CN103362557B - The linkage structure of a kind of impeller and turbine shaft - Google Patents
The linkage structure of a kind of impeller and turbine shaft Download PDFInfo
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- CN103362557B CN103362557B CN201310336424.0A CN201310336424A CN103362557B CN 103362557 B CN103362557 B CN 103362557B CN 201310336424 A CN201310336424 A CN 201310336424A CN 103362557 B CN103362557 B CN 103362557B
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Abstract
The invention discloses the linkage structure of the tight axial impeller of a kind of latch and this impeller and turbine shaft, belong to pressurized machine technical field.Impeller of the present invention, comprises blade, nose cone and is arranged on the blind hole of impeller rear, and impeller rear offers one or more narrow groove equably, and one end of narrow groove extends to the end of impeller, and the other end processes the circular hole that diameter is greater than narrow well width.The linkage structure of above-mentioned impeller and turbine shaft, comprise one end and be fixed on the turbine shaft on turbine, above-mentioned impeller and thrust housing, blind hole interference fit on the axle head of turbine shaft and impeller, turbine shaft and narrow slot are put corresponding section and are provided with ring-shaped step, the inner chamber of thrust housing is taper, inner chamber is set in the rear of impeller, and this rear compressive deformation, snap in ring-shaped step.The present invention not only impeller and turbine shaft easy processing, assemble fast, the amount of unbalance of rotor assembly is low, high financial profit, and the processing dimension of impeller and turbine shaft limits little, can be applied on the very little impeller of external diameter.
Description
Technical field
The present invention relates to the linkage structure of a kind of impeller and impeller and turbine shaft, more particularly, relate to the linkage structure of the tight axial impeller of latch in a kind of pressurized machine and this impeller and turbine shaft.
Background technique
Pressurized machine is the device improving inflammable mixture or the air pressure entered in cylinder.As shown in Figure 4, the action basic principle of pressurized machine is, turbine (6) utilizes the energy in engine exhaust gas to produce rotation, and portion of energy is passed to the impeller (1) being connected in turbine shaft (2) the other end by this motion through turbine shaft (2), when impeller (1) rotates in pressurized machine, (or compression) ambient air will be promoted and enter internal-combustion engine.Due to the effect of compression, the density of air is improved, thus improves the air inflow in cylinder of internal-combustion engine, makes power raising and efficient burning become possibility.Simultaneously, floating bearing (4), thrust bearing (3) and lubrication system are installed in intermediate (5), can high speed rotary motion in order to support the rotor assembly that is made up of impeller (1) and turbine (6), keep stable, and limit its axial displacement, avoid rubbing with volute or pressure shell, cause damage.
Due to the speed of turbosupercharger running, be fixed according to the moment of torsion of engine demand and emission request, and at various speeds, these require along with the change of operating mode instant.These changes make the being forced to property adjustment between various high low speed of turbocharger rotor assembly, this means that impeller and turbine inside subject violent STRESS VARIATION, cause material mechanical tired.This fatigue can be formed at first at the region of high stress, causes portion of material to peel off, and turbosupercharger cannot be worked on.In order to the life-span extending turbosupercharger increases reliability, just must analyze each component, find out heavily stressed part, manage to improve.Experience and analysis show, the axis hole of impeller, are cause heavily stressed main cause.Can say, the life-span length of whole rotor assembly depends on the Placement of impeller and turbine shaft, and has two kinds of conventional Placements at present: through hole and blind hole.Passing hole type structure is simple, as Chinese Patent Application No. 201210100765.3, Shen Qing Publication day is on August 1st, 2012, invention and created name is: the connection set of a kind of compressor impeller and axle and method, this application case relates to connection set and the method for a kind of compressor impeller and axle, belong to Compressor Technology field, the connection set of compressor impeller and axle comprises impeller, impeller rotates about the axis and includes the impeller stem axle with outer surface extended at axial direction, outer surface has tapered profiles and having noncircular symmetry profile perpendicular in the cross section of axis in the cross section comprising axis, impeller stem axle also comprises the opening that axial direction extends, gear shaft, the hole axially extended described in gear shaft is included in, its mesopore is for accept impeller stem axle when gear shaft rotates and to engage impeller stem axle, bolt is inserted in impeller opening and hole for impeller is connected to gear shaft, wherein, bolt and hole must firm thread engagement by executing.Bolt and gear shaft must engage by firm screw thread by executing by this application case, ensure that the reliability of the rotor assembly when running up, but its deficiency is: the impeller maximum stress district of this application case is positioned at the bolt place in the middle of impeller, and bolt easily produces mechanical fatigue, reduces working life.
