WO2016059866A1 - ラビリンスシール、遠心圧縮機及び過給機 - Google Patents

ラビリンスシール、遠心圧縮機及び過給機 Download PDF

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Publication number
WO2016059866A1
WO2016059866A1 PCT/JP2015/073128 JP2015073128W WO2016059866A1 WO 2016059866 A1 WO2016059866 A1 WO 2016059866A1 JP 2015073128 W JP2015073128 W JP 2015073128W WO 2016059866 A1 WO2016059866 A1 WO 2016059866A1
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WO
WIPO (PCT)
Prior art keywords
impeller
convex portion
labyrinth seal
stationary member
centrifugal compressor
Prior art date
Application number
PCT/JP2015/073128
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
平野　雄一郎
Original Assignee
三菱重工業株式会社
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 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Priority to KR1020167032861A priority Critical patent/KR101855610B1/ko
Priority to CN201580039997.4A priority patent/CN108026938B/zh
Publication of WO2016059866A1 publication Critical patent/WO2016059866A1/ja

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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
    • F04D29/08—Sealings
    • F04D29/083—Sealings 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • 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
    • F04D29/08—Sealings
    • 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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/447—Labyrinth packings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved

Definitions

  • the present disclosure relates to a radially extending labyrinth seal of a centrifugal compressor, and a centrifugal compressor and a turbocharger provided with the same.
  • a centrifugal compressor of a supercharger is configured to pressurize air flowing into the centrifugal compressor by an impeller.
  • the air pressurized by the centrifugal compressor is led to the engine cylinder and burns, and the high-temperature, high-pressure combustion gas generated by the combustion passes through the turbine of the turbocharger to rotate the shaft connected to the turbine,
  • the centrifugal compressor provided on the other end side of is driven.
  • a labyrinth seal may be provided between a rotating member including an impeller and a stationary member including a bearing casing.
  • Patent Document 1 describes a labyrinth seal disposed on an impeller back wall of a centrifugal compressor of an exhaust gas turbine supercharger. In this configuration, the leakage flow of the compressed fluid compressed when passing through the impeller via the rear side of the impeller is suppressed.
  • the labyrinth seal has a configuration in which narrow areas and fluid expansion areas are alternately provided. Thereby, the amount of fluid leakage from the centrifugal compressor can be suppressed. In addition, since the fluid leaking out of the labyrinth seal is gradually reduced in pressure, the pressure on the back of the impeller can be reduced.
  • the fluid force acting on the turbine of the supercharger may exert a thrust from the turbine side to the compressor side, and in this case, it is necessary to reduce the pressure on the back of the impeller It is desirable from the viewpoint of maintaining the thrust balance properly.
  • the temperature of the leak flow rises due to fluid friction in the narrow flow passage, and the amount of heat transfer to the impeller increases.
  • the impeller is a component on which high centrifugal stress acts by rotation, and when the temperature is increased by the amount of heat transfer, the possibility of breakage due to creep increases. Therefore, there is a demand for a labyrinth seal having high sealing performance and small heat transfer to the impeller.
  • a vortex chamber is provided on the downstream side of the throttling point (narrow area), and a part of the fluid passing through the throttling point is vortexed in the vortex chamber and the remaining fluid is It is supposed to join the Thereby, the heat input to the impeller side is suppressed to a certain extent.
  • At least one embodiment of the present invention provides a labyrinth seal capable of reducing the amount of heat input from the fluid passing through the labyrinth seal to the impeller, and a centrifugal compressor and a turbocharger provided with the same.
  • the purpose is to
  • a labyrinth seal for use in a centrifugal compressor comprising: an impeller through which fluid flows in a radial direction; and a stationary member provided on the rear side of the impeller, A plurality of first convex portions respectively provided along the circumferential direction at a plurality of radial positions on the rear surface of the impeller; And a plurality of second convex portions provided along the circumferential direction on the stationary member such that a tip end portion intrudes between the adjacent first convex portions.
