifugal stress acting on the hub can be reduced. can.
  • FIG. 6 is a schematic cross-sectional view of the centrifugal compressor 4 (4E) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 3 shall indicate the same configuration as each configuration shown in FIG. 3 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 6 is the configuration shown in FIG. 3 in that the outer peripheral portion 12e of the hub 12 has a C surface 32 formed so that the hub surface 13 side is located radially outside the back surface 14 side. Different from.
  • the C surface 32 is formed in a plane shape, and is inclined inward in the radial direction from the hub surface 13 side toward the back surface 14 side.
  • the stepped surface 30 of the housing 10 includes the C surface 52 formed in parallel with the C surface 32. The C surface 52 extends inward in the radial direction from the hub side wall surface 26 toward the back side wall surface 28.
  • FIG. 7 is a schematic cross-sectional view of the centrifugal compressor 4 (4F) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 3 shall indicate the same configuration as each configuration shown in FIG. 3 unless otherwise specified, and the description thereof will be omitted.
  • the outer peripheral portion 12e of the hub 12 has a concave R surface 34 formed so that the hub surface 13 side is located radially outside the back surface 14 side. It is different from the configuration shown.
  • the R surface 34 is smoothly curved and is inclined inward in the radial direction from the hub surface 13 side to the back surface 14 side.
  • the stepped surface 30 of the housing 10 includes a convex R surface 54 formed in parallel with the R surface 34.
  • the R surface 54 is formed to be smoothly curved, and extends inward in the radial direction from the hub side wall surface 26 toward the back side wall surface 28.
  • the hub side end 16b of the trailing edge 16 is the outer peripheral portion 12e of the hub 12 (the hub 12). It is located radially outward from the outer peripheral end), and the hub side end 16b of the trailing edge 16 is located on the first line L1 extending the hub surface 13 radially outward. Therefore, for the same reason as the configuration shown in FIG. 2, it is possible to suppress a decrease in the pressure ratio of the centrifugal compressor 4 with a low weight, and further improve the efficiency of the centrifugal compressor 4 by suppressing the clearance flow. can.
  • a clearance 22 flows between the outer peripheral portion 12e of the hub 12 and the stepped surface 30. It can be tilted in the opposite direction to the direction. As a result, the main flow flowing through the air flow path 18 is suppressed from entering the clearance 22, and the clearance loss can be reduced, so that the efficiency of the centrifugal compressor 4 can be improved.
  • FIG. 8 is a schematic cross-sectional view of the centrifugal compressor 4 (4G) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 3 shall indicate the same configuration as each configuration shown in FIG. 3 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 8 is different from the configuration shown in FIG. 3 in that the wing root outer peripheral portion 24 connecting the hub side end 16b of the trailing edge 16 and the outer peripheral portion 12e of the hub 12 has a C surface edge 36.
  • the wing root outer peripheral portion 24 has a portion 35 extending radially inward from the hub side end 16b of the trailing edge 16, and a radial inner end and the outer peripheral portion 12e of the portion 35. Includes a C-plane edge 36 to be connected.
  • the C-plane edge 36 is inclined inward in the radial direction as it moves away from the portion 35 in the axial direction, and is connected to the boundary between the outer peripheral portion 12e and the back surface 14.
  • the stepped surface 30 of the housing 10 includes the C surface 52 formed in parallel with the C surface edge 36, and the C surface 52 increases from the hub side wall surface 26 toward the back side wall surface 28. It extends inward in the radial direction.
  • FIG. 9 is a schematic cross-sectional view of the centrifugal compressor 4 (4H) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 3 shall indicate the same configuration as each configuration shown in FIG. 3 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 9 is different from the configuration shown in FIG. 3 in that the wing root outer peripheral portion 24 connecting the hub side end 16b of the trailing edge 16 and the outer peripheral portion 12e of the hub 12 has a concave R surface edge 38. ..