From above-mentioned, passing hole type can not show a candle to blind-hole type, so needing low-speed big or bearing on the violent motor of change in torque, the technology of frequent use blind hole impeller, for example the people such as JeanLuc is at U.S. Patent number: propose in 4986733 without passing hole type Impeller Design, as shown in Figure 1, it is what to use internal thread (101) together with thread (201) compact siro spinning technology on turbine shaft (2), this design being threaded connection impeller (1), relatively consuming time and expensive to the manufacture of parts, because need all to need to process accurate screw thread on impeller (1) and turbine shaft (2).Meanwhile, due to various processing dimension, this Placement cannot be applied on the less impeller of external diameter (1).Moreover because rotor assembly is fixing to complete by screw thread, the mode of this Placement double thread and locking requires very high, and reason to avoid the amount of unbalance of rotor assembly excessive.Therefore, a kind of new impeller connects theory and is suggested, and according to this theory, impeller has blind hole, but without screw thread.Therefore, turbine shaft axle head does not just have threaded demand yet.
Summary of the invention
1. invent the technical problem that will solve
The amount of unbalance that the object of the invention is to overcome supercharger rotor assembly in prior art is excessive, the life-span of pressurized machine is low, poor reliability, and by the mode be threaded, requirement on machining accuracy is high, manufacture consuming time, expensive, and the deficiency that can not be applied on the less impeller of external diameter, the linkage structure of the tight axial impeller of a kind of latch and this impeller and turbine shaft is provided, adopt technological scheme provided by the invention, not only impeller and turbine shaft easy processing, assembling fast, the amount of unbalance of rotor assembly is low, high financial profit, and the processing dimension of impeller and turbine shaft limits little, can be applied on the very little impeller of external diameter, technological scheme of the present invention effectively can be improved the performance of pressurized machine and extend fatigue life simultaneously.
2. technological scheme
For achieving the above object, technological scheme provided by the invention is:
The tight axial impeller of a kind of latch of the present invention, comprise blade, nose cone and be arranged on the blind hole of impeller rear, the axis of described blind hole and the dead in line of impeller, described impeller rear offers the narrow groove of one or more equably.
Further improve as the present invention, one end of described narrow groove extends to the end of impeller, and the other end processes the circular hole that diameter is greater than narrow well width.
Further improve as the present invention, described nose cone profile is streamlined.
Further improve as the present invention, described narrow groove is set to 3 or 4 or 6.
Further improve as the present invention, the material of described impeller is aluminum or aluminum alloy.
The linkage structure of a kind of impeller of the present invention and turbine shaft, comprise one end and be fixed on the turbine shaft on turbine, the tight axial impeller of above-mentioned latch and thrust housing, blind hole interference fit on the axle head of described turbine shaft and impeller, the axle head of described turbine shaft is processed with a pair or more of parallel surface, form a non-circular geometric cross section, described turbine shaft and narrow slot are put corresponding section and are provided with ring-shaped step, the inner chamber of described thrust housing is taper, described inner chamber is set in the rear of impeller, and this rear compressive deformation, snap in ring-shaped step.
Further improve as the present invention, the distance between often pair of described parallel surface is all less than the aperture of blind hole, exhaust during for installing.
Further improve as the present invention, the rear end face of described impeller is pressed on thrust housing.
Further improve as the present invention, the axle head of described turbine shaft and the blind hole of impeller are all processed with chamfering.
Further improve as the present invention, the material hardness of described turbine shaft is greater than the material hardness of impeller.