  • a labyrinth-like flow path including a plurality of minimum clearances formed between the first projection and the second projection is in the radial direction.
  • the stationary member is positioned upstream of the minimum clearance portion in the flow direction of the leak flow passing through the minimum clearance portion formed between the first convex portion and the second convex portion, and the minimum clearance portion
  • the back side of the impeller is located on the downstream side of the wheel.
  • one of the causes of heat input to the impeller in the conventional labyrinth seal is that the fluid having a high flow velocity that has passed through the minimum clearance portion collides with the wall surface of the stationary member and It has been found that when flowing, fluid in the vicinity of the wall surface of the stationary member, which has a high relative temperature as viewed from the impeller side, is transported to the impeller side.
  • the configuration of the above (1) is conceived based on this finding by the present inventors, and the stationary member is located upstream of the minimum clearance portion in the flow direction of the leakage flow passing through the minimum clearance portion. And, the back of the impeller is positioned downstream of the minimum clearance portion.
  • the fluid accelerated when passing through the minimum clearance portion flows along the back of the impeller after colliding with the back of the impeller instead of the stationary member side. Therefore, it is possible to suppress a situation in which the fluid near the wall surface of the stationary member having a high relative total temperature as viewed from the impeller side is accompanied by the fluid having the high flow velocity which has passed through the minimum clearance portion and transported to the impeller side. Therefore, the amount of heat input from the fluid passing through the labyrinth seal to the impeller can be reduced, and the temperature rise of the impeller can be suppressed.
  • the labyrinth seal seals the leakage flow directed radially inward between the rear surface of the impeller and the stationary member.
  • the minimum clearance portion is formed between the tip of the first convex portion or the radially inner surface of the first convex portion and the second convex portion.
  • a seal sword tip is provided at the tip of the second convex portion, and the minimum clearance portion is an inner side in the radial direction of the first convex portion. And the seal tip of the second protrusion.
  • the seal blade tip is provided on the second convex portion on the stationary member side, the wall surface of the stationary member from the flow of fluid passing through the minimal clearance portion on the downstream side of the minimal clearance portion 2) The wall surface of the convex part is moving away. For this reason, it is possible to effectively suppress a situation in which the flow velocity passing through the minimum clearance portion is accompanied by the high fluid and transferred to the impeller side. Therefore, the amount of heat input from the fluid passing through the labyrinth seal to the impeller can be effectively reduced, and the temperature rise of the impeller can be further suppressed.
  • the radially inner surface of the first convex portion forms a sealing surface extending along the axial direction of the centrifugal compressor.
  • the second convex portion is provided so as to project from the stationary member toward the rear surface side of the impeller and the outer side in the radial direction.
  • a seal sword tip is provided at the tip of the first convex portion, and the minimum clearance portion is the seal sword tip of the first convex portion. And the radial outer surface of the second projection.
  • the fluid that has passed through the minimum clearance formed between the seal tip of the first projection on the impeller side and the radially outer surface of the second projection of the stationary member Can be directed to the back of the impeller.
  • the amount of heat input from the fluid passing through the labyrinth seal to the impeller can be reduced, and the temperature rise of the impeller can be suppressed.
  • a seal sword tip is provided at the tip of the first convex portion, the minimum clearance portion is the seal sword tip of the first convex portion, It is formed between the radially outer surface of the second convex portion.