  • the wing root outer peripheral portion 24 has a portion 35 extending radially inward from the hub side end 16b of the trailing edge 16, and a radial inner end and the outer peripheral portion 12e of the portion 35. Includes a concave R-face edge 38 to be connected.
  • the R surface edge 38 is smoothly curved so as to be radially inward as it is separated from the portion 35 in the axial direction, and is connected to the boundary between the outer peripheral portion 12e and the back surface 14.
  • the stepped surface 30 of the housing 10 includes a convex R surface 54 formed in parallel with the R surface edge 38.
  • the R surface 54 is formed to be smoothly curved, and extends inward in the radial direction from the hub side wall surface 26 toward the back side wall surface 28.
  • the hub side end 16b of the trailing edge 16 is the outer peripheral portion 12e of the hub 12 (the hub 12). It is located radially outward from the outer peripheral end), and the hub side end 16b of the trailing edge 16 is located on the first line L1 extending the hub surface 13 radially outward. Therefore, for the same reason as the configuration shown in FIG. 2, it is possible to suppress a decrease in the pressure ratio of the centrifugal compressor 4 with a low weight, and further improve the efficiency of the centrifugal compressor 4 by suppressing the clearance flow. can.
  • the C surface edge 36 or the R surface edge 38 of the blade root outer peripheral portion 24 and the stepped surface can be tilted in the direction opposite to the flow direction.
  • the main flow flowing through the air flow path 18 is suppressed from entering the clearance 22, and the clearance loss can be reduced, so that the efficiency of the centrifugal compressor 4 can be improved.
  • the stress concentration can be relaxed without forming a corner portion in the blade root outer peripheral portion 24, the strength of the blade 15 against centrifugal stress can be improved.
  • FIG. 10 is a schematic cross-sectional view of the centrifugal compressor 4 (4I) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 3 shall indicate the same configuration as each configuration shown in FIG. 3 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 10 is the configuration shown in FIG. 3 in that the outer peripheral portion 12e of the hub 12 has a C surface 40 formed so that the back surface 14 side is located radially outside the hub surface 13 side. Different from.
  • the C surface 40 is formed in a plane shape, and is inclined outward in the radial direction from the hub surface 13 side toward the back surface 14 side.
  • the stepped surface 30 of the housing 10 is formed in parallel with the C surface 40. That is, the stepped surface 30 is also configured as a C surface, and extends outward in the radial direction from the hub side wall surface 26 side toward the back side wall surface 28 side.
  • the outer peripheral portion 12e has a concave shape that is inclined outward in the radial direction from the hub surface 13 side to the back surface 14 side instead of the C surface 40 or together with the C surface 40. It may have an R surface.
  • the hub side end 16b of the trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12, and the trailing edge 16 is located at the trailing edge.
  • the hub side end 16b of 16 is located on the first line L1 extending the hub surface 13 radially outward. Therefore, for the same reason as the configuration shown in FIG. 2, it is possible to suppress a decrease in the pressure ratio of the centrifugal compressor 4 with a low weight, and further improve the efficiency of the centrifugal compressor 4 by suppressing the clearance flow. can.
  • peeling f may occur on the side wall surface 26 side of the hub.
  • the clearance loss in the case where the peeling f as described above occurs can be reduced. Can be reduced.
  • FIG. 11 is a schematic cross-sectional view of the centrifugal compressor 4 (4J) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 10 shall indicate the same configuration as each configuration shown in FIG. 10 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 11 is different from the configuration shown in FIG. 10 in that the wing root outer peripheral portion 24 connecting the hub side end 16b of the trailing edge 16 and the outer peripheral portion 12e of the hub 12 has a concave R surface edge 38. ..
  • the R surface edge 38 is smoothly curved so as to be radially inward as it is separated from the trailing edge 16 in the axial direction, and is connected to the boundary between the outer peripheral portion 12e and the back surface 14.
  • the stepped surface 30 of the housing 10 includes a convex R surface 54 formed in parallel with the R surface edge 38.
  • the R surface 54 is formed to be smoothly curved, and extends inward in the radial direction from the hub side wall surface 26 side toward the back side wall surface 28 side.
