CN103362557A - Inserting pin tightening shaft type impeller and connecting structure of impeller and turbine shaft - Google Patents
Inserting pin tightening shaft type impeller and connecting structure of impeller and turbine shaft Download PDFInfo
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- CN103362557A CN103362557A CN2013103364240A CN201310336424A CN103362557A CN 103362557 A CN103362557 A CN 103362557A CN 2013103364240 A CN2013103364240 A CN 2013103364240A CN 201310336424 A CN201310336424 A CN 201310336424A CN 103362557 A CN103362557 A CN 103362557A
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Abstract
The invention discloses an inserting pin tightening shaft type impeller and a connecting structure of the impeller and a turbine shaft, and belongs to the technical field of supercharger. The impeller comprises a vane, a nose cone and a blind hole formed in the tail end of the impeller. More than one narrow groove is evenly formed in the tail end of the impeller. One ends of the narrow grooves extend to the tail end of the impeller, and circular holes with the diameters larger than the widths of the narrow grooves are machined in the other ends of the narrow grooves. The connecting structure of the impeller and the turbine shaft comprises the turbine shaft with one end fixedly connected with a turbine, the impeller and a pushing stopping sleeve. The shaft end of the turbine shaft is in interference fit with the blind hole in the impeller. The turbine shaft is provided with annular steps on the portions corresponding to the narrow grooves. An inner cavity of the pushing stopping sleeve is in a cone shape. The inner cavity is arranged at the tail end of the impeller in a sleeved mode. The tail end deforms under pressure and is clamped in the annular steps. According to the connecting structure, the impeller and the turbine shaft are easy to machine and quick to assemble, unbalance amount of a rotor assembly is low, economic benefit is high, machining size limitation of the impeller and the turbine shaft is low, and the connecting structure can be used for the impeller with the small outer 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 interior latch mandrel formula impeller of a kind of pressurized machine and the linkage structure of this impeller and turbine shaft.
Background technique
Pressurized machine is to improve to enter the interior inflammable mixture of cylinder or the device of air pressure.As shown in Figure 4, the action basic principle of pressurized machine is, turbine (6) utilizes the power generation rotation in the engine exhaust gas, and this motion passes to the impeller (1) that is connected in turbine shaft (2) the other end with portion of energy through turbine shaft (2), when impeller (1) rotates in pressurized machine, will promote (or compression) ambient air and enter internal-combustion engine.Because the effect of compression, the density of air is improved, thereby has improved the air inflow in the cylinder of internal-combustion engine, so that power improves and efficient burning becomes 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 formed by impeller (1) and turbine (6), keep stable, and limit its axial displacement, avoid rubbing with volute or pressure shell, cause damage.
Because the speed of turbosupercharger running, be according to the moment of torsion of engine demand and emission request and fixed, and under various rotating speeds, these requirements are along with the operating mode instant changes.These variations are so that the being forced to property adjustment between various high low speed of turbocharger rotor assembly, this means that impeller and turbine inside bearing violent STRESS VARIATION, cause material mechanical tired.This fatigue can form at first at the region of high stress, causes the part material to peel off, so that turbosupercharger can't work on.For the life-span that prolongs turbosupercharger increases reliability, just must analyze each component, find out heavily stressed part, manage to improve.Experience and the analysis showed that the axis hole of impeller is to 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 two kinds of Placements commonly used are arranged at present: through hole and blind hole.Passing hole type is simple in structure, such as Chinese patent application numbers 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 the Compressor Technology field, the connection set of compressor impeller and axle comprises impeller, impeller rotates and includes the impeller stem axle with outer surface that extends at axial direction around axis, outer surface has tapered profiles and have non-circular symmetrical profiles in the cross section perpendicular to axis within comprising the cross section of axis, the impeller stem axle also comprises the opening that axial direction extends; Gear shaft, gear shaft are included in the upwardly extending hole of described axle, and its mesopore is for to accept the impeller stem axle and to mesh the impeller stem axle when gear shaft rotates; Bolt is inserted in and is used in impeller opening and the hole impeller is connected to gear shaft; Wherein, bolt and hole must firm thread engagement by executing.This application case must firm screw thread mesh bolt and gear shaft by executing, guaranteed the reliability of 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 the impeller, and bolt easily produces mechanical fatigue, has reduced working life.