  • the clearance width direction of the minimum clearance portion is along the radial direction, the clearance width of the minimum clearance portion is hardly influenced even if the impeller is shifted in the axial direction. Therefore, the seal performance deterioration due to the displacement of the axial direction of the impeller can be suppressed.
  • a centrifugal compressor according to at least one embodiment of the present invention, An impeller through which fluid flows in a radial direction; A stationary member provided on the back side of the impeller; The labyrinth seal according to any one of the above (1) to (6) may be provided between the rear surface of the impeller and the stationary member. According to the structure of said (7), the heat gain to the impeller from the fluid which passes a labyrinth seal can be reduced, and the temperature rise of an impeller can be suppressed. Therefore, it is possible to suppress a decrease in creep life caused by the high temperature of the impeller, and to realize a high pressure ratio of the centrifugal compressor.
  • a turbocharger configured to include the centrifugal compressor according to the configuration of the above (7), for compressing intake air to an internal combustion engine; And a turbine configured to be driven by the exhaust gas of an internal combustion engine to drive the compressor.
  • the amount of heat input from the fluid passing through the labyrinth seal to the impeller can be reduced, and the temperature rise of the impeller can be suppressed. Therefore, the fall of the creep life resulting from temperature rising of an impeller can be suppressed.
  • the labyrinth seal 10 is specifically applied to the centrifugal compressor 3 of the supercharger 1.
  • the application destination of the labyrinth seal 10 is not limited to the illustrated centrifugal compressor 3 and may be used for other types of centrifugal compressors.
  • FIG. 1 is a cross-sectional view (longitudinal cross-sectional view) showing an entire configuration of a turbocharger 1 according to an embodiment, and shows an exhaust turbine turbocharger for marine use as an example.
  • a turbocharger 1 according to an embodiment is an axial flow turbine (hereinafter referred to as a turbine) 2 configured to be driven by exhaust gas from an internal combustion engine (for example, a marine diesel engine).
  • a centrifugal compressor 3 driven by the turbine 2 and configured to compress intake air supplied to the internal combustion engine.
  • a bearing stand 4 is provided between the turbine 2 and the centrifugal compressor 3.
  • the turbine casing 21 of the turbine 2, the bearing stand 4, and the compressor casing 31 of the centrifugal compressor 3 are integrally configured by connection means such as a fastening member (for example, a bolt).
  • a thrust bearing 41 and radial bearings 42 and 43 are accommodated in the bearing stand 4.
  • the rotor 5 is rotatably supported by the thrust bearing 41 and the radial bearings 42 and 43.
  • the moving blade 24 of the turbine 2 is connected to one end side of the rotor 5, and the impeller 32 of the centrifugal compressor 3 is connected to the other end side.
  • the turbine 2 is configured to be driven by the exhaust gas of an internal combustion engine (not shown) to drive the centrifugal compressor 3.
  • the turbine 2 is provided on the outer peripheral side of the rotor 5 (actually, one end side of the rotor 5), a plurality of moving blades 24 implanted on the outer periphery of the rotor 5, the rotor 5 and the moving blades 24.
  • a turbine casing 21 a turbine casing 21.
  • An inlet passage 27 through which exhaust gas flows, an axial passage 28 and an outlet passage 29 are sequentially formed in the flow direction of the exhaust gas by the stationary system member including the turbine casing 21.
  • An axial passage 28 is located between the inlet passage 27 and the outlet passage 29 and extends along the rotational axis O of the rotor 5.
  • a moving blade 24 is provided in the axial passage. Further, a turbine nozzle (static blade) 25 is provided on the inlet side of the moving blade 24.
  • exhaust gas from the internal combustion engine is introduced from the inlet passage 27, and the rotor 5 coupled to the moving blades 24 is rotated by the exhaust gas flowing through the axial passage 28. Exhaust gas having passed through the moving blades 24 is discharged through the outlet passage 29.
  • the centrifugal compressor 3 is configured to compress intake air to an internal combustion engine (not shown), and the rotor 5 (actually, the other end side of the rotor 5) and an impeller 32 provided on the outer periphery of the rotor 5 , And a compressor casing 31 provided on the outer peripheral side of the rotor 5 and the impeller 32.
  • An air inlet 37 and an outlet scroll 38 are formed by a stationary system member including the compressor casing 31. Between the air inlet 37 and the outlet scroll 38, an impeller 32 and a diffuser 36 are disposed in order in the air flow direction (radial direction of the centrifugal compressor 3).