  • the hub side end 16b of the trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12, and the trailing edge 16 is located at the trailing edge.
  • the hub side end 16b of 16 is located on the first line L1 extending the hub surface 13 radially outward. Therefore, for the same reason as the configuration shown in FIG. 2, it is possible to suppress a decrease in the pressure ratio of the centrifugal compressor 4 with a low weight, and further improve the efficiency of the centrifugal compressor 4 by suppressing the clearance flow. can.
  • the wing root outer peripheral portion 24 has a concave R surface edge 38, stress concentration can be relaxed without forming a corner portion in the wing root outer peripheral portion 24, so that the strength of the blade 15 against centrifugal stress is improved. be able to.
  • the flow is discharged from the clearance 22 toward the outer peripheral side (that is, the air flow path 18 side) due to the action of the centrifugal force accompanying the rotation of the blade 15.
  • the action is generated, and it can contribute to the reduction of clearance loss and the reduction of thrust load.
  • the outer peripheral portion 12e has a concave shape that is inclined outward in the radial direction from the hub surface 13 side to the back surface 14 side instead of the C surface 40 or together with the C surface 40. It may have an R surface. Further, instead of forming the stepped surface 30 with a convexly curved R surface, the stepped surface 30 may be formed with a C surface.
  • FIG. 12 is a schematic cross-sectional view of the centrifugal compressor 4 (4K) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 2 shall indicate the same configuration as each configuration shown in FIG. 2 unless otherwise specified, and the description thereof will be omitted.
  • the hub side end 16b of the trailing edge 16 is located on the first line L1.
  • the first line L1 is a curved line continuous with the hub surface 13 extending radially outward from the outer peripheral end 13a of the hub surface 13.
  • the wing 15 includes a wing root outer peripheral portion 24 that connects the hub side end 16b of the trailing edge 16 and the outer peripheral portion 12e of the hub 12.
  • the wing root outer peripheral portion 24 extends curvedly along the first line L1 so as to connect the hub side end 16b of the trailing edge 16 and the outer peripheral end 13a of the hub surface 13.
  • the trailing edge 16 is inclined with respect to the axial direction and extends linearly so that the shroud side end 16a is located outside the hub side end 16b in the radial direction.
  • the wing root outer peripheral portion 24 is formed along the hub side wall surface 26 and extends parallel to the hub side wall surface 26.
  • the hub side wall surface 26 includes a curved portion 27 that curves along the outer peripheral portion 24 of the wing root.
  • the wing root outer peripheral portion 24 is formed along the curved portion 27, and is formed parallel to the curved portion 27.
  • the hub side end 16b of the trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12, and the trailing edge 16 is located at the trailing edge.
  • the hub side end 16b of 16 is located on the first line L1 extending the hub surface 13 radially outward. Therefore, for the same reason as the configuration shown in FIG. 2, it is possible to suppress a decrease in the pressure ratio of the centrifugal compressor 4 with a low weight, and further improve the efficiency of the centrifugal compressor 4 by suppressing the clearance flow. can.
  • FIG. 13 is a schematic cross-sectional view of the centrifugal compressor 4 (4L) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • a reference numeral common to each configuration shown in FIG. 2 shall indicate the same configuration as each configuration shown in FIG. 2 unless otherwise specified, and description thereof will be omitted.
  • the second line L2 is a linear virtual line extending radially outward from the outer peripheral end 14a of the back surface 14 along the tangential direction (diameter direction) of the back surface 14. ..
  • the wing 15 includes a wing root outer peripheral portion 24 that connects the hub side end 16b of the trailing edge 16 and the outer peripheral portion 12e of the hub 12.
  • the wing root outer peripheral portion 24 extends along the second line L2 so as to connect the hub side end 16b of the trailing edge 16 and the outer peripheral end 14a of the back surface 14.
