WO2017094546A1 - 取付構造、および、過給機 - Google Patents
取付構造、および、過給機 Download PDFInfo
- Publication number
- WO2017094546A1 WO2017094546A1 PCT/JP2016/084474 JP2016084474W WO2017094546A1 WO 2017094546 A1 WO2017094546 A1 WO 2017094546A1 JP 2016084474 W JP2016084474 W JP 2016084474W WO 2017094546 A1 WO2017094546 A1 WO 2017094546A1
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- WIPO (PCT)
- Prior art keywords
- diameter portion
- shaft
- large diameter
- hole
- small
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
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- 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
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
-
- 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
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
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- 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
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- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
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- 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
-
- 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
- F05D2240/60—Shafts
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
Definitions
- the present disclosure relates to a mounting structure for attaching an impeller to a shaft, and a turbocharger.
- turbocharger in which a shaft is rotatably supported by a bearing housing.
- a turbine impeller is provided at one end of the shaft, and a compressor impeller is provided at the other end.
- the turbocharger is connected to the engine.
- the exhaust gas discharged from the engine rotates the turbine impeller.
- the rotation of the turbine impeller causes the compressor impeller to rotate via the shaft.
- the supercharger compresses air as the compressor impeller rotates and sends it to the engine.
- the compressor impeller includes a main body and a plurality of blades.
- the plurality of blades are provided on the outer peripheral surface of the main body.
- a through hole is formed in the main body of the compressor impeller.
- the shaft is inserted through the through hole.
- two large diameter portions are formed on the portion of the shaft inserted into the through hole, with the small diameter portion interposed therebetween. The two large diameter portions center the shaft coaxially with the through hole.
- An object of the present disclosure is to provide a mounting structure and a supercharger capable of suppressing an increase in unbalance.
- the attachment structure concerning one mode of this indication has the main part in which the penetration hole by which a shaft is penetrated was formed, and a plurality of feathers provided in the peripheral face of a main part.
- An impeller having a boss portion formed on one end side of the shaft with respect to a plurality of blades of the main body portion, and a small diameter of the shaft opposed to the inner circumferential surface of the through hole in the radial direction of the shaft Part and the shaft, which is located on the other end side of the shaft than the small diameter part, and is located on the first large diameter part having a larger outer diameter than the small diameter part and of the shaft on one end side of the shaft than the small diameter part
- the second large diameter portion located at the radially inner side of the boss with a larger outer diameter, and the through hole, provided radially inward of the boss, radially in the first large diameter portion of the through hole
- the second large diameter portion may extend longer in the axial direction of the shaft than the first large diameter portion.
- the through hole and the first large diameter portion may be interference fit, and the through hole and the second large diameter portion may be intermediately fitted.
- the shaft may have a third large diameter portion located between the first large diameter portion and the second large diameter portion and having an outer diameter larger than the small diameter portion.
- the back surface portion of the main body portion located closer to the other end of the shaft than the plurality of blades is inclined in the direction in which the outer diameter becomes smaller toward the other end side of the shaft, and the first large diameter portion is the back surface It may be located radially inward of the part.
- the small diameter portion may be located radially inward of the outermost diameter portion of the main body portion that extends to the outermost side in the radial direction of the shaft.
- the supercharger concerning one mode of this indication is provided with the above-mentioned attachment structure.
- FIG. 2 (a) shows a state before the compressor impeller is attached to the shaft.
- FIG. 2 (b) shows the state after the compressor impeller is attached to the shaft. It is an explanatory view for explaining the 1st modification.
- FIG. 4A is a first diagram for explaining the second modification.
- FIG. 4 (b) is a second diagram for explaining the second modification.
- FIG. 1 is a schematic cross-sectional view of a turbocharger C.
- the supercharger C includes a supercharger main body 1.
- the turbocharger body 1 includes a bearing housing 2 (housing).
- the turbine housing 4 is connected to the left side of the bearing housing 2 by the fastening mechanism 3.
- the compressor housing 6 is connected to the right side of the bearing housing 2 by a fastening bolt 5.
- the bearing housing 2, the turbine housing 4, and the compressor housing 6 are integrated.
- a projection 2 a is provided on the outer peripheral surface of the bearing housing 2 near the turbine housing 4.
- the protrusion 2 a protrudes in the radial direction of the bearing housing 2.
- a protrusion 4 a is provided on the outer peripheral surface of the turbine housing 4 near the bearing housing 2.
- the protrusion 4 a protrudes in the radial direction of the turbine housing 4.
- the bearing housing 2 and the turbine housing 4 are attached by band fastening the projections 2 a and 4 a by the fastening mechanism 3.
- the fastening mechanism 3 is configured by, for example, a G coupling that clamps the protrusions 2a and 4a.