3. beneficial effect
Adopt technological scheme provided by the invention, compared with existing known technology, there is following remarkable result:
(1) linkage structure of the tight axial impeller of a kind of latch of the present invention and this impeller and turbine shaft, impeller rear offers one or more narrow groove equably, turbine shaft and narrow slot are put corresponding section and are provided with ring-shaped step, the inner chamber of thrust housing is taper, and inner chamber is set in the rear of impeller, and this rear compressive deformation, snap in ring-shaped step, narrow groove is the space that the rear of impeller provides compressive deformation, and moving axially to inlet end during the work of restriction impeller, thus avoids the risk of wiping shell;
(2) linkage structure of the tight axial impeller of a kind of latch of the present invention and this impeller and turbine shaft, blind hole interference fit on the axle head of turbine shaft and impeller, the material hardness of turbine shaft is greater than the material hardness of impeller, the axle head of turbine shaft is processed with a pair or more of parallel surface, distance between often pair of parallel surface is all less than the aperture of blind hole, on the one hand, when turbine shaft coordinates with impeller, blind hole interior section material produces plastic deformation, be forced to expand, and non-contact segment is still in elastic state, transmitting torque makes wheel rotation effectively; On the other hand, when impeller is loaded onto turbine shaft, the air in blind hole can be discharged via the space in parallel surface and blind hole, avoids the difficulty causing fit on;
(3) linkage structure of the tight axial impeller of a kind of latch of the present invention and this impeller and turbine shaft, one end of narrow groove extends to the end of impeller, and the other end processes the circular hole that diameter is greater than narrow well width, and this circular hole is conducive to the compressive deformation of impeller rear, make assembling convenient, efficiency is higher;
(4) linkage structure of the tight axial impeller of a kind of latch of the present invention and this impeller and turbine shaft, nose cone profile is streamlined, not only can reduce gas flow loss, the stall event that blade occurs in import outer radius can also be avoided, and then the spendable effective coverage of pressurized machine and performance are improved, in addition, fairshaped nose cone makes moderate progress to the various stress that centrifugal force brings, and effectively extends the fatigue life of impeller;
(5) linkage structure of the tight axial impeller of a kind of latch of the present invention and this impeller and turbine shaft, because impeller is completely fixed on turbine shaft, the rear end face of impeller is pressed on thrust housing, whole rotor assembly is made to form one securely, do not need employing to be threaded, the amount of unbalance that extra screw-threaded coupling produces can not be brought;
(6) linkage structure of the tight axial impeller of a kind of latch of the present invention and this impeller and turbine shaft, the axle head of turbine shaft and the blind hole of impeller is all processed with chamfering, is convenient to the installation of turbine shaft and impeller;
(7) linkage structure of the tight axial impeller of a kind of latch of the present invention and this impeller and turbine shaft, the processing dimension of impeller and turbine shaft limits little, can be applied on the very little impeller of external diameter.
Accompanying drawing explanation
Fig. 1 is the impeller of pressurized machine in prior art and the linkage structure schematic diagram of turbine shaft;
Fig. 2 is the blade wheel structure schematic diagram of pressurized machine in prior art;
Fig. 3 is the B-B direction sectional view of Fig. 2;
Fig. 4 is the sectional view of intermediate rotor assembly assembly in prior art;
Fig. 5 is the sectional structure schematic diagram of the tight axial impeller of a kind of latch of the present invention;
Fig. 6 is the rear enlarged partial sectional view of the tight axial impeller of a kind of latch of the present invention;
Fig. 7 is the A-A direction sectional view of Fig. 6;
Fig. 8 is the cross-sectional view of thrust housing in the present invention;
Fig. 9 is the linkage structure partial sectional view of impeller of the present invention and turbine shaft;
Figure 10 is the partial structurtes schematic diagram of turbine shaft in the present invention;
Figure 11 is 3 kinds of schematic cross-sections of turbine shaft axle head in the present invention;
Figure 12 is the structural representation that in the present invention, impeller coordinates with turbine shaft axle head;
Figure 13 is the stress analysis figure of the tight axial impeller of a kind of latch of the present invention;
Figure 14 is the linkage structure partial enlargement cross-sectional schematic of impeller of the present invention and turbine shaft.
Label declaration in schematic diagram:
1, impeller; 101, internal thread; 102, blind hole; 103, maximum stress district; 104, narrow groove; 105, hexagon nose; 106, nose cone; 2, turbine shaft; 201, thread; 202, axle head; 203, parallel surface; 204, ring-shaped step; 3, thrust bearing; 4, floating bearing; 5, intermediate; 6, turbine; 7, thrust housing; 701, inner chamber.
Embodiment
For understanding content of the present invention further, the present invention is described in detail by reference to the accompanying drawings.
Composition graphs 5, Fig. 6 and Fig. 7, the tight axial impeller of a kind of latch of the present invention, comprise blade, nose cone 106 and be arranged on the blind hole 102 of impeller 1 rear, the axis of blind hole 102 and the dead in line of impeller 1, impeller 1 rear offers one or more narrow groove 104 equably, one end of narrow groove 104 extends to the end of impeller 1, the other end processes the circular hole that diameter is greater than narrow groove 104 width, nose cone 106 profile is streamlined, the material of impeller 1 is aluminum or aluminum alloy, as preferred version of the present invention, narrow groove 104 is set to 3 or 4 or 6.