  • the housing 10 does not have the stepped surface 30 shown in FIG. 2 and the like, and is opposed to the hub side wall surface 26 facing the wing root outer peripheral portion 24 and the back surface 14 of the impeller 6. Includes a back side wall surface 28 that connects to the hub side wall surface 26.
  • the wing root outer peripheral portion 24 is formed along the hub side wall surface 26 and extends parallel to the hub side wall surface 26.
  • the hub side end 16b of the trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12. Therefore, it has the same outer diameter of the impeller 6 as the configuration shown in FIG. 13, and the radial position of the hub side end 16b of the trailing edge 16 and the radial position of the outer peripheral end 13a of the hub surface 13 coincide with each other.
  • the weight of the impeller 6 can be reduced while suppressing the decrease in the pressure ratio of the centrifugal compressor 4. Further, it has the same outer diameter of the impeller 6 as the outer diameter of the hub 12 shown in FIG.
  • the hub side end 16b of the trailing edge 16 is located on the second line L2 which extends the back surface 14 radially outward. Therefore, as the impeller 6 rotates, a centrifugal force acts on the air near the inlet of the clearance 22 (the gap between the outer peripheral portion 12e of the hub 12 and the housing 10) to suppress the inflow of the clearance flow into the clearance 22. The effect can be further enhanced. Further, since the clearance 22 between the hub 12 and the housing 10 extends in the direction opposite to the main flow leaving the air flow path 18 from the position of the outer peripheral portion 12e of the hub 12, the main flow leaving the air flow path 18 is the clearance 22. It is possible to suppress the entry and further reduce the clearance loss.
  • the decrease in the pressure ratio of the centrifugal compressor 4 can be suppressed with a low weight, and the efficiency of the centrifugal compressor 4 is improved by further suppressing the clearance flow. can do.
  • FIG. 14 is a schematic cross-sectional view of the centrifugal compressor 4 (4M) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 13 shall indicate the same configuration as each configuration shown in FIG. 13, unless otherwise specified, and description thereof will be omitted.
  • the configuration shown in FIG. 14 is different from the configuration shown in FIG. 13 in that the hub 12 has a convex R surface portion 42 that is smoothly curved so as to connect the hub surface 13 and the outer peripheral portion 12e.
  • the hub side end 16b of the trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12 (outer peripheral end of the hub 12).
  • the hub-side end 16b of the trailing edge 16 is located on the second line L2, which extends the back surface 14 radially outward. Therefore, for the same reason as the configuration shown in FIG. 13, it is possible to suppress a decrease in the pressure ratio of the centrifugal compressor 4 with a low weight, and further improve the efficiency of the centrifugal compressor 4 by suppressing the clearance flow. can.
  • the hub 12 has a convex R surface portion 42 connecting the hub surface 13 and the outer peripheral portion 12e, it is possible to prevent the flow path area from rapidly expanding at the position of the outer peripheral portion 12e of the hub 12. The efficiency improvement effect can be enhanced.
  • FIG. 15 is a schematic cross-sectional view of the centrifugal compressor 4 (4N) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 13 shall indicate the same configuration as each configuration shown in FIG. 13 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 15 is different from the configuration shown in FIG. 13 in that the hub 12 has an inscribed surface portion 44 that is continuous with the hub surface 13 and inscribed with respect to the second line L2.
  • the inscribed surface portion 44 is inscribed in the wing root outer peripheral portion 24.
  • the hub side end 16b of the trailing edge 16 is located radially outside the outer peripheral portion 12e of the hub 12 (outer peripheral end of the hub 12).
  • the hub-side end 16b of the trailing edge 16 is located on the second line L2, which extends the back surface 14 radially outward. Therefore, for the same reason as the configuration shown in FIG. 13, it is possible to suppress a decrease in the pressure ratio of the centrifugal compressor 4 with a low weight, and further improve the efficiency of the centrifugal compressor 4 by suppressing the clearance flow. can.
  • the hub 12 has an inscribed surface portion 44 that is continuous with the hub surface 13 and inscribed with respect to the second line L2, it is possible to prevent the flow path area from rapidly expanding at the position of the outer peripheral portion 12e of the hub 12. And the efficiency improvement effect can be enhanced.