By as seen 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, often use the technology of blind hole impeller, for example the people such as Jean Luc is at U.S. Patent number: propose in 4986733 without the passing hole type Impeller Design, as shown in Figure 1, it is closely to link together with the thread (201) on internal thread (101) and the turbine shaft (2), this design that is threaded connection impeller (1), manufacturing to parts is relatively consuming time and expensive, because need to all need to process accurate screw thread on impeller (1) and turbine shaft (2).Simultaneously, because various processing dimensions, so that this Placement can't be applied on the less impeller of external diameter (1).Moreover because rotor assembly is to finish fixingly by screw thread, the mode of this Placement double thread and locking requires very high, and reason is to avoid the amount of unbalance of rotor assembly excessive.Therefore, a kind of new impeller connection theory is suggested, and according to this theory, impeller has blind hole, but without screw thread.Therefore, the 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 the prior art is excessive, the life-span of pressurized machine is low, poor reliability, and with the mode that is threaded, requirement on machining accuracy is high, make consuming time, expensive, and can not be applied to the deficiency on the less impeller of external diameter, the linkage structure of a kind of latch mandrel formula impeller 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, economic benefit is high, and the restriction of the processing dimension of impeller and turbine shaft is little, can be applied on the very little impeller of external diameter, technological scheme of the present invention can effectively be improved the performance of pressurized machine and prolong fatigue life simultaneously.
2. technological scheme
For achieving the above object, technological scheme provided by the invention is:
A kind of latch mandrel formula impeller of the present invention comprises blade, nose cone and is arranged on the blind hole of impeller rear, the axis of described blind hole and the dead in line of impeller, and described impeller rear offers the narrow groove of one or more equably.
Further improve as the present invention, an end of described narrow groove extends to the end of impeller, and the other end processes diameter greater than the circular hole of 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 that an end is fixed on the turbine shaft on the turbine, above-mentioned latch mandrel formula impeller and thrust housing, the axle head of described turbine shaft and the blind hole interference fit on the impeller, be processed with a pair or more of parallel surface on the axle head of described turbine shaft, form a non-circular geometric cross section, described turbine shaft and corresponding section, narrow groove position 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 snaps in the ring-shaped step.
Further improve as the present invention, the distance between described every pair of parallel surface is all less than the aperture of blind hole, the exhaust when being used for installing.
Further improve as the present invention, the rear end face of described impeller is pressed on the thrust housing.
Further improve as the present invention, all be processed with chamfering on the axle head of described turbine shaft and the blind hole of impeller.
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, compare with existing known technology, have following remarkable result:
(1) linkage structure of a kind of latch mandrel formula impeller of the present invention and this impeller and turbine shaft, the impeller rear offers the narrow groove of one or more equably, turbine shaft and corresponding section, narrow groove position 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 the ring-shaped step, narrow groove provides the space of compressive deformation for the rear of impeller, restriction impeller when work moves axially to inlet end, thereby avoided wiping the risk of shell;
(2) linkage structure of a kind of latch mandrel formula impeller of the present invention and this impeller and turbine shaft, the axle head of turbine shaft and the blind hole interference fit on the impeller, the material hardness of turbine shaft is greater than the material hardness of impeller, be processed with a pair or more of parallel surface on the axle head of turbine shaft, distance between the every pair of parallel surface is all less than the aperture of blind hole, on the one hand, when turbine shaft cooperates with impeller, the plastic deformation of blind hole interior section material production, be forced to expand, and contact segment still is not in elastic state, and transmitting torque makes wheel rotation effectively; On the other hand, when impeller was loaded onto turbine shaft, the air in the blind hole can be discharged via the space in parallel surface and the blind hole, avoids causing the difficulty of fit on;
(3) linkage structure of a kind of latch mandrel formula impeller 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 diameter greater than the circular hole of narrow well width, and this circular hole is conducive to the compressive deformation of impeller rear, so that assemble conveniently, efficient is higher;
(4) linkage structure of a kind of latch mandrel formula impeller of the present invention and this impeller and turbine shaft, the nose cone profile is streamlined, not only can reduce the gas flow loss, the stall phenomenon that can also avoid blade to occur in the import outer radius, 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 has effectively prolonged the fatigue life of impeller;
(5) linkage structure of a kind of latch mandrel formula impeller of the present invention and this impeller and turbine shaft, because impeller is completely fixed on the turbine shaft, the rear end face of impeller is pressed on the thrust housing, make whole rotor assembly form securely one, do not need to adopt and be threaded the amount of unbalance that can not bring extra screw-threaded coupling to produce;
(6) linkage structure of a kind of latch mandrel formula impeller of the present invention and this impeller and turbine shaft all is processed with chamfering on the axle head of turbine shaft and the blind hole of impeller, is convenient to the installation of turbine shaft and impeller;
(7) linkage structure of a kind of latch mandrel formula impeller of the present invention and this impeller and turbine shaft, the processing dimension restriction of impeller and turbine shaft is little, can be applied on the very little impeller of external diameter.