  • the impeller 32 has a disk-like hub 33 fixed to the outer periphery of the rotor 5 and a plurality of vanes 34 fixed to the hub 33 and arranged radially with respect to the hub 33.
  • fluid here, air
  • a multistage centrifugal compressor may be sufficient.
  • the air introduced from the air inlet 37 is pressurized when passing through the impeller 32, the diffuser 36 and the outlet scroll 38.
  • Most of the air compressed by the centrifugal compressor 3 is led to the engine cylinder of the internal combustion engine and performs the work of pushing down the piston in the combustion / expansion stroke.
  • the high-temperature and high-pressure combustion gas generated here is sent to the turbine 2, and the turbine 2 drives the centrifugal compressor 3 coaxially.
  • a lubricating oil supply passage 44 is formed in the bearing stand 4.
  • One end of the lubricating oil supply passage 44 is connected to a lubricating oil supply unit (for example, an oil tank and an oil pump).
  • the other end of the lubricating oil supply passage 44 is branched into a plurality of branches, and the branched ends are connected to the thrust bearing 41 and the radial bearings 42 and 43, respectively.
  • the lubricating oil is supplied to the thrust bearing 41 and the radial bearings 42 and 43 through the lubricating oil supply passage 44, respectively.
  • a labyrinth seal 10 is provided between the centrifugal compressor 3 and the bearing stand 4.
  • the labyrinth seal 10 is configured to seal between the impeller 32 and the stationary member 46 of the bearing stand 4 facing the impeller 32.
  • the labyrinth seal 10 mainly prevents air containing lubricating oil in the bearing stand 4 from mixing in with the compressed air of the centrifugal compressor 3.
  • the internal space of the bearing stand 4 may be filled with mist in which the lubricating oil is scattered.
  • a part of the air discharged from the impeller 32 may go around to the back and leak into the internal space of the bearing stand 4.
  • the back surface of the impeller 32 has a high pressure, and in the direction of the rotation axis O of the rotor 5, a high thrust force acting on the impeller 32 from the back surface side to the inlet side of the impeller 32 acts.
  • This high thrust force may lead to an increase in the size of the thrust bearing 41 and high friction loss. Therefore, also from the viewpoint of thrust balance, it may be desirable to reduce the pressure on the rear surface of the impeller 32 by the labyrinth seal 10.
  • FIG. 2A is a view showing the labyrinth seal 10 according to one embodiment, and is a longitudinal cross-sectional view of the periphery of the back surface of the impeller 32.
  • FIG. 2B is a plan view of the impeller 32 shown in FIG. 2A as viewed from the rear surface (direction A) 35 side.
  • FIG. 3 is a view showing the labyrinth seal 10 according to one embodiment, and is a schematic cross-sectional view of the impeller 32 and the stationary member 46.
  • FIG. FIG.4 and FIG.5 is an expanded sectional view of the labyrinth seal 10 in each embodiment.
  • the labyrinth seal 10 includes an impeller 32 through which fluid (for example, air) flows in a radial direction, and a stationary member provided on the back surface 35 of the impeller 32. And 46 are used in a centrifugal compressor.
  • the labyrinth seal 10 seals between the rear surface 35 of the impeller 32 and the stationary member 46 in the radial direction of the centrifugal compressor.
  • the labyrinth seal 10 includes a plurality of first projections 11 provided on the back surface 35 of the impeller 32 and a plurality of second projections 12 provided on the stationary member 46. There is.
  • a labyrinth flow passage 15 is formed between the first convex portion 11 and the second convex portion 12 in the radial direction.
  • the plurality of first protrusions 11 are provided along the circumferential direction at a plurality of radial positions on the back surface 35 of the impeller 32.
  • a plurality of first convex portions 11 are provided in a ring shape around the rotation axis O of the rotor 5. That is, the plurality of first convex portions 11 are formed concentrically.
  • the plurality of second convex portions 12 are provided along the circumferential direction on the stationary member 46 such that the tip end portion enters between the adjacent first convex portions 11.
  • the plurality of second convex portions 12 are annularly provided around the rotation axis O of the rotor 5 so as to correspond to the plurality of first convex portions 11 shown in FIG. 2B. That is, the plurality of second convex portions 12 are formed concentrically.