  • the angle formed by the mainstream flowing through the air flow path 18 and the hub side wall surface 26 of the housing 10 can be reduced, whereby the mainstream can be suppressed from entering the clearance 22 and the clearance loss can be reduced.
  • the outer peripheral portion 12e of the hub 12 may include a minute R surface.
  • FIG. 16 is a schematic cross-sectional view of the centrifugal compressor 4 (4O) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to the configurations shown in FIG. 13 indicate the same configurations as those shown in FIG. 13 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 16 is different from the configuration shown in FIG. 13 in that the back surface 14 of the impeller 6 has a curved surface 46 formed in a concave shape.
  • the curved surface 46 is smoothly curved, and is inclined in the radial direction so as to move inward in the radial direction as the distance from the outer peripheral portion 12e of the impeller 6 increases in the axial direction.
  • the back side wall surface 28 of the housing 10 is formed parallel to the curved surface 46. That is, the back side wall surface 28 is configured to be smoothly curved as a convex curved surface, and extends inward in the radial direction as the distance from the hub side wall surface 26 in the axial direction increases.
  • FIG. 17 is a schematic cross-sectional view of the centrifugal compressor 4 (4P) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to the configurations shown in FIG. 16 indicate the same configurations as those shown in FIG. 16 unless otherwise specified, and the description thereof will be omitted.
  • the configuration shown in FIG. 17 is different from the configuration shown in FIG. 13 in that the outer peripheral portion 24 of the wing root has a curved surface edge 48 continuous with the curved surface 46.
  • the second line L2 is a curved virtual line extending radially outward from the outer peripheral end 14a of the back surface 14, and the hub side end 16b of the trailing edge 16 is the second line. Located on line L2. Further, the portion of the hub side wall surface 26 facing the curved surface edge 48 is smoothly curved as a convex curved surface so as to be parallel to the curved surface edge 48.
  • FIG. 18 is a schematic cross-sectional view of the centrifugal compressor 4 (4Q) according to the embodiment along the axial direction, and shows an example of the detailed configuration of the centrifugal compressor 4 shown in FIG.
  • the reference numerals common to each configuration shown in FIG. 16 indicate the same configuration as each configuration shown in FIG. 16 unless otherwise specified, and the description thereof will be omitted.
  • the second line L2 is a curved virtual line extending radially outward from the outer peripheral end 14a of the back surface 14, and has a hub surface 13 having a diameter. It corresponds to the first line L1 extending outward in the direction. Therefore, the hub-side end 16b of the trailing edge 16 is located on the second line L2 and on the first line L1.
  • the flow path width of the diffuser flow path 19 at the position of the hub side end 16b of the trailing edge 16 is W1, the hub side end 16b of the trailing edge 16 and the hub side wall surface.
  • the centrifugal compressor 4 is configured so as to satisfy 0.20 ⁇ W2 / W1.
  • the centrifugal compressor 4 may preferably satisfy 0.16 ⁇ W2 / W1.
  • the above-mentioned centrifugal compressor 4 (4A) has been described as an example, but in each of the above-mentioned centrifugal compressors 4 (4B to 4Q), 0.20 ⁇ W2 / W1 (more preferably 0). .16 ⁇ W2 / W1) may be satisfied.
  • the present disclosure is not limited to the above-mentioned embodiment, and includes a form in which the above-mentioned embodiment is modified and a form in which these forms are appropriately combined.
  • the impeller for example, the above-mentioned impeller 6 of the centrifugal compressor (for example, the above-mentioned centrifugal compressor 4 (4A to 4Q)) according to at least one embodiment of the present disclosure may be used.
  • An impeller of a centrifugal compressor comprising a hub (eg, the hub 12 described above) and at least one blade (eg, the blade 15 described above) provided on the hub surface (eg, the hub surface 13) of the hub.
