US20260043418A1 - Rotation device - Google Patents

Rotation device

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Publication number
US20260043418A1
US20260043418A1 US19/359,235 US202519359235A US2026043418A1 US 20260043418 A1 US20260043418 A1 US 20260043418A1 US 202519359235 A US202519359235 A US 202519359235A US 2026043418 A1 US2026043418 A1 US 2026043418A1
Authority
US
United States
Prior art keywords
wall surface
vanes
turbine
vane plate
impeller
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.)
Pending
Application number
US19/359,235
Other languages
English (en)
Inventor
Ryosuke Miyao
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.)
IHI Corp
Original Assignee
IHI Corp
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 IHI Corp filed Critical IHI Corp
Publication of US20260043418A1 publication Critical patent/US20260043418A1/en
Pending 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
    • F04D29/40—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
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide 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
    • F04D29/26—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

Definitions

  • the present disclosure relates to a rotation device.
  • a rotation device such as a turbine or a centrifugal compressor may include vanes that are arranged radially outside an impeller.
  • Patent Literature 1 discloses fixed blades that are arranged radially outside a turbine impeller.
  • the fixed blades are arranged in a passage between a bearing housing and a turbine housing.
  • the fixed blades include a plurality of blade bodies and an annular movable member.
  • the plurality of blade bodies are fixed to a front surface of the movable member. Ends of the blade bodies face the turbine housing.
  • a disc spring is arranged in a space between a rear surface of the movable member and the bearing housing. The disc spring presses the blade bodies against the turbine housing. This configuration suppresses clearance between the blade bodies and the turbine housing. As such, decrease in turbine efficiency is curbed.
  • the present disclosure aims to provide a rotation device that can suppress clearance between vanes and a housing.
  • a rotation device includes an impeller, a plurality of vanes that are arranged along a circumferential direction in an area radially outside the impeller and that protrude in an axial direction, a first wall surface that faces a protruding end of each of the plurality of vanes in the axial direction, and an inclined surface that is formed on at least one of the first wall surface and the protruding ends of the plurality of vanes and that is inclined with respect to a radial direction of the impeller.
  • the rotation device may include an annular vane plate that is arranged radially outside the impeller and that includes a first surface facing the axial direction and a second surface opposite to the first surface, the plurality of vanes protruding from the first surface of the vane plate, a second wall surface that faces the first wall surface across the vane plate and the plurality of vanes in the axial direction, the second wall surface facing the second surface of the vane plate, and an elastic body that is arranged between the second surface of the vane plate and the second wall surface and that presses the vane plate and the plurality of vanes toward the first wall surface.
  • the inclined surface may be formed on the first wall surface, and the first wall surface may include a discontinuous portion that is positioned radially inside the protruding ends of the plurality of vanes and that protrudes from the inclined surface.
  • FIG. 1 is a schematic cross-sectional view of a turbocharger including a turbine according to a first embodiment.
  • FIG. 2 is a schematic enlarged cross-sectional view showing area A in FIG. 1 .
  • FIG. 3 is a schematic enlarged cross-sectional view showing a deformation mode of a vane plate of the turbine without an inclined surface, when the vane plate is heated.
  • FIG. 4 is a schematic enlarged cross-sectional view showing a deformation mode of the vane plate of the turbine without the inclined surface, when the vane plate is cooled.
  • FIG. 5 is a schematic enlarged cross-sectional view showing behavior of a vane when the vane plate in FIG. 2 is heated.
  • FIG. 6 is a schematic enlarged cross-sectional view of a turbine according to a second embodiment.
  • FIG. 7 is a schematic enlarged cross-sectional view of a turbine according to a third embodiment.
  • FIG. 8 is a schematic enlarged cross-sectional view of a turbine according to a fourth embodiment.
  • FIG. 9 is a schematic enlarged cross-sectional view of a turbine according to a fifth embodiment.
  • FIG. 1 is a schematic cross-sectional view of a turbocharger 100 including a turbine T 1 according to a first embodiment.
  • the turbine T 1 according to the present embodiment is applied to the turbocharger 100 .
  • the turbine T 1 may be applied to equipment other than the turbocharger 100 , or may be a standalone unit.