- a bearing hole 2 b is formed in the bearing housing 2.
- the bearing hole 2 b penetrates in the left-right direction of the turbocharger C.
- the shaft 8 is rotatably supported by a bearing 7 (a semi-floating bearing is shown as an example in FIG. 1) provided in the bearing hole 2b.
- a turbine impeller 9 is provided at the left end of the shaft 8.
- a turbine impeller 9 is rotatably accommodated in the turbine housing 4.
- a compressor impeller 10 (impeller) is provided at the right end of the shaft 8.
- a compressor impeller 10 is rotatably accommodated in the compressor housing 6.
- An intake port 11 is formed in the compressor housing 6.
- the intake port 11 opens to the right of the turbocharger C.
- the intake port 11 is connected to an air cleaner (not shown).
- the diffuser flow passage 12 is formed.
- the diffuser channel 12 is formed by the facing surfaces of the bearing housing 2 and the compressor housing 6.
- the diffuser passage 12 pressurizes air.
- the diffuser channel 12 is annular.
- the diffuser flow passage 12 communicates with the intake port 11 via the compressor impeller 10 at the radially inner side.
- a compressor scroll channel 13 is provided in the compressor housing 6.
- the compressor scroll passage 13 is annular.
- the compressor scroll passage 13 is located radially outside the shaft 8 with respect to the diffuser passage 12.
- the compressor scroll passage 13 communicates with an intake port of an engine (not shown).
- the compressor scroll passage 13 is also in communication with the diffuser passage 12. Therefore, when the compressor impeller 10 rotates, air is sucked into the compressor housing 6 from the intake port 11.
- the intake air is accelerated by the action of centrifugal force in the process of flowing between the blades of the compressor impeller 10.
- the boosted and boosted air is boosted in the diffuser passage 12 and the compressor scroll passage 13.
- the boosted air is led to the intake port of the engine.
- a discharge port 14 is formed in the turbine housing 4.
- the discharge port 14 opens on the left side of the turbocharger C.
- the discharge port 14 is connected to an exhaust gas purification device (not shown).
- an exhaust gas purification device not shown
- a flow path 15 and a turbine scroll flow path 16 are provided in the turbine housing 4.
- the turbine scroll passage 16 is annular.
- the turbine scroll passage 16 is located radially outside the turbine impeller 9 with respect to the passage 15.
- the turbine scroll passage 16 communicates with a gas inlet (not shown).
- the gas inlet leads exhaust gas discharged from an exhaust manifold of the engine (not shown).
- the turbine scroll flow passage 16 is also in communication with the flow passage 15 described above. Therefore, the exhaust gas led from the gas inlet to the turbine scroll passage 16 is led to the discharge port 14 through the passage 15 and the turbine impeller 9.
- the exhaust gas guided to the discharge port 14 rotates the turbine impeller 9 in the circulation process.
- the rotational force of the turbine impeller 9 is transmitted to the compressor impeller 10 via the shaft 8.
- the rotational force of the compressor impeller 10 as described above, the air is pressurized and led to the intake port of the engine.
- FIG. 2A shows a state before the compressor impeller 10 is attached to the shaft 8.
- FIG. 2 (b) shows the state after the compressor impeller 10 is attached to the shaft 8.
- the mounting structure 20 includes an oil removing member 21 and a nut 22 in addition to the shaft 8 and the compressor impeller 10.
- the oil removing member 21 has a main body 21 a.
- the main body portion 21a has a cylindrical shape.
- One end 8 a of the shaft 8 is inserted into the main body 21 a.
- Part of the lubricating oil after lubricating the bearing 7 shown in FIG. 1 flows along the shaft 8 to the end 8 a side of the shaft 8.
- the lubricating oil that has flowed to the end 8 a side of the shaft 8 reaches the main body 21 a of the oil removing member 21 before the compressor impeller 10.
- the oil removing member 21 scatters the lubricating oil radially outward by the centrifugal force.
- the scattered lubricating oil is discharged to the outside from an oil outlet 2 c (see FIG. 1) provided in the bearing housing 2.
- the oil removing member 21 has a function of suppressing the leakage of the lubricating oil to the compressor impeller 10 side.
- the compressor impeller 10 has a main body 10 a.
- the main body portion 10a is annular.
- a through hole 10b is formed in the main body portion 10a.
- the shaft 8 is inserted into the through hole 10 b.
- a front surface portion 10d is formed on the outer peripheral surface 10c of the main body portion 10a.
- the front portion 10 d is inclined in such a direction that the outer diameter decreases toward the end 8 a of the shaft 8.
- a back surface 10e is formed on the side opposite to the front surface 10d.