  • the hub-side end (eg, the above-mentioned hub-side end 16b) of the trailing edge of at least one wing is It is located radially outside the outer peripheral portion of the hub (for example, the outer peripheral portion 12e described above), and A first line extending the hub surface of the hub radially outward (eg, the first line L1 described above), or a second line extending the back surface of the hub (eg, the back surface 14 described above) radially outward (eg, the back surface 14 described above). It is located on one of the above-mentioned second lines L2).
  • the hub-side end of the trailing edge is located radially outside the outer peripheral portion of the hub. Therefore, compared with the configuration in which the radial position of the outer peripheral end of the hub surface is expanded to the radial position of the hub side end of the trailing edge while maintaining the outer diameter of the impeller, the decrease in the pressure ratio of the centrifugal compressor is suppressed. However, the weight of the impeller can be reduced. Further, compared with the configuration in which the outer diameter of the impeller is reduced and the radial position of the hub side end of the trailing edge is reduced to the radial position of the outer peripheral end of the hub surface, the impeller is increased while increasing the pressure ratio of the centrifugal compressor.
  • the hub-side end of the trailing edge is located on either the first line extending the hub surface radially outward or the second line extending the back surface of the hub radially outward. .. Therefore, the centrifugal force acts on the air near the inlet of the clearance with the rotation of the impeller, and the effect of suppressing the inflow of the clearance flow can be further enhanced.
  • the shroud-side end of the trailing edge (eg, the shroud-side end 16a described above) is located radially outward of the hub-side end.
  • the total pressure tends to decrease on the shroud side as compared to the hub side. Therefore, according to the configuration described in (3) above, the non-uniform total pressure distribution generated by the impeller is made uniform. It is possible to suppress the occurrence of peeling in the diffuser flow path. Further, as a result of reducing the mass of the portion of the blade near the outer peripheral portion of the hub, the centrifugal stress acting on the hub can be reduced.
  • the total pressure on the hub side may be lower than that on the shroud side. Therefore, according to the configuration described in (4) above, the non-uniform total pressure distribution generated by the impeller can be made uniform, and the occurrence of peeling in the diffuser flow path can be suppressed.
  • the central portion of the trailing edge (eg, the central portion 16c described above) is located radially outward of the shroud-side and hub-side ends of the trailing edge.
  • the total pressure may be lower at the center of the trailing edge than at the hub side and shroud side. Therefore, according to the configuration described in (5) above, the non-uniform total pressure distribution generated by the impeller can be made uniform, and the occurrence of peeling in the diffuser flow path can be suppressed.
  • the outer peripheral portion of the hub is a C surface (for example, the above-mentioned C surface 32) or a concave R surface (for example, the above-mentioned above) formed so that the hub surface side is located radially outside the back surface side. It has an R surface 34).
  • the clearance formed along the outer peripheral portion of the hub can be inclined in the direction opposite to the mainstream flow direction of the centrifugal compressor.
  • the mainstream is suppressed from entering the clearance, and the clearance loss can be reduced, so that the efficiency of the centrifugal compressor can be improved.
  • the at least one wing is a wing root outer peripheral portion (for example, the above-mentioned wing root outer peripheral portion 24) connecting the hub-side end of the trailing edge and the outer peripheral portion of the hub, and is a C-plane edge (for example, the above-mentioned above-mentioned).
  • a wing root perimeter having a C-face edge 36) or a concave R-face edge (eg, the R-face edge 38 described above).
  • the clearance formed along the C-plane edge or the R-plane edge of the outer peripheral portion of the wing root is set in the direction opposite to the mainstream flow direction of the centrifugal compressor. Can be tilted. As a result, the mainstream is suppressed from entering the clearance, and the clearance loss can be reduced, so that the efficiency of the centrifugal compressor can be improved. Further, since the stress concentration can be relaxed without forming a corner portion on the outer peripheral portion of the blade root, the strength of the blade against centrifugal stress can be improved.
  • the outer peripheral portion of the hub has a C surface (for example, the C surface 40 described above) or a concave R surface formed so that the back surface side is located radially outside the hub surface side.