  • one second protrusion 12 is disposed between two adjacent first protrusions 11 in the radial direction, ie, the first protrusion 11 and the first protrusion 11 in the radial direction.
  • the configuration in which the two convex portions 12 are alternately arranged one by one is illustrated.
  • at least one second convex portion 12 may be disposed between two adjacent first convex portions 11, and, for example, between two adjacent first convex portions 11 in the radial direction, Two second projections 12 may be disposed.
  • the back surface 35 of the impeller 32 is formed to be orthogonal to the rotation axis O of the rotor 5.
  • the arrangement direction of the plurality of first protrusions 11 in the radial direction and the arrangement direction of the plurality of second protrusions 12 in the radial direction are both orthogonal to the rotation axis O of the rotor 5 .
  • the arrangement direction of the plurality of first convex portions 11 or the plurality of second convex portions 12 may be a direction inclined with respect to a plane orthogonal to the rotation axis O.
  • the plurality of first protrusions 11 or the plurality of second protrusions are arranged along a direction inclined away from the inlet side of the impeller 32 in the axial direction as going from the radially outer side to the inner side It is also good.
  • FIG. 6 is a diagram showing a flow velocity distribution in the meridional plane among the flow analysis results in the labyrinth seal 50.
  • FIG. 7 is a diagram showing the relative total temperature distribution among the flow analysis results in the labyrinth seal 50. As shown in FIG.
  • the first convex portion 52 on the back side of the impeller 32 and the second convex portion 53 of the stationary member 46 are alternately arranged in the radial direction. It is arranged. Further, the flow path 51 between the first convex portion 52 and the second convex portion 53 has a minimum clearance between the radial outer surface of the first convex portion 52 and the tip portion of the second convex portion 53.
  • the portion 54 is formed.
  • the flow velocity distribution in the flow passage 51 has the highest flow velocity at the minimum clearance portion 54.
  • an expansion area 55 formed between adjacent second convex portions 53 and the tip end portion of the first convex portion 52 is located.
  • the fluid having a high flow velocity in the minimum clearance portion 54 decelerates rapidly in the expansion region 55. By repeating this, it is known that the pressure of the fluid gradually decreases.
  • the fluid having a high flow velocity that has actually passed through the minimum clearance portion 54 collides with the wall surface 56 on the stationary member 46 side, and the flow velocity is partial in the flow path returning to the impeller 32 side. It remains relatively high.
  • FIG. 6 the fluid having a high flow velocity that has actually passed through the minimum clearance portion 54 collides with the wall surface 56 on the stationary member 46 side, and the flow velocity is partial in the flow path returning to the impeller 32 side. It remains relatively high.
  • the labyrinth seal 10 which concerns on this embodiment is conceived based on the above-mentioned knowledge by the present inventors, and is further provided with the following composition.
  • a labyrinth comprising a plurality of minimum clearances 16 formed between the first projection 11 and the second projection 12 between the back surface 35 of the impeller 32 and the stationary member 46
  • a channel 15 is formed along the radial direction.
  • the stationary member 46 is positioned upstream of the minimum clearance portion 16, and the minimum The back surface 35 of the impeller 32 is located downstream of the clearance portion 16.
  • the stationary member 46 is positioned upstream of the minimum clearance 16 in the flow direction of the leakage flow passing through the minimum clearance 16, and the back surface 35 of the impeller 32 downstream of the minimum clearance 16. Is supposed to be located. Therefore, the fluid accelerated when passing through the minimum clearance portion 16 flows along the back surface 35 of the impeller 32 after colliding with the back surface 35 of the impeller 32 instead of the stationary member 46 side. Therefore, the fluid near the wall surface of the stationary member 46 having a high relative total temperature as viewed from the impeller 32 side is prevented from being transferred to the impeller 32 side along with the fluid having a high flow velocity which has passed through the minimum clearance portion 16 it can. Therefore, the amount of heat input from the fluid passing through the labyrinth seal 10 to the impeller 32 can be reduced, and the temperature rise of the impeller 32 can be suppressed.