  • the turbocharger 100 includes a housing 1 , a shaft 2 , a turbine impeller 3 , and a compressor impeller 4 .
  • the housing 1 includes a bearing housing 5 , a turbine housing 6 , and a compressor housing 7 .
  • one end of the bearing housing 5 is connected to the turbine housing 6 by a fastener such as a G-coupling.
  • the other end of the bearing housing 5 is connected to the compressor housing 7 by a fastener such as bolts.
  • the bearing housing 5 includes a bearing hole 5 a .
  • the bearing hole 5 a extends in the axial direction within the bearing housing 5 .
  • the bearing hole 5 a accommodates a bearing B.
  • the bearing B rotatably supports the shaft 2 .
  • a pair of rolling bearings is used as the bearing B.
  • other radial bearings such as a full-floating bearing or a semi-floating bearing, may be used as the bearing B.
  • the turbine impeller 3 is provided on a first end of the shaft 2 in the axial direction.
  • the turbine impeller 3 rotates integrally with the shaft 2 .
  • the turbine housing 6 accommodates the turbine impeller 3 in a rotatable manner.
  • the compressor impeller 4 is provided at a second end that is opposite to the first end in the axial direction in the shaft 2 .
  • the compressor impeller 4 rotates integrally with the shaft 2 .
  • the compressor housing 7 accommodates the compressor impeller 4 in a rotatable manner.
  • the compressor housing 7 includes an inlet 71 at an end that is opposite to the bearing housing 5 in the axial direction.
  • the inlet 71 is connected to an air cleaner (not shown).
  • the bearing housing 5 and the compressor housing 7 define a diffuser flow path 72 therebetween.
  • the diffuser flow path 72 has an annular shape.
  • the diffuser flow path 72 is positioned radially outside the compressor impeller 4 .
  • the diffuser flow path 72 is fluidly connected to the inlet 71 via the compressor impeller 4 .
  • the compressor housing 7 includes a compressor scroll flow path 73 .
  • the compressor scroll flow path 73 is positioned radially outside the diffuser flow path 72 .
  • the compressor scroll flow path 73 is connected to the diffuser flow path 72 .
  • the compressor scroll flow path 73 is fluidly connected to an intake port of an engine (not shown).
  • the turbine housing 6 includes an outlet 61 at an end that is opposite to the bearing housing 5 in the axial direction.
  • the outlet 61 is connected to an exhaust gas purifier (not shown).
  • the turbine housing 6 includes a connecting flow path 62 .
  • the connecting flow path 62 has an annular shape.
  • the connecting flow path 62 is positioned radially outside the turbine impeller 3 .
  • the connecting flow path 62 is fluidly connected to the outlet 61 via the turbine impeller 3 .
  • a plurality of vanes V are arranged in the connecting flow path 62 .
  • the plurality of vanes V are arranged along the circumferential direction in an area radially outside the turbine impeller 3 . The vanes V will be described in detail below.
  • the turbine housing 6 includes a turbine scroll flow path 63 .
  • the turbine scroll flow path 63 is positioned radially outside the connecting flow path 62 .
  • the turbine scroll flow path 63 is fluidly connected to the connecting flow path 62 .
  • the turbine scroll flow path 63 is connected to a gas inlet opening (not shown).
  • the gas inlet opening receives exhaust gas discharged from an exhaust manifold (not shown) of the engine.
  • the exhaust gas is directed from the gas inlet opening into the turbine scroll flow path 63 , and further directed through the connecting flow path 62 and the turbine impeller 3 to the outlet 61 .
  • the exhaust gas rotates the turbine impeller 3 while passing therethrough. Rotational force of the turbine impeller 3 is transmitted to the compressor impeller 4 via the shaft 2 .
  • the compressor impeller 4 rotates, the air is pressurized as described above. As such, the pressurized air is directed to the intake port of the engine.
  • FIG. 2 is a schematic enlarged cross-sectional view showing area A in FIG. 1 .
  • FIG. 2 shows a vane plate 8 and the vane V without thermal deformation. Note that in the drawings of the present disclosure, an angle of an inclined surface S (described later) with respect to the radial direction is exaggerated for better understanding.