  • peeling may occur on the hub side of the diffuser flow path.
  • peeling occurs by adopting the C surface or the concave R surface described in (8) above and inclining the shape of the clearance along the outer peripheral surface of the hub. Clearance loss can be reduced.
  • the at least one wing is a wing root outer peripheral portion (for example, the above-mentioned wing root outer peripheral portion 24) connecting the hub-side end of the trailing edge and the outer peripheral portion of the hub, and is a C-plane edge (for example, the above-mentioned above-mentioned).
  • a wing root perimeter having a C-face edge 36) or a concave R-face edge (eg, the R-face edge 38 described above).
  • the hub has a convex R surface portion (for example, the above-mentioned R surface portion 42) that connects the hub surface and the outer peripheral portion.
  • the hub since the hub has a convex R surface portion connecting the hub surface and the outer peripheral portion, the flow path area rapidly expands at the position of the outer peripheral portion of the hub. This can be suppressed and the efficiency improvement effect can be enhanced.
  • the hub has an inscribed surface portion (for example, the above-mentioned inscribed surface portion 44) that is continuous with the hub surface and inscribed with respect to the second line.
  • the flow path area is located at the position of the outer peripheral portion of the hub. It is possible to suppress rapid expansion and enhance the efficiency improvement effect.
  • the angle between the mainstream of the centrifugal compressor and the hub side wall surface of the diffuser flow path can be reduced, which prevents the mainstream from entering the clearance on the back side of the impeller and reduces clearance loss. can.
  • the back surface of the hub has a concavely formed curved surface (eg, the curved surface 46 described above).
  • the at least one wing is a wing root outer peripheral portion (for example, the wing root outer peripheral portion 24 described above) that connects the hub side end of the trailing edge and the outer peripheral portion of the hub, and is a curved edge continuous with the curved surface.
  • a wing root outer peripheral portion for example, the wing root outer peripheral portion 24 described above
  • curved edge 48 described above includes the outer peripheral portion of the wing root.
  • the hub has an inscribed surface portion (for example, the above-mentioned inscribed surface portion 44) that is continuous with the hub surface and inscribed with respect to the second line.
  • the flow path area is located at the position of the outer peripheral portion of the hub. It is possible to suppress rapid expansion and enhance the efficiency improvement effect.
  • the centrifugal compressor according to at least one embodiment of the present disclosure is The impeller of the centrifugal compressor according to any one of (1) to (15) above, and A centrifugal compressor comprising a shroud side wall surface and a hub side wall surface that define a diffuser flow path (for example, the above-mentioned diffuser flow path 19) through which a fluid compressed by an impeller of the centrifugal compressor flows.
  • the flow path width of the diffuser flow path at the position of the hub side end of the trailing edge is W1
  • W2 When the distance along the axial direction between the hub side end of the trailing edge and the hub side wall surface is W2, 0.20 ⁇ W2 / W1 is satisfied.
  • the centrifugal force is effectively applied to the air near the inlet of the clearance formed along the back surface of the impeller as the impeller rotates, and the centrifugal force is applied to the clearance.
  • the effect of suppressing the inflow of the clearance flow can be further enhanced.
  • the centrifugal compressor according to at least one embodiment of the present disclosure is With the impeller of the centrifugal compressor described in (6) above, A shroud side wall surface and a hub side wall surface that define a diffuser flow path (for example, the above-mentioned diffuser flow path 19) through which a fluid compressed by an impeller of the centrifugal compressor flows.
  • a centrifugal compressor comprising a back side wall surface facing the back surface of the hub.
  • a facing wall surface that connects the hub side wall surface and the back side wall surface and that faces the outer peripheral surface of the hub and has a C-plane or a convex R-plane is further provided.
  • the clearance between the outer peripheral portion of the hub and the facing wall surface can be inclined in the direction opposite to the flow direction.