  • the labyrinth seal 10 is configured to seal the radially inward leakage flow between the back surface 35 of the impeller 32 and the stationary member 46, and the minimum clearance 16 is a first protrusion It may be formed between the second protrusion 12 and the radially inner surface of the first end 11 or the first protrusion 11.
  • the flow of the fluid toward the back surface 35 of the impeller 32 can be realized on the downstream side of the minimum clearance portion 16. Thereby, the amount of heat input from the fluid passing through the labyrinth seal 10 to the impeller 32 can be reduced, and the temperature rise of the impeller 32 can be suppressed.
  • the radially inner surface of the first convex portion 11 or this surface side The minimum clearance portion 16 is formed by the tip (sword tip) of the second projection 12 and the radially outer surface of the second convex portion 12 or the tip (sword tip) on the surface side.
  • the fluid flowing along the radially inner surface of the first protrusion 11 or the radially outer surface of the second protrusion 12 is the stationary member 46. It flows from the side toward the impeller 32 side.
  • the labyrinth seal 10 may be configured to allow the fluid to flow radially inward from the inside in the flow path 15.
  • a seal tip 12 a is provided at the tip of the second convex portion 12 of the labyrinth seal 10. Further, the minimum clearance portion 16 is formed between the radial inner surface of the first convex portion 11 and the seal tip 12 a of the second convex portion 12. As a specific configuration example, the radially inner surface of the first convex portion 11 is formed along the axial direction. Further, the radially outer surface of the first convex portion 11 is formed to be inclined with respect to the axial direction.
  • the radially outer surface of the first convex portion 11 may be inclined in a direction away from the inlet side of the impeller 32 in the axial direction as it goes from the radially outer side to the inner side.
  • the width of the first convex portion 11 in the radial direction is larger at the end on the stationary member 46 side than the base on the rear surface 35 side of the impeller 32.
  • the first convex portion 11 may be rounded at corner portions in the radial direction, or the corner portions may be chamfered in a tapered shape.
  • both the radially inner surface and the outer surface are formed to be inclined with respect to the axial direction, and these surfaces are parallel to each other.
  • the radially inner surface and the outer surface of the second convex portion 12 may be inclined in a direction away from the inlet side of the impeller 32 in the axial direction as it goes from the radially outer side to the inner side.
  • R may be attached to the corner
  • the seal tip 12a is provided on the second convex portion 12 on the stationary member 46 side, the wall surface of the stationary member 46 from the flow of fluid passing through the minimal clearance portion 16 on the downstream side of the minimal clearance portion 16 (The wall surface of the second convex portion 12) is far away. For this reason, it is possible to effectively suppress a situation in which the flow velocity passing through the minimum clearance portion 16 is accompanied by the high fluid and transferred to the impeller 32 side. Therefore, the amount of heat input from the fluid passing through the labyrinth seal 10 to the impeller 32 can be effectively reduced, and the temperature rise of the impeller 32 can be further suppressed.
  • the radially inner surface of the first convex portion 11 forms a seal surface extending along the axial direction of the centrifugal compressor (for example, the direction of the rotation axis O shown in FIG. 1).
  • the second convex portion 12 is provided so as to protrude from the stationary member 46 toward the rear surface 35 side of the impeller 32 and the outer side in the radial direction.
  • a seal point 11 a is provided at the tip of the first convex portion 11 of the labyrinth seal 10. Further, the minimum clearance portion 16 is formed between the seal tip 11 a of the first convex portion 11 and the outer surface of the second convex portion 12 in the radial direction.
  • the radially inner surface of the first protrusion 11 and the radially outer surface of the first protrusion 11 are formed to be inclined with respect to the axial direction.