  • the turbine T 1 includes the vane plate 8 and an elastic body 9 .
  • the vane plate 8 has an annular shape.
  • the vane plate 8 is arranged radially outside the turbine impeller 3 .
  • the vane plate 8 is arranged concentrically with the turbine impeller 3 .
  • the turbine housing 6 includes a groove 64 for arranging the vane plate 8 .
  • the vane plate 8 is arranged in the groove 64 .
  • the vane plate 8 includes a first surface 81 and a second surface 82 that face the axial direction.
  • the second surface 82 is positioned opposite to the first surface 81 .
  • the first surface 81 and the second surface 82 expand in the radial direction.
  • the first surface 81 and the second surface 82 have an annular shape.
  • the housing 1 includes a first wall surface W 1 and a second wall surface W 2 facing each other across the vane plate 8 and the vanes V in the axial direction.
  • the first wall surface W 1 faces protruding ends Va of the vanes V in the axial direction.
  • the first wall surface W 1 is a surface that is far away from the outlet 61 , among a pair of surfaces that face each other across the connecting flow path 62 in the axial direction.
  • the first wall surface W 1 is formed in the bearing housing 5 .
  • the second wall surface W 2 faces the second surface 82 of the vane plate 8 in the axial direction.
  • the second wall surface W 2 is a surface that is closer to the outlet 61 , among the pair of surfaces that face each other across the connecting flow path 62 in the axial direction.
  • the second wall surface W 2 is formed in the turbine housing 6 .
  • the second wall surface W 2 is a surface that defines the groove 64 .
  • the second wall surface W 2 defines the groove 64 in the axial direction.
  • the first wall surface W 1 and the second wall surface W 2 expand in the radial direction.
  • the first wall surface W 1 and the second wall surface W 2 have an annular shape.
  • the connecting flow path 62 is defined by the first wall surface W 1 and the first surface 81 of the vane plate 8 .
  • the vane V protrudes in the axial direction from the first surface 81 of the vane plate 8 .
  • the vane V is fixed to the first surface 81 .
  • the vane V may be formed monolithically with the vane plate 8 .
  • the vane V may be formed separately from the vane plate 8 and connected to the vane plate 8 .
  • the protruding end Va of the vane V faces the first wall surface W 1 .
  • the elastic body 9 is arranged between the second surface 82 of the vane plate 8 and the second wall surface W 2 of the turbine housing 6 .
  • the elastic body 9 is arranged in the groove 64 .
  • the elastic body 9 presses the vane plate 8 and the vanes V toward the first wall surface W 1 . Accordingly, the protruding ends Va of the vanes V are pressed against the first wall surface W 1 .
  • the elastic body 9 is a disc spring.
  • other elastic bodies, such as a plurality of coil springs may be used as the elastic body 9 .
  • the elastic body 9 has a truncated conical shape.
  • the elastic body 9 is arranged concentrically with the turbine impeller 3 .
  • FIG. 3 is a schematic enlarged cross-sectional view showing a deformation mode of the vane plate 8 of the turbine T without an inclined surface S, when the vane plate 8 is heated.
  • the turbine T in FIG. 3 and the following FIG. 4 does not include the inclined surface S (described later).
  • the deformation of the vane plate 8 is exaggerated for better understanding.
  • the first surface 81 which faces the connecting flow path 62 , in the vane plate 8 becomes hotter than the opposite second surface 82 . Accordingly, the first surface 81 expands radially outward with respect to the second surface 82 .
  • the vanes V tilt together with the vane plate 8 . In this deformation mode, radially outermost parts of the protruding ends Va of the vanes V move away from the first wall surface W 1 , creating clearance between the vanes V and the first wall surface W 1 . Accordingly, efficiency of the turbine T 1 decreases.
  • FIG. 4 is a schematic enlarged cross-sectional view showing a deformation mode of the vane plate 8 of the turbine T without the inclined surface S, when the vane plate 8 is cooled.
  • the first surface 81 which faces the connecting flow path 62 , in the vane plate 8 becomes colder than the opposite second surface 82 . Accordingly, the first surface 81 contracts radially inward with respect to the second surface 82 .