Composition graphs 8, Fig. 9, Figure 10, Figure 11 and Figure 14, the linkage structure of a kind of impeller of the present invention and turbine shaft, comprise one end and be fixed on the turbine shaft 2 on turbine 6, the tight axial impeller 1 of above-mentioned latch and thrust housing 7, axle head 202 and blind hole 102 interference fit on impeller 1 of turbine shaft 2, turbine shaft 2 and corresponding section, narrow groove 104 position are provided with ring-shaped step 204, the inner chamber 701 of thrust housing 7 is taper, inner chamber 701 is set in the rear of impeller 1, and this rear compressive deformation, snap in ring-shaped step 204, the rear end face of impeller 1 is pressed on thrust housing 7.The axle head 202 of turbine shaft 2 is processed with a pair or more of parallel surface 203, form a non-circular geometric cross section (as shown in figure 11), distance between often pair of parallel surface 203 is all less than the aperture of blind hole 102, and the length of parallel surface 203 must be appropriate, exhaust during for installing, ensures the axle head 202 of turbine shaft 2 and blind hole 102 interference fit of impeller 1 simultaneously.The axle head 202 of turbine shaft 2 and the blind hole 102 of impeller 1 are all processed with chamfering, and the material hardness of turbine shaft 2 is greater than the material hardness of impeller 1.
Below in conjunction with embodiment, the invention will be further described.
Embodiment 1
The tight axial impeller of a kind of latch of the present embodiment, comprise blade, nose cone 106 and be arranged on the blind hole 102 of impeller 1 rear, the axis of blind hole 102 and the dead in line of impeller 1, impeller 1 rear offers 3 narrow grooves 104 equably, one end of narrow groove 104 extends to the end of impeller 1, and the other end processes the circular hole that diameter is greater than narrow groove 104 width, and circular hole is conducive to the compressive deformation of impeller 1 rear, make assembling convenient, efficiency is higher.Narrow groove 104 is the space that the rear of impeller 1 provides compressive deformation, and moving axially to inlet end when restriction impeller 1 works, thus avoids the risk of wiping shell.Compared with the impeller 1 being threaded blind hole, the tight axial impeller of a kind of latch of the present embodiment eliminates hexagon nose 105(that impeller 1 needs because of assembling as shown in Figures 2 and 3), impeller 1 in the present embodiment is by suitable frock press-in turbine shaft 2 and thrust housing 7, therefore the vane inlet inside/outside diameter size of impeller 1 can reduce, and the flow that do not have the greatest impact, as shown in Figure 5, what dotted line represented is that traditional impeller 1 designs, and solid line represents the Curve guide impeller of the present embodiment.Nose cone 106 profile is streamlined, not only can reduce gas flow loss, the stall event that blade occurs in import outer radius can also be avoided, and then the spendable effective coverage of pressurized machine and performance are improved, in addition, the various stress that fairshaped nose cone 106 pairs of centrifugal force bring make moderate progress, and effectively extend the fatigue life of impeller 1.The material of impeller 1 is aluminium, and the quality of aluminium is light, good processability.In addition, Figure 13 is the stress analysis figure of the tight axial impeller of a kind of latch of the present embodiment, and as seen from the figure, the position of blind hole 102, away from maximum stress district 103, makes the working life of impeller 1 compared with the impeller 1 of band blind screw hole, basically identical.