  • the radially inner surface of the first convex portion 11 and the radially outer surface of the first convex portion 11 are in the axial direction on the inlet side of the impeller 32 as they go from the radially outer side to the inner side. It may be inclined in the direction away from. Further, the inclination angles of the radial inner surface of the first convex portion 11 and the radial outer surface of the first convex portion 11 may be different. In this case, the width of the first convex portion 11 in the radial direction is larger at the end on the stationary member 46 side than at the base on the rear surface 35 side of the impeller 32.
  • first convex portion 11 may be rounded at corner portions in the radial direction, or the corner portions may be chamfered in a tapered shape.
  • first convex portion 11 may be rounded at corner portions in the radial direction, or the corner portions may be chamfered in a tapered shape.
  • second convex portion 12 both the radially inner surface and the outer surface are formed along the axial direction, and these surfaces are parallel to each other.
  • R may be attached to the corner
  • the minimum clearance portion 16 formed between the seal tip 11a of the first convex portion 11 on the impeller 32 side and the radial outer surface of the second convex portion 12 of the stationary member 46 is passed.
  • the fluid can be directed to the back 35 of the impeller 32.
  • the seal nib 11 a is provided at the tip of the first convex portion 11, and the minimum clearance portion 16 is the outer surface of the seal convex 11 a of the first convex portion 11 and the second convex portion 12 in the radial direction. And between.
  • the clearance width direction of the minimum clearance portion 16 is in the radial direction, the clearance width of the minimum clearance portion 16 is not easily affected even if the impeller 32 is shifted in the axial direction. Therefore, the seal performance deterioration due to the displacement of the axial direction of the impeller 32 can be suppressed.
  • the amount of heat input to the impeller 32 from the fluid passing through the labyrinth seal 10 is reduced, and the temperature rise of the impeller 32 is suppressed. Can. Therefore, the fall of the creep life resulting from high temperature formation of impeller 32 can be controlled.
  • the centrifugal compressor according to at least one embodiment of the present invention the amount of heat input from the fluid passing through the labyrinth seal 10 to the impeller 32 can be reduced, and the temperature rise of the impeller 32 can be suppressed. Therefore, it is possible to suppress a decrease in creep life caused by the high temperature of the impeller 32, and to realize a high pressure ratio of the centrifugal compressor.
  • the increase in pressure ratio of the centrifugal compressor is realized by reducing the amount of heat input from the fluid passing through the labyrinth seal 10 to the impeller 32.
  • the performance of the turbocharger 1 can be improved.
  • the present invention is not limited to the above-described embodiments, and includes the embodiments in which the above-described embodiments are modified, and the embodiments in which these embodiments are appropriately combined.
  • the application destination of the labyrinth seal 10 is limited to the centrifugal compressor 3 of a supercharger. Instead, it may be used for other centrifugal compressors.
  • the supercharger 1 was demonstrated as an application destination of a centrifugal compressor as an example in the said embodiment, the application destination of the centrifugal compressor which concerns on this embodiment is not limited to this.
  • relative or absolute arrangements such as “radial”, “in a certain direction”, “along a certain direction”, “parallel”, “orthogonal”, “center”, “concentric” or “coaxial”
  • the expression is not only to express such an arrangement strictly, but also to indicate a relative displacement or a relative displacement with an angle or distance that can obtain the same function.
  • expressions that indicate that things such as “identical”, “equal” and “homogeneous” are equal states not only represent strictly equal states, but also have tolerances or differences with which the same function can be obtained. It also represents the existing state.
  • expressions representing shapes such as quadrilateral shapes and cylindrical shapes not only represent shapes such as rectangular shapes and cylindrical shapes in a geometrically strict sense, but also uneven portions and chamfers within the range where the same effect can be obtained.
  • the shape including a part etc. shall also be expressed.
  • the expressions “comprising”, “including” or “having” one component are not exclusive expressions excluding the presence of other components.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
PCT/JP2015/073128 2014-10-17 2015-08-18 ラビリンスシール、遠心圧縮機及び過給機 WO2016059866A1 (ja)