  • the vanes V tilt together with the vane plate 8 . In this deformation mode, radially innermost parts of the protruding ends Va of the vanes V move away from the first wall surface W 1 , creating clearance between the vanes V and the first wall surface W 1 . Accordingly, the efficiency of the turbine T 1 decreases.
  • an inclined surface S is formed on the first wall surface W 1 to suppress the clearance formed by the deformation of the vane plate 8 described above.
  • the inclined surface S is formed in a direction that suppresses the clearance between the vanes V and the first wall surface W 1 when the vane plate 8 is heated (the situation shown in FIG. 3 ).
  • the inclined surface S is formed on the first wall surface W 1 so as to be inclined in a direction in which the inclined surface is closer to the radially outermost parts of the protruding ends Va, when there is no thermal deformation.
  • the inclined surface S in a cross-section that is parallel to the central axis and that includes the central axis, the inclined surface S has a straight shape.
  • the inclined surface S is formed so as to overlap the entire length of the protruding end Va in the radial direction.
  • an angle of the inclined surface S with respect to the radial direction may be determined based on the amount of deformation of the vane plate 8 when the vane plate 8 is heated under a predetermined operating condition.
  • the amount of deformation of the vane plate 8 may be obtained by analysis or experiment.
  • FIG. 5 is a schematic enlarged cross-sectional view showing behavior of the vane V when the vane plate 8 in FIG. 2 is heated. In FIG. 5 as well, the deformation of the vane plate 8 is exaggerated for better understanding.
  • the vane plate 8 when the vane plate 8 is heated, the vane plate 8 deforms such that the radially outermost parts of the protruding ends Va of the vanes V move away from the first wall surface W 1 .
  • the inclined surface S is formed on the first wall surface W 1 so as to be inclined in the direction in which the inclined surface is closer to the radially outermost parts of the protruding ends Va.
  • the protruding ends Va of the vanes V move into positions parallel to the inclined surface S.
  • contact area between the protruding ends Va and the inclined surface S increases, thereby suppressing the clearance between the vanes V and the first wall surface W 1 .
  • the inclined surface S may be formed in a direction that suppresses the clearance between the vanes V and the first wall surface W 1 when the vane plate 8 is cooled (the situation shown in FIG. 4 ).
  • the inclined surface S is formed on the first wall surface W 1 so as to be inclined in a direction in which the inclined surface is far away from the radially outermost parts of the protruding ends Va.
  • the turbine T 1 includes the turbine impeller 3 , the plurality of vanes V that are arranged along the circumferential direction in the area radially outside the turbine impeller 3 and that protrude in the axial direction, the first wall surface W 1 that faces the protruding end Va of each of the plurality of vanes V in the axial direction, and the inclined surface S that is formed on the first wall surface W 1 and that is inclined with respect to the radial direction.
  • the protruding end Va of the vane V moves to a position parallel to the inclined surface S.
  • contact area between the protruding ends Va and the inclined surface S increases, thereby suppressing the clearance between the vane V and the first wall surface W 1 .
  • the turbine T 1 includes the annular vane plate 8 that is arranged radially outside the turbine impeller 3 and that includes the first surface 81 facing the axial direction and the second surface 82 opposite to the first surface 81 , wherein the plurality of vanes V protrude from the first surface 81 of the vane plate 8 , the second wall surface W 2 that faces the first wall surface W 1 across the vane plate 8 and the plurality of vanes V in the axial direction, wherein the second wall surface W 2 faces the second surface 82 of the vane plate 8 , and the elastic body 9 that is arranged between the second surface 82 of the vane plate 8 and the second wall surface W 2 and that presses the vane plate 8 and the vanes V toward the first wall surface W 1 .
  • the elastic body 9 can firmly press the protruding ends Va of the vanes V against the inclined surface S.
  • FIG. 6 is a schematic enlarged cross-sectional view of a turbine T 2 according to a second embodiment.
  • the vane plate 8 and the vane V before thermal deformation are shown in solid lines, while those after thermal deformation are shown in dashed lines.
  • the deformation of the vane plate 8 is exaggerated for better understanding.