A kind of impeller of the present embodiment and the linkage structure of turbine shaft, comprise one end and be fixed on the turbine shaft 2 on turbine 6, the tight axial impeller 1 of above-mentioned latch and thrust housing 7, rotate in order to impeller 1 can be made, axle head 202 and blind hole 102 interference fit on impeller 1 of turbine shaft 2, through calculating and experiment, only need the external diameter aperture of blind hole 102 being suitably less than turbine shaft 2.Turbine shaft 2 and corresponding section, narrow groove 104 position are provided with ring-shaped step 204; when pressurized machine works; impeller 1 often can be greater than impeller 1 inlet pressure due to backside gas pressure, and now impeller 1 may move to its inlet end, if mobile excessive; impeller 1 will contact with pressure shell, and wear and tear and damage; for preventing the generation of problems, the inner chamber 701 of thrust housing 7 is designed to taper, and inner chamber 701 is set in the rear of impeller 1; and this rear compressive deformation, snap in ring-shaped step 204.According to the demand of moment of torsion, the axle head 202 of turbine shaft 2 is processed with a pair or more of parallel surface 203, form a non-circular geometric cross section (as shown in figure 11), specifically in the present embodiment, parallel surface 203 is processed with a pair, distance between often pair of parallel surface 203 is all less than the aperture of blind hole 102, and the length of parallel surface 203 must be appropriate, exhaust during for installing, ensure the axle head 202 of turbine shaft 2 and blind hole 102 interference fit of impeller 1, the material hardness of turbine shaft 2 is greater than the material hardness of impeller 1 simultaneously.As shown in figure 12, on the one hand, when turbine shaft 2 coordinates with impeller 1, blind hole 102 interior section material produces plastic deformation, is forced to expand, and non-contact segment is still in elastic state, original size is unaffected, the inner diameter shape of blind hole 102 has not been circular under the effect of interference power, the possibility not getting loose between turbine shaft 2 and impeller 1 or slide, and transmitting torque makes impeller 1 rotate effectively; On the other hand, when impeller 1 is loaded onto turbine shaft 2, the air in blind hole 102 can be discharged via parallel surface 203 and the space in blind hole 102, avoids the difficulty causing fit on.Because impeller 1 is completely fixed on turbine shaft 2, the rear end face of impeller 1 is pressed on thrust housing 7, makes whole rotor assembly form one securely, does not need employing to be threaded, can not bring the amount of unbalance that extra screw-threaded coupling produces.The axle head 202 of turbine shaft 2 and the blind hole 102 of impeller 1 are all processed with chamfering, are convenient to the installation of turbine shaft and impeller.Because impeller 1 and the processing dimension of turbine shaft 2 limit little, a kind of impeller of the present embodiment and the linkage structure of turbine shaft can be applied on the very little impeller of external diameter 1.
Embodiment 2
The basic structure of the tight axial impeller of a kind of latch of the present embodiment and the linkage structure of this impeller and turbine shaft is with embodiment 1, difference is: impeller 1 rear offers 4 narrow grooves 104 equably, the material of impeller 1 is aluminum alloy, the axle head 202 of turbine shaft 2 is processed with two pairs of parallel surfaces 203.
Embodiment 3
The basic structure of the tight axial impeller of a kind of latch of the present embodiment and the linkage structure of this impeller and turbine shaft is with embodiment 1, difference is: impeller 1 rear offers 6 narrow grooves 104 equably, the material of impeller 1 is aluminum alloy, the axle head 202 of turbine shaft 2 is processed with three pairs of parallel surfaces 203.
During intermediate rotor assembly general assembly in the present invention, by impeller 1 vertical depression, turbine shaft 2 is made to enter blind hole 102, because the axle head 202 of blind hole 102 and turbine shaft 2 is equipped with chamfering, therefore turbine shaft 2 is easy to enter blind hole 102, and make the material generation plastic deformation in blind hole 102; Now, the rear of impeller 1 enters the inner chamber 701 of thrust housing 7, extrusion, and snaps in ring-shaped step 204.The rear of impeller 1 relies on the inner chamber 701 of spring-back force and thrust housing 7 to closely cooperate, and its end face is pressed on thrust housing 7, makes whole rotor assembly substantially form one securely.The linkage structure of the tight axial impeller of a kind of latch of the present invention and this impeller and turbine shaft, not only impeller 1 and turbine shaft 2 easy processing, assemble that amount of unbalance that is quick, rotor assembly is low, high financial profit, and impeller 1 limits little with the processing dimension of turbine shaft 2, can be applied on the very little impeller of external diameter 1, technological scheme of the present invention effectively can be improved the performance of pressurized machine and extend fatigue life simultaneously.
Schematically above be described the present invention and mode of execution thereof, this description does not have restricted, and also just one of the embodiments of the present invention shown in accompanying drawing, actual structure is not limited thereto.So, if those of ordinary skill in the art enlightens by it, when not departing from the invention aim, designing the mode of structure similar to this technological scheme and embodiment without creationary, all should protection scope of the present invention be belonged to.