- the back surface portion 10e is inclined in such a direction that the outer diameter decreases toward the other end side (left side in FIG. 2) of the shaft 8, for example.
- the back surface portion 10 e may extend, for example, perpendicularly to the axial direction of the shaft 8.
- An outermost diameter portion 10f is formed between the front surface portion 10d and the back surface portion 10e.
- the outermost diameter portion 10 f extends in the axial direction of the shaft 8.
- the outermost diameter portion 10f extends from the front surface portion 10d to the back surface portion 10e.
- the outermost diameter portion 10 f extends to the outermost side in the radial direction of the shaft 8 in the main body portion 10 a.
- a plurality of blades 10g are provided on the front surface portion 10d of the main body portion 10a.
- the plurality of blades 10g extend toward the one end 8a side of the shaft 8 from the end on the outermost diameter portion 10f side in the front surface portion 10d.
- the plurality of blades 10g are spaced apart from one another in the circumferential direction of the front portion 10d.
- the plurality of blades 10 g configured to include a plurality of short blades 10 g 1, a plurality of the long wing 10 g 2.
- a plurality of long blades 10 g 2 is longer extending to one end 8a side in the axial direction of the shaft 8 than the short blades 10 g 1.
- plurality of vanes 10 g and a plurality of short blades 10 g 1, both the plurality of long blades 10 g 2.
- the boss portion 10 h is a portion of the main body portion 10 a that protrudes toward the one end 8 a of the shaft 8 (more than any of the short blades 10 g 1 and the long blades 10 g 2 ) than the plurality of blades 10 g. That is, the plurality of blades 10g are not disposed on the radially outer side of the boss portion 10h.
- the shaft 8 is provided with a small diameter portion 8b, a first large diameter portion 8c, a second large diameter portion 8d, and a step surface 8e.
- the first large diameter portion 8 c is formed on the other end side of the shaft 8 than the small diameter portion 8 b of the shaft 8.
- the second large diameter portion 8 d is formed closer to one end 8 a of the shaft 8 than the small diameter portion 8 b of the shaft 8.
- the small diameter portion 8 b is formed between the first large diameter portion 8 c and the second large diameter portion 8 d.
- Each of the first large diameter portion 8c and the second large diameter portion 8d has an outer diameter larger than that of the small diameter portion 8b.
- the second large diameter portion 8 d extends in the axial direction of the shaft 8 longer than the first large diameter portion 8 c.
- the step surface 8 e is formed on the other end side of the shaft 8 than the first large diameter portion 8 c.
- the step surface 8 e is formed by the outer diameter difference of the shaft 8.
- the step surface 8 e extends in the radial direction of the shaft 8.
- the step surface 8 e faces the one end 8 a side of the shaft 8.
- the shaft 8 is inserted into the main body 21a from the state shown in FIG. 2A to a position where the left end of the left side of the main body 21a of the oil removing member 21 abuts against the step surface 8e. .
- the right end portion of the oil removing member 21 opposite to the left end portion of the main body portion 21a is in contact with the left end portion on the left side in FIG. 2 of the main body portion 10a of the compressor impeller 10 Through the shaft 8.
- a threaded portion 8 f is provided on the end 8 a side of the shaft 8.
- the screw portion 8 f is formed with a screw groove.
- the screw portion 8f protrudes from the main body portion 10a.
- the nut 22 is screwed into the protruding portion of the screw portion 8 f.
- an axial force is generated between the step surface 8 e of the shaft 8 and the nut 22.
- the oil removing member 21 and the compressor impeller 10 are attached to the shaft 8 by the axial force, as shown in FIG. 2 (b).
- the small diameter portion 8 b is separated and opposed in the radial direction of the shaft 8 with respect to the inner peripheral surface of the through hole 10 b of the main body portion 10 a. That is, a gap is provided in the radial direction of the shaft 8 between the small diameter portion 8 b and the inner peripheral surface of the through hole 10 b.
- the through hole 10b and the first large diameter portion 8c have a dimensional relationship to be an interference fit.
- the through hole 10 b and the second large diameter portion 8 d have a dimensional relationship to be an intermediate fit.
- the outer diameter of the first large diameter portion 8c is larger than the inner diameter of the through hole 10b.
- the upper limit value of the dimensional tolerance of the outer diameter of the second large diameter portion 8d is larger than the lower limit value of the dimensional tolerance of the inner diameter of the through hole 10b.
- the lower limit value of the dimensional tolerance of the outer diameter of the second large diameter portion 8d is smaller than the upper limit value of the dimensional tolerance of the inner diameter of the through hole 10b. That is, the second large diameter portion 8d and the inner peripheral surface of the through hole 10b may have clearances as in the case where the interference can be made within the range of the dimensional tolerance.