Priority Applications (2)

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KR1020167032861A KR101855610B1 (ko) 2014-10-17 2015-08-18 래버린스 시일, 원심 압축기 및 과급기
CN201580039997.4A CN108026938B (zh) 2014-10-17 2015-08-18 迷宫式密封件、离心压缩机以及增压机

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2014-212559 2014-10-17
JP2014212559A JP6225092B2 (ja) 2014-10-17 2014-10-17 ラビリンスシール、遠心圧縮機及び過給機

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WO2016059866A1 true WO2016059866A1 (ja) 2016-04-21

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JP (1) JP6225092B2 (zh)
KR (1) KR101855610B1 (zh)
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WO (1) WO2016059866A1 (zh)

Cited By (4)

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US20150345373A1 (en) * 2012-12-17 2015-12-03 Valeo Air Management Uk Limited Compressing device with thermal protection
GB2568715A (en) * 2017-11-24 2019-05-29 Jaguar Land Rover Ltd Impeller
WO2020177941A1 (de) * 2019-03-06 2020-09-10 Robert Bosch Gmbh Verdichter
US20230184127A1 (en) * 2021-12-14 2023-06-15 Regi U.S., Inc. Rotary vane device with longitudinally extending seals

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KR102033355B1 (ko) * 2018-02-07 2019-10-17 엘지전자 주식회사 소형 터보 압축기
CN110145479A (zh) * 2019-05-23 2019-08-20 大连海事大学 一种自带电机转子冷却系统的电动空压机
CN110671157A (zh) * 2019-11-22 2020-01-10 东方电气集团东方汽轮机有限公司 一种用于径流式透平的径向汽封结构及径流式透平
KR20220065923A (ko) * 2020-11-13 2022-05-23 엘지전자 주식회사 압축기 및 이를 포함하는 칠러
CN115450949B (zh) * 2022-11-08 2023-04-25 中国核动力研究设计院 超临界二氧化碳压气机以及同轴发电系统
CN115450950B (zh) * 2022-11-08 2023-03-03 中国核动力研究设计院 压气机和超临界二氧化碳发电系统
KR102643218B1 (ko) * 2023-05-02 2024-03-04 윤홍태 반도체 제조용 호리젠탈 펌프 장치

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JP2934530B2 (ja) * 1991-06-14 1999-08-16 三菱重工業株式会社 遠心圧縮機

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CN100491740C (zh) * 2007-08-31 2009-05-27 清华大学 一种球床高温气冷堆离心式氦气压缩机
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JPS5337567B2 (zh) * 1974-04-04 1978-10-09
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JPH05195999A (ja) * 1991-08-03 1993-08-06 Man B & W Diesel Gmbh 半径流圧縮機ロータの動的安定化装置

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150345373A1 (en) * 2012-12-17 2015-12-03 Valeo Air Management Uk Limited Compressing device with thermal protection
GB2568715A (en) * 2017-11-24 2019-05-29 Jaguar Land Rover Ltd Impeller
GB2568715B (en) * 2017-11-24 2020-02-26 Jaguar Land Rover Ltd Pump assembly with tortuous flow path
US11092161B2 (en) 2017-11-24 2021-08-17 Jaguar Land Rover Limited Impeller
WO2020177941A1 (de) * 2019-03-06 2020-09-10 Robert Bosch Gmbh Verdichter
US20230184127A1 (en) * 2021-12-14 2023-06-15 Regi U.S., Inc. Rotary vane device with longitudinally extending seals
US11873816B2 (en) * 2021-12-14 2024-01-16 Regi U.S., Inc. Rotary vane device with longitudinally extending seals

Also Published As

Publication number Publication date
CN108026938B (zh) 2019-12-24
KR101855610B1 (ko) 2018-05-04
JP2016079904A (ja) 2016-05-16
JP6225092B2 (ja) 2017-11-01
KR20160147916A (ko) 2016-12-23
CN108026938A (zh) 2018-05-11

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