  • the turbine T 2 of the present embodiment differs from the turbine T 1 of the first embodiment in that the inclined surfaces S are formed on the protruding ends Va of the vanes V instead of on the first wall surface W 1 .
  • the turbine T 2 may be the same as the turbine T 1 .
  • the inclined surface S is formed in a direction that suppresses the clearance between the vane V and the first wall surface W 1 when the vane plate 8 is heated.
  • the inclined surface S is formed on the protruding end Va such that the radially outermost part of the protruding end Va protrudes axially toward the first wall surface W 1 relative to the radially innermost part.
  • the inclined surface S is formed along the entire length of the protruding end Va in the radial direction. In another embodiment, the inclined surface S may only be formed on a part of the protruding end Va in the radial direction.
  • the inclined surface S may only be formed on a radially inner part of the protruding end Va.
  • the rest of the protruding end Va may be parallel or substantially parallel to the first wall surface W 1 in a state without thermal deformation.
  • FIG. 7 is a schematic enlarged cross-sectional view of a turbine T 3 according to a third embodiment.
  • the turbine T 3 according to the present embodiment differs from the turbine T 1 according to the first embodiment in that the arrangement of the vane plate 8 and the vanes V is inverted in the axial direction compared to FIGS. 2 to 6 , and the inclined surface S is formed in the turbine housing 6 instead of the bearing housing 5 . Accordingly, in the present embodiment, a groove 51 for accommodating the vane plate 8 and the elastic body 9 is formed in the bearing housing 5 .
  • the turbine T 3 may be the same as the turbine T 1 .
  • the first wall surface W 1 facing the protruding ends Va of the vanes V is a surface closer to the outlet 61 , among the pair of surfaces facing each other across the connecting flow path 62 in the axial direction.
  • the first wall surface W 1 is formed in the turbine housing 6 .
  • the second wall surface W 2 facing the second surface 82 of the vane plate 8 is a surface far away from the outlet 61 , among the pair of surfaces facing each other across the connecting flow path 62 in the axial direction.
  • the second wall surface W 2 is formed in the bearing housing 5 .
  • the second wall surface W 2 is a surface defining the groove 51 .
  • the second wall surface W 2 defines the groove 51 in the axial direction.
  • the inclined surface S is formed in a direction suppressing the clearance between the vanes V and the first wall surface W 1 when the vane plate 8 is heated.
  • the hot exhaust gas from the engine flows through the connecting flow path 62 .
  • the first surface 81 of the vane plate 8 which faces the connecting flow path 62 , becomes hotter than the opposite second surface 82 . Accordingly, as shown by the vane plate 8 in the dashed lines, the first surface 81 expands radially outward with respect to the second surface 82 .
  • the inclined surface S is formed on the first wall surface W 1 so as to be inclined in a direction in which the inclined surface is closer to the radially outermost parts of the protruding ends Va of the vanes V, in a state without thermal deformation.
  • the inclined surface S is formed so as to overlap the entire length of the protruding end Va in the radial direction.
  • the inclined surface S may be formed so as to be inclined in a direction suppressing the clearance between the vanes V and the first wall surface W 1 when the vane plate 8 is cooled.
  • the inclined surface S is formed on the first wall surface W 1 so as to be inclined in a direction in which the inclined surface is far away from the radially outermost parts of the protruding ends Va of the vanes V, in a state without thermal deformation.
  • the turbine T 3 when the vane plate 8 is heated, the protruding ends Va of the vanes V move to positions parallel to the inclined surface S. As a result, contact area between the protruding ends Va and the inclined surface S increases, suppressing the clearance between the vanes V and the first wall surface W 1 . As such, the turbine T 3 achieves effects substantially similar to those of the turbine T 1 of the first embodiment.
  • FIG. 9 is a schematic enlarged cross-sectional view of a turbine T 5 according to a fifth embodiment.
  • the turbine T 5 of the present embodiment differs from the turbine T 3 of the third embodiment in that a discontinuous portion 65 is formed on the first wall surface W 1 .
  • the turbine T 5 may be the same as the turbine T 3 . Note that a height in the axial direction of the discontinuous portion 65 is exaggerated.
  • the discontinuous portion 65 protrudes substantially in the axial direction from the inclined surface S.