- the outer diameter of the second large diameter portion 8d may be the same as, or smaller than, the inner diameter of the through hole 10b.
- the inner diameter from the portion facing the first large diameter portion 8c in the radial direction to the portion facing the second large diameter portion 8d in the radial direction is approximately equal.
- the first large diameter portion 8c side is an interference fit
- the second large diameter portion 8d side is an intermediate fitting.
- the first large diameter portion 8c is slightly larger in diameter than the second large diameter portion 8d. Therefore, by disposing the second large diameter portion 8 d on the one end side 8 a of the shaft 8, the shaft 8 can be easily inserted into the through hole 10 b from the one end 8 a side. The workability of assembly is improved.
- a small diameter portion 8 b which is smaller in diameter than the first large diameter portion 8 c and the second large diameter portion 8 d and which is easily elastically deformed is provided.
- the shaft 8 is stretched by tightening with the nut 22. As a result, a stable axial force is generated.
- the shaft 8 is provided with two large diameter portions (a first large diameter portion 8c and a second large diameter portion 8d). Therefore, the large diameter portion is guided by the inner peripheral surface of the through hole 10b.
- the shaft 8 is inserted into the compressor impeller 10 while maintaining the positional relationship in which the compressor impeller 10 is coaxial with the shaft 8. Further, the two large diameter portions are separated from each other across the small diameter portion 8b. The inclination of the compressor impeller 10 with respect to the axial center of the shaft 8 is effectively suppressed during the assembling operation as compared with the case where the two large diameter portions are adjacent to each other.
- the rotating body is configured, for example, by integrally attaching the turbine impeller 9, the oil removing member 21, and the compressor impeller 10 to the shaft 8.
- the second large diameter portion 8d is disposed radially inward of the boss portion 10h.
- the boss portion 10 h is not provided with a plurality of blades 10 g on the radially outer side.
- the boss 10 h is less susceptible to the centrifugal force of the blade 10 g when it rotates. Therefore, the inner circumferential surface of the region of the through hole 10b which is located radially inward of the boss 10h is not pushed and spread too much.
- the amount of eccentricity of the compressor impeller 10 with respect to the axial center of the shaft 8 is suppressed. An increase in the above-mentioned imbalance of the rotating body is suppressed.
- the first large diameter portion 8 c is disposed radially inward of the back surface portion 10 e of the main body portion 10 a of the compressor impeller 10.
- a portion positioned radially inward of the outermost diameter portion 10f has a large mass extending radially inward of the outermost diameter portion 10f.
- part located in the radial direction inner side of outermost diameter part 10f among the through-holes 10b receives a big centrifugal force, and is easy to expand.
- the back surface portion 10 e is formed to be inclined in a direction in which the outer diameter decreases as going from the outermost diameter portion 10 f to the other end side of the shaft 8.
- the mass of the back surface portion 10 e extending radially outward is smaller than that of the outermost diameter portion 10 f. That is, in the area
- the first large diameter portion 8c is tightly fitted to the through hole 10b.
- the compressor impeller 10 is attached to the shaft 8 by the frictional force.
- the outer diameter of the first large diameter portion 8c is larger than the inner diameter of the through hole 10b. Even if the through hole 10b is pushed and expanded by the centrifugal force, the interference is caused by the first large diameter portion 8c following the through hole 10b. Separation of the first large diameter portion 8c from the inner circumferential surface of the through hole 10b is suppressed.
- the second large diameter portion 8d extends in the axial direction of the shaft 8 longer than the first large diameter portion 8c.
- the second large diameter portion 8d is easily guided by the inner peripheral surface of the through hole 10b even if the dimensional relationship with the through hole 10b is an intermediate fit. Further, during the assembling operation, the positional relationship in which the compressor impeller 10 is coaxial with the shaft 8 is stably maintained.
- the first large diameter portion 8c has a length in the axial direction which does not reach from the rear surface portion 10e to a portion positioned radially inward of the outermost diameter portion 10f.
- the axial length of the first large diameter portion 8c is appropriately set in consideration of, for example, the workability of assembling the compressor impeller 10 to the shaft 8 and the effect of suppressing the unbalance of the rotating body. It is also good.
- the first large diameter portion 8c may extend toward the one end 8a in the axial direction of the shaft 8 including a region located radially inward of the outermost diameter portion 10f.
- the first large diameter portion 8c may be formed in the axial direction starting from a position separated from the back surface portion 10e on the side of one end 8a in the axial direction of the shaft 8. That is, by forming the first large diameter portion 8c including at least a part of the region located on the inner side in the radial direction of the back surface portion 10e, the two large diameter portions are sufficiently separated. Therefore, the inclination of the compressor impeller 10 with respect to the axial center of the shaft 8 is more effectively suppressed at the time of assembly work and rotation of the shaft 8.