Claims (9)
1. the linkage structure of an impeller and turbine shaft, it is characterized in that: comprise one end and be fixed on turbine shaft (2), impeller (1) and thrust housing (7) on turbine (6), described impeller (1) comprises blade, nose cone (106) and is arranged on the blind hole (102) of impeller (1) rear, the axis of described blind hole (102) and the dead in line of impeller (1), described impeller (1) rear offers the narrow groove (104) of one or more equably; Axle head (202) and blind hole (102) interference fit on impeller (1) of described turbine shaft (2), the axle head (202) of described turbine shaft (2) is processed with more than one pair of parallel surface (203), form a non-circular geometric cross section, described turbine shaft (2) and narrow groove (104) corresponding section, position are provided with ring-shaped step (204), the inner chamber (701) of described thrust housing (7) is taper, described inner chamber (701) is set in the rear of impeller (1), and this rear compressive deformation, snap in ring-shaped step (204).
2. the linkage structure of a kind of impeller according to claim 1 and turbine shaft, is characterized in that: one end of described narrow groove (104) extends to the end of impeller (1), and the other end processes the circular hole that diameter is greater than narrow groove (104) width.
3. the linkage structure of a kind of impeller according to claim 2 and turbine shaft, is characterized in that: described nose cone (106) profile is streamlined.
4. the linkage structure of a kind of impeller according to claim 3 and turbine shaft, is characterized in that: described narrow groove (104) is set to 3 or 4 or 6.
5. the linkage structure of a kind of impeller according to claim 4 and turbine shaft, is characterized in that: the material of described impeller (1) is aluminum or aluminum alloy.
6. a kind of impeller according to claim 1 to 5 any one and the linkage structure of turbine shaft, is characterized in that: the distance between the parallel surface (203) described in often pair is all less than the aperture of blind hole (102), exhaust during for installing.
7. the linkage structure of a kind of impeller according to claim 6 and turbine shaft, is characterized in that: the rear end face of described impeller (1) is pressed on thrust housing (7).
8. the linkage structure of a kind of impeller according to claim 7 and turbine shaft, is characterized in that: the axle head (202) of described turbine shaft (2) and the blind hole (102) of impeller (1) are all processed with chamfering.
9. the linkage structure of a kind of impeller according to claim 8 and turbine shaft, is characterized in that: the material hardness of described turbine shaft (2) is greater than the material hardness of impeller (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310336424.0A CN103362557B (en) | 2013-08-05 | 2013-08-05 | The linkage structure of a kind of impeller and turbine shaft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310336424.0A CN103362557B (en) | 2013-08-05 | 2013-08-05 | The linkage structure of a kind of impeller and turbine shaft |
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| CN103362557A CN103362557A (en) | 2013-10-23 |
| CN103362557B true CN103362557B (en) | 2016-04-20 |
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| CN201310336424.0A Expired - Fee Related CN103362557B (en) | 2013-08-05 | 2013-08-05 | The linkage structure of a kind of impeller and turbine shaft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3712438A4 (en) * | 2017-11-15 | 2021-04-21 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Compressor impeller, compressor, and turbocharger |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9371835B2 (en) * | 2013-07-19 | 2016-06-21 | Praxair Technology, Inc. | Coupling for directly driven compressor |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1430308A (en) * | 1973-04-06 | 1976-03-31 | Woollenweber W E | Rotatable assembly |
| JPS56159600A (en) * | 1980-05-09 | 1981-12-08 | Mitsubishi Heavy Ind Ltd | Impeller fitting structure |
| KR0154105B1 (en) * | 1989-10-30 | 1998-11-16 | 제랄드 피. 루니 | Turbocharger compressor wheel assembly with boreless hub compressor wheel |
| CN200949582Y (en) * | 2006-09-06 | 2007-09-19 | 中国船舶重工集团公司第七�三研究所 | Clamp hub |
| US20100047072A1 (en) * | 2006-11-29 | 2010-02-25 | Borgwarner Inc. | Turbocharger |
| CN102619781A (en) * | 2012-04-09 | 2012-08-01 | 三一能源重工有限公司 | Device and method for connecting impeller with shaft of compressor |
| CN203441545U (en) * | 2013-08-05 | 2014-02-19 | 汉美综合科技（常州）有限公司 | Bolt shaft tightening impeller and connection structure of impeller and turbine shaft |
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2013
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3712438A4 (en) * | 2017-11-15 | 2021-04-21 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Compressor impeller, compressor, and turbocharger |
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