  • the discontinuous portion 65 is positioned radially inside the protruding ends Va of the vanes V.
  • the discontinuous portion 65 may be continuous in the circumferential direction.
  • the discontinuous portion 65 is smoothly connected to and continuous with the shroud 66 .
  • the turbine T 5 achieves effects substantially similar to those of the turbine T 3 according to the third embodiment.
  • the inclined surface S is formed on the first wall surface W 1 , and the first wall surface W 1 includes the discontinuous portion 65 that is positioned radially inside the protruding ends Va of the vanes V and that protrudes from the inclined surface S. This configuration allows the vanes V to be positioned deeper relative to the discontinuous portion 65 , thereby reducing the clearance at the protruding ends Va of the vanes V.
  • the rotation devices are the turbine T 1 , T 2 , T 3 , T 4 and T 5 , and the inclined surface S is formed on the vanes V arranged in the connecting flow path 62 or on the wall surface defining the connecting flow path 62 .
  • the rotation device may be the centrifugal compressor C, and the inclined surface S may be formed on diffuser vanes arranged in the diffuser flow path 72 or on a wall surface defining the diffuser flow path 72 .
  • the rotation devices include the elastic body 9 .
  • the rotation device may not include the elastic body 9 .
  • the rotation device may not include the vane plate 8 , and the vanes V may protrude directly from a wall defining the flow path in which the vanes V are arranged.
  • the inclined surface S is formed on either the first wall surface W 1 or the protruding ends Va of the vanes V.
  • the inclined surface S may be formed on both the first wall surface W 1 and the protruding ends Va of the vanes V.
  • angles of the inclined surfaces S may be determined such that the sum of an absolute value of an angle with respect to the radial direction of the inclined surface S formed on the first wall surface W 1 and an absolute value of an angle with respect to the radial direction of the inclined surface S formed on the protruding end Va corresponds to the amount of deformation of the vane plate 8 .
  • the inclined surface S formed on the first wall surface W 1 and the inclined surface S formed on the protruding ends Va are inclined in opposite directions with respect to the radial direction.
  • the inclined surface S may be formed on the first wall surface W 1 such that its angle is half that shown in FIG. 2
  • the inclined surface S may be formed on the protruding ends Va such that its angle is half that shown in FIG. 6 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
US19/359,235 2023-06-22 2025-10-15 Rotation device Pending US20260043418A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2023102413 2023-06-22
JP2023-102413 2023-06-22
PCT/JP2024/008777 WO2024262099A1 (ja) 2023-06-22 2024-03-07 回転装置

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2024/008777 Continuation WO2024262099A1 (ja) 2023-06-22 2024-03-07 回転装置

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US20260043418A1 true US20260043418A1 (en) 2026-02-12

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US19/359,235 Pending US20260043418A1 (en) 2023-06-22 2025-10-15 Rotation device

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US (1) US20260043418A1 (https=)
JP (1) JPWO2024262099A1 (https=)
CN (1) CN121013940A (https=)
DE (1) DE112024001434T5 (https=)
WO (1) WO2024262099A1 (https=)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6361545U (https=) * 1986-10-09 1988-04-23
JP3153409B2 (ja) * 1994-03-18 2001-04-09 株式会社日立製作所 遠心圧縮機の製作方法
US7150151B2 (en) * 2002-11-19 2006-12-19 Cummins Inc. Method of controlling the exhaust gas temperature for after-treatment systems on a diesel engine using a variable geometry turbine
BE1017777A3 (nl) * 2007-10-09 2009-06-02 Atlas Copco Airpower Nv Verbeterde turbocompressor.
EP2617960B1 (en) * 2010-09-13 2020-03-18 IHI Corporation Fixed vane-type turbo charger
US10385765B2 (en) * 2012-12-27 2019-08-20 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Variable geometry turbocharger
WO2016031017A1 (ja) * 2014-08-28 2016-03-03 三菱重工業株式会社 膨張タービン及びターボチャージャ

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WO2024262099A1 (ja) 2024-12-26
JPWO2024262099A1 (https=) 2024-12-26
CN121013940A (zh) 2025-11-25

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