- the small diameter portion 8b is located radially inward of the outermost diameter portion 10f.
- part located in the radial direction inner side of outermost diameter part 10f among the through-holes 10b receives a big centrifugal force, and is easy to expand.
- the small diameter portion 8 b is located radially inward of the outermost diameter portion 10 f.
- the fitting structure is not taken on the radially inner side of the outermost diameter portion 10 f. That is, the first large diameter portion 8c and the second large diameter portion 8d are disposed so as to avoid the radially inner side of the outermost diameter portion 10f. In this case, of the inner circumferential surface of the through hole 10b, the portion facing the first large diameter portion 8c and the second large diameter portion 8d in the radial direction is difficult to expand in diameter. An increase in imbalance is suppressed.
- FIG. 3 is an explanatory view for explaining a first modification.
- the case where two large diameter portions are formed in the shaft 8 has been described.
- the first modification three large diameter portions are provided on the shaft 38.
- a third large diameter portion 38g is provided between the first large diameter portion 38c and the second large diameter portion 38d in the shaft 38.
- the third large diameter portion 38g may be formed on one end 38a side of the shaft 38 at the radially inner side of the plurality of blades 10g.
- the number of large diameter parts is not limited to three. It may be appropriately set based on the axial length of the compressor impeller 10 and the like. For example, the number of the large diameter portions may be four.
- the position of the large diameter portion provided between the first large diameter portion 38c and the second large diameter portion 38d is not limited to the one end 38a side of the shaft 38.
- the large diameter portion may be appropriately formed at any position between the first large diameter portion 38c and the second large diameter portion 38d.
- the large diameter portion may be formed on the other end side of the shaft 38, for example. However, when the large diameter portion is formed on one end 38 a side of the shaft 38, the large diameter portion may be disposed in the region of the through hole 10 b where the diameter expansion by centrifugal force is small. Also, for example, the third large diameter portion 38g may be sized to be an intermediate fit with the through hole 10b, as with the second large diameter portion 38d. In this case, the deterioration of the workability of assembling the compressor impeller 10 to the shaft 38 is suppressed.
- the second large diameter portion 38 d and the third large diameter portion 38 g may each have a shorter axial length than the second large diameter portion 8 d in the above-described embodiment.
- the shaft 38 two small diameter portions of the shaft 38 are provided with the third large diameter portion 38g interposed therebetween (the oil removing member 21 side is a first small diameter portion 38b 1 , and one end 38a side of the shaft 38 is a second small diameter portion 38b 2 ).
- the first small-diameter portion 38b 1 and the second small diameter portion 38b 2 the total axial length of the shaft 38 may be axial length and equal approximate shaft 8 of the small-diameter portion 8b of the embodiments described above.
- the tensile stress to the shaft 8 by fastening by the nut 22 acts, the first small diameter portion 38b 1 and the sum of the elastic deformation of the second small diameter portion 38b 2 becomes about the same as the small diameter portion 8b. Similar to the small diameter portion 8b, a stable axial force is generated between the nut 22 and the step surface 38e.
- FIG. 4A is a first diagram for explaining the second modification.
- FIG. 4 (b) is a second diagram for explaining the second modification.
- a small inner diameter portion 40i is provided inside the through hole 40b of the compressor impeller 40 (impeller) in the radial direction of the boss 40h. .
- the inner diameter of the small inner diameter portion 40i is smaller than the inner diameter of the portion 40j radially opposed to the first large diameter portion 8c in the through hole 40b.
- the small inner diameter portion 40i is a protrusion provided on the inner peripheral surface of the through hole 40b.
- the small inner diameter portion 40i is located closer to one end 8a of the shaft 8 than the blades 40g of the compressor impeller 40.
- a stepped surface 40k is formed on the inner peripheral surface of the through hole 40b from the portion 40j in the through hole 40b radially opposed to the first large diameter portion 8c to the small inner diameter portion 40i.
- the step surface 40k is located, for example, on the radially outer side of the second large diameter portion 8d. However, the step surface 40k may be located closer to the first large diameter portion 8c than the second large diameter portion 8d.
- the stepped surface 40 k extends in the radial direction of the shaft 8.
- the boss 40 h is not easily affected by the centrifugal force of the blade 40 g.
- the amount of eccentricity of the compressor impeller 40 with respect to the axial center of the shaft 8 is suppressed. An increase in unbalance of the rotating body is suppressed.
- the shaft 8 is inserted from the side of the through hole 40b opposite to the small inner diameter portion 40i. That is, the second large diameter portion 8d is also inserted from the side opposite to the small inner diameter portion 40i.