  • the mainstream of the centrifugal compressor is suppressed from entering the clearance, and the clearance loss can be reduced, so that the efficiency of the centrifugal compressor can be improved.
  • the centrifugal compressor according to at least one embodiment of the present disclosure is With the impeller of the centrifugal compressor described in (7) above, A shroud side wall surface and a hub side wall surface that define a diffuser flow path (for example, the above-mentioned diffuser flow path 19) through which a fluid compressed by an impeller of the centrifugal compressor flows.
  • a centrifugal compressor comprising a back side wall surface facing the back surface of the hub.
  • a facing wall surface that connects the hub side wall surface and the back side wall surface and that faces the outer peripheral portion of the wing root and has a C-plane or a convex R-plane is further provided.
  • the clearance between the outer peripheral portion of the wing root and the facing wall surface can be inclined in the direction opposite to the flow direction.
  • the mainstream of the centrifugal compressor is suppressed from entering the clearance, and the clearance loss can be reduced, so that the efficiency of the centrifugal compressor can be improved.
  • the centrifugal compressor according to at least one embodiment of the present disclosure is With the impeller of the centrifugal compressor described in (8) above, A shroud side wall surface and a hub side wall surface that define a diffuser flow path (for example, the above-mentioned diffuser flow path 19) through which a fluid compressed by an impeller of the centrifugal compressor flows.
  • a centrifugal compressor comprising a back side wall surface facing the back surface of the hub.
  • a facing wall surface that connects the hub side wall surface and the back side wall surface and that faces the outer peripheral portion of the hub and has a C-plane or a convex R-plane is further provided.
  • the clearance between the outer peripheral portion of the hub and the facing wall surface can be inclined in the direction opposite to the flow direction.
  • the mainstream of the centrifugal compressor is suppressed from entering the clearance, and the clearance loss can be reduced, so that the efficiency of the centrifugal compressor can be improved.
  • the centrifugal compressor according to at least one embodiment of the present disclosure is The impeller of the centrifugal compressor according to any one of (1) to (15) above, and A housing (for example, the housing 10 described above) that houses a bearing that supports the impeller. Equipped with The at least one wing includes a wing root outer peripheral portion (for example, the above-mentioned wing root outer peripheral portion 24) connecting the hub-side end of the trailing edge and the outer peripheral portion of the hub. The outer peripheral portion of the wing root extends parallel to the facing wall surface of the housing facing the outer peripheral portion of the wing root.
  • the outer peripheral portion of the wing root extends parallel to the facing wall surface of the housing facing the outer peripheral portion of the wing root. Therefore, the centrifugal force acts on the air near the inlet of the clearance with the rotation of the impeller, and the effect of suppressing the inflow of the clearance flow can be further enhanced.

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  • General Engineering & Computer Science (AREA)
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PCT/JP2020/030031 2020-08-05 2020-08-05 遠心圧縮機のインペラ及び遠心圧縮機 Ceased WO2022029932A1 (ja)

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PCT/JP2020/030031 WO2022029932A1 (ja) 2020-08-05 2020-08-05 遠心圧縮機のインペラ及び遠心圧縮機
JP2022541018A JPWO2022029932A1 (https=) 2020-08-05 2020-08-05
US18/015,816 US12435730B2 (en) 2020-08-05 2020-08-05 Impeller of centrifugal compressor and centrifugal compressor
CN202080103036.6A CN115989370A (zh) 2020-08-05 2020-08-05 离心压缩机的叶轮以及离心压缩机
DE112020007258.4T DE112020007258T5 (de) 2020-08-05 2020-08-05 Laufrad eines zentrifugalverdichters und zentrifugalverdichter
JP2024048841A JP7654133B2 (ja) 2020-08-05 2024-03-26 遠心圧縮機のインペラ及び遠心圧縮機

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US12560176B1 (en) * 2025-01-23 2026-02-24 Garrett Transportation I Inc. Extended wheel tip and back-disk cavity

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US20230258197A1 (en) 2023-08-17
US12435730B2 (en) 2025-10-07
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