Description of drawings
Fig. 1 is the impeller of pressurized machine in the prior art and the linkage structure schematic diagram of turbine shaft;
Fig. 2 is the blade wheel structure schematic diagram of pressurized machine in the 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 the prior art;
Fig. 5 is the sectional structure schematic diagram of a kind of latch mandrel formula impeller of the present invention;
Fig. 6 is the local amplification view of the rear of a kind of latch mandrel formula impeller 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 among 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 among the present invention;
Figure 11 is 3 kinds of schematic cross-sections of turbine shaft axle head among the present invention;
Figure 12 is the structural representation that impeller cooperates with the turbine shaft axle head among the present invention;
Figure 13 is the stress analysis figure of a kind of latch mandrel formula impeller of the present invention;
Figure 14 is the local cross-sectional schematic of amplifying of the linkage structure of impeller of the present invention and turbine shaft.
Label declaration in the 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 further understanding content of the present invention, by reference to the accompanying drawings the present invention is described in detail.
In conjunction with Fig. 5, Fig. 6 and Fig. 7, a kind of latch mandrel formula impeller of the present invention, comprise blade, nose cone 106 and be arranged on the blind hole 102 of impeller 1 rear, the dead in line of the axis of blind hole 102 and impeller 1, impeller 1 rear offers the narrow groove 104 of one or more equably, one end of narrow groove 104 extends to the end of impeller 1, the other end processes diameter greater than the circular hole of narrow groove 104 width, nose cone 106 profiles are 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.
In conjunction with Fig. 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 that an end is fixed on the turbine shaft 2 on the turbine 6, above-mentioned latch mandrel formula impeller 1 and thrust housing 7, the axle head 202 of turbine shaft 2 and blind hole 102 interference fit on the impeller 1, turbine shaft 2 is provided with ring-shaped step 204 with corresponding section, narrow groove 104 position, 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 the ring-shaped step 204, the rear end face of impeller 1 is pressed on the thrust housing 7.Be processed with a pair or more of parallel surface 203 on the axle head 202 of turbine shaft 2, form a non-circular geometric cross section (as shown in figure 11), the distance that the every pair of parallel surface is 203 is all less than the aperture of blind hole 102, and the length of parallel surface 203 must be appropriate, exhaust when being used for installing guarantees the axle head 202 of turbine shaft 2 and blind hole 102 interference fit of impeller 1 simultaneously.All be processed with chamfering on the axle head 202 of turbine shaft 2 and the blind hole 102 of impeller 1, the material hardness of turbine shaft 2 is greater than the material hardness of impeller 1.
The invention will be further described below in conjunction with embodiment.
A kind of latch mandrel formula impeller of the present embodiment, comprise blade, nose cone 106 and be arranged on the blind hole 102 of impeller 1 rear, the dead in line of the axis of blind hole 102 and 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 diameter greater than the circular hole of narrow groove 104 width, and circular hole is conducive to the compressive deformation of impeller 1 rear, so that assemble conveniently, efficient is higher.Narrow groove 104 provides the space of compressive deformation for the rear of impeller 1, to the moving axially of inlet end, thereby avoided wiping the risk of shell during the work of restriction impeller 1.Compare with the impeller 1 that is threaded blind hole, a kind of latch mandrel formula impeller of the present embodiment has been cancelled hexagon nose 105(that impeller 1 needs because of assembling as shown in Figures 2 and 3), impeller 1 in the present embodiment is to be pressed into turbine shaft 2 and thrust housing 