- the outer diameter of the second large diameter portion 8 d is smaller than that of the first large diameter portion 8 c.
- the outer diameter of the second large diameter portion 8d has a dimension corresponding to the inner diameter of the small inner diameter portion 40i. That is, the radial gap between the second large diameter portion 8d and the portion 40j is larger than the radial gap between the second large diameter portion 8d and the small inner diameter portion 40i.
- both the first large diameter portion 8c and the portion 40j, and the second large diameter portion 8d and the small inner diameter portion 40i may be an interference fit.
- an inclined surface or a curved surface may be provided at the boundary between the radially inner end of the step surface 40k and the small inner diameter portion 40i.
- the inclined surface or the curved surface serves as a guide, and the second large diameter portion 8d is easily inserted into the small inner diameter portion 40i.
- the attachment structure 20 is provided in the supercharger C
- the modification described above if the impeller is attached to the shafts 8 and 38, the attachment structure 20 may be provided in another rotating machine. Good. That is, the mounting structure 20 described above is applicable to any rotating machine other than the turbocharger C.
- the second large diameter portions 8 d and 38 d extend in the axial direction of the shafts 8 and 38 from the first large diameter portions 8 c and 38 c has been described.
- the second large diameter portions 8d and 38d may have the same or shorter axial length of the shafts 8 and 38 than the first large diameter portions 8c and 38c.
- the magnitude of the coefficient of friction of the surfaces of the shafts 8 and 38 varies depending on the product. The magnitude of the coefficient of friction of the surfaces of the shafts 8 and 38 affects the resistance (frictional resistance) when the shafts 8 and 38 are inserted through the through holes 10 b.
- the following effects can be obtained. is there. In the assembling operation, the variation in resistance when the shafts 8 and 38 are inserted into the through holes 10 b can be reduced.
- the third large diameter portion 38g is formed on the side of the one end 38a of the shaft 38 inward of the plurality of blades 10g in the radial direction.
- the third large diameter portion 38g may be formed at any position between the first large diameter portion 38c and the second large diameter portion 38d.
- the back surface portion 10e of the main body portion 10a is inclined in the direction in which the outer diameter becomes smaller as it goes to the other end side of the shafts 8 and 38 is described.
- the case where the first large diameter portions 8c and 38c are located radially inward of the back surface portion 10e has been described.
- the back surface portion 10 e may extend, for example, along the radial direction of the shafts 8, 38.
- the first large diameter portions 8c and 38c may be offset in the axial direction of the shafts 8 and 38 from the inner side in the radial direction of the back surface portion 10e.
- the small diameter portion 8b, the first small diameter portion 38b 1 has been described a case located radially inward of the outermost diameter portion 10f of the main body portion 10a.
- the small diameter portion 8b, a first small diameter portion 38b 1 may deviate from the radially inner side of the outermost diameter portion 10f of the main body portion 10a in the axial direction of the shaft 8, 38.
- a plurality of vanes 10 g, 40 g was described a case configured to include a plurality of short blades 10 g 1, a plurality of long blades 10 g 2.
- the plurality of blades 10g and 40g may have one type of axial length of the shafts 8 and 38.
- the step surface 40k is formed on the inner peripheral surface of the through hole 40b.
- a tapered surface may be formed in which the inner diameter gradually decreases from the portion 40 j in the through hole 40 b radially opposite to the first large diameter portion 8 c to the small inner diameter portion 40 i.
- the provision of the step surface 40k facilitates the processing of the through hole 40b. Processing costs are reduced.
- the second large diameter portion 8 d may not be provided as long as the small inner diameter portion 40 i of the compressor impeller 40 fits to the small diameter portion 8 b. That is, the small diameter portion 8b may extend to one axial end 8a side of the shaft 8 and may be in a fitting relationship with the small inner diameter portion 40i. Also in this case, as in the second modification described above, for example, when the compressor impeller 40 is heated and the shaft 8 is inserted, the contact between the through hole 40 b and the second large diameter portion 8 d is suppressed. The contraction of the through hole 40b is suppressed.
- the amount of eccentricity of the compressor impeller 40 with respect to the axial center of the shaft 8 is suppressed. An increase in unbalance of the rotating body is suppressed.
- the second large diameter portion 8d having a larger outer diameter than the small inner diameter portion 8b the following effects can be obtained.
- the shaft 8 only the second large diameter portion 8 d fitted with the inner circumferential surface located radially inward of the boss portion 40 h may be processed with high accuracy. Processing time is reduced.
- the configuration of the second modified example may be applied to the embodiment and the first modified example described above, such as providing the small inner diameter portion 40i, for example.
- the present disclosure can be utilized for a mounting structure for attaching an impeller to a shaft, and a turbocharger.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Abstract
Description
8 シャフト
8a 一端
8b 小径部
8c 第1大径部
8d 第2大径部
10 コンプレッサインペラ(インペラ)
10a 本体部
10b 貫通孔
10c 外周面
10e 背面部
10f 最外径部
10g 羽根
10h ボス部
20 取付構造
38 シャフト
38a 一端
38c 第1大径部
38d 第2大径部
38g 第3大径部
40 コンプレッサインペラ(インペラ)
40b 貫通孔
40g 羽根
40h ボス部
40i 小内径部
40j 部位
Claims (7)
- シャフトが挿通される貫通孔が形成された本体部と、前記本体部の外周面に設けられた複数の羽根とを有し、前記本体部のうち前記複数の羽根よりも前記シャフトの一端側に突出するボス部が形成されたインペラと、
前記シャフトのうち、前記貫通孔の内周面に対して前記シャフトの径方向に離隔して対向する小径部と、
前記シャフトのうち、前記小径部より前記シャフトの他端側に位置し、前記小径部より外径が大きい第1大径部と、
前記シャフトのうち、前記小径部より前記シャフトの一端側に位置し、前記小径部より外径が大きく、前記ボス部の径方向内側に位置する第2大径部、および、前記貫通孔のうち、前記ボス部の径方向内側に設けられ、前記貫通孔における前記第1大径部に径方向に対向する部位より内径が小さい小内径部の一方または双方と、
を備える取付構造。 - 前記第2大径部は、前記第1大径部より前記シャフトの軸方向に長く延在する請求項1に記載の取付構造。
- 前記貫通孔と前記第1大径部は、締り嵌めされ、前記貫通孔と前記第2大径部は、中間嵌めされた請求項1または2に記載の取付構造。
- 前記シャフトのうち、前記第1大径部と前記第2大径部との間に位置し、前記小径部より外径が大きい第3大径部を備える請求項1から3のいずれか1項に記載の取付構造。
- 前記本体部のうち、前記複数の羽根よりも前記シャフトの他端側に位置する背面部は、前記シャフトの他端側に向かう程、外径が小径となる向きに傾斜し、
前記第1大径部は、前記背面部の径方向内側に位置する請求項1から4のいずれか1項に記載の取付構造。 - 前記小径部は、前記本体部のうち、前記シャフトの径方向に最も外側まで延在する最外径部の径方向内側に位置する請求項1から5のいずれか1項に記載の取付構造。
- 前記請求項1から6のいずれか1項に記載の取付構造を備える過給機。
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CN201680067972.XA CN108350798B (zh) | 2015-12-01 | 2016-11-21 | 安装构造以及增压器 |
DE112016005491.2T DE112016005491T5 (de) | 2015-12-01 | 2016-11-21 | Montagestruktur und turbolader |
JP2017553782A JP6566043B2 (ja) | 2015-12-01 | 2016-11-21 | 取付構造、および、過給機 |
US15/988,793 US10753367B2 (en) | 2015-12-01 | 2018-05-24 | Mounting structure and turbocharger |
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US15/988,793 Continuation US10753367B2 (en) | 2015-12-01 | 2018-05-24 | Mounting structure and turbocharger |
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DE112021007176T5 (de) | 2021-06-16 | 2024-01-04 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Montagestruktur von kompressorrad und auflader |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH01159131U (ja) * | 1988-04-23 | 1989-11-02 | ||
JP2011122536A (ja) * | 2009-12-11 | 2011-06-23 | Ihi Corp | ロータ軸及び過給機 |
JP2013515208A (ja) * | 2009-12-22 | 2013-05-02 | ボーグワーナー インコーポレーテッド | 排気ガスターボ過給機のシャフト組立体 |
US20130115088A1 (en) * | 2011-11-08 | 2013-05-09 | Honeywell International Inc. | Compressor wheel shaft with recessed portion |
WO2015087414A1 (ja) * | 2013-12-11 | 2015-06-18 | 三菱重工業株式会社 | 回転体及び該回転体の製造方法 |
WO2015146765A1 (ja) * | 2014-03-26 | 2015-10-01 | 株式会社Ihi | インペラ締結構造及びターボ圧縮機 |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3579805A (en) | 1968-07-05 | 1971-05-25 | Gen Electric | Method of forming interference fits by heat treatment |
DE2621201C3 (de) * | 1976-05-13 | 1979-09-27 | Maschinenfabrik Augsburg-Nuernberg Ag, 8900 Augsburg | Laufrad für eine Strömungsmaschine |
EP0072582B1 (de) * | 1981-08-18 | 1985-12-18 | BBC Aktiengesellschaft Brown, Boveri & Cie. | Abgasturbolader mit zwischen Turbine und Verdichter angeordneter Lagerung |
JPS58124002A (ja) * | 1982-01-20 | 1983-07-23 | Toyota Motor Corp | タ−ボチヤ−ジヤのインペラ組み付け方法 |
US4884942A (en) * | 1986-06-30 | 1989-12-05 | Atlas Copco Aktiebolag | Thrust monitoring and balancing apparatus |
US6368077B1 (en) * | 2000-05-10 | 2002-04-09 | General Motors Corporation | Turbocharger shaft dual phase seal |
US6364634B1 (en) * | 2000-09-29 | 2002-04-02 | General Motors Corporation | Turbocharger rotor with alignment couplings |
JP2002242937A (ja) | 2001-02-16 | 2002-08-28 | Nsk Ltd | ターボチャージャ用転がり軸受の保持器とその製造方法及びターボチャージャ用回転支持装置 |
US6478553B1 (en) * | 2001-04-24 | 2002-11-12 | General Motors Corporation | High thrust turbocharger rotor with ball bearings |
JP2002332850A (ja) * | 2001-05-10 | 2002-11-22 | Sogi Kogyo Kk | 非金属介在物を低減化した部材により構成される高温耐久性を向上させたvgsタイプターボチャージャの排気ガイドアッセンブリ |
US6896479B2 (en) * | 2003-04-08 | 2005-05-24 | General Motors Corporation | Turbocharger rotor |
JP4432638B2 (ja) | 2004-06-24 | 2010-03-17 | 株式会社Ihi | ターボ過給機、ターボ過給機の組立て方法およびタービン・コンプレッサ組立て装置 |
US8740465B2 (en) * | 2005-08-11 | 2014-06-03 | Robert D. McKeirnan, Jr. | Bearing system |
EP2066886B1 (en) * | 2006-09-29 | 2013-05-15 | BorgWarner Inc. | Sealing system between bearing and compressor housing |
JP5012730B2 (ja) | 2008-08-12 | 2012-08-29 | 株式会社Ihi | インペラ取付構造及び過給機 |
WO2014109849A1 (en) * | 2013-01-08 | 2014-07-17 | Borgwarner Inc. | An oil drain for the bearing housing of a turbocharger |
DE102014213641A1 (de) | 2014-01-17 | 2015-08-06 | Borgwarner Inc. | Verfahren zur Verbindung eines Verdichterrades mit einer Welle einer Aufladeeinrichtung |
US9598961B2 (en) * | 2014-07-14 | 2017-03-21 | Siemens Energy, Inc. | Gas turbine spindle bolt structure with reduced fretting fatigue |
US9708925B2 (en) * | 2014-12-17 | 2017-07-18 | Honeywell International Inc. | Adjustable-trim centrifugal compressor, and turbocharger having same |
US10233936B2 (en) * | 2016-03-25 | 2019-03-19 | Garrett Transportation I Inc. | Turbocharger compressor wheel assembly |
-
2016
- 2016-11-21 JP JP2017553782A patent/JP6566043B2/ja active Active
- 2016-11-21 WO PCT/JP2016/084474 patent/WO2017094546A1/ja active Application Filing
- 2016-11-21 DE DE112016005491.2T patent/DE112016005491T5/de active Pending
- 2016-11-21 CN CN201680067972.XA patent/CN108350798B/zh active Active
-
2018
- 2018-05-24 US US15/988,793 patent/US10753367B2/en active Active
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH01159131U (ja) * | 1988-04-23 | 1989-11-02 | ||
JP2011122536A (ja) * | 2009-12-11 | 2011-06-23 | Ihi Corp | ロータ軸及び過給機 |
JP2013515208A (ja) * | 2009-12-22 | 2013-05-02 | ボーグワーナー インコーポレーテッド | 排気ガスターボ過給機のシャフト組立体 |
US20130115088A1 (en) * | 2011-11-08 | 2013-05-09 | Honeywell International Inc. | Compressor wheel shaft with recessed portion |
WO2015087414A1 (ja) * | 2013-12-11 | 2015-06-18 | 三菱重工業株式会社 | 回転体及び該回転体の製造方法 |
WO2015146765A1 (ja) * | 2014-03-26 | 2015-10-01 | 株式会社Ihi | インペラ締結構造及びターボ圧縮機 |
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US20180266432A1 (en) | 2018-09-20 |
CN108350798B (zh) | 2020-05-26 |
JP6566043B2 (ja) | 2019-08-28 |
DE112016005491T5 (de) | 2018-08-09 |
CN108350798A (zh) | 2018-07-31 |
US10753367B2 (en) | 2020-08-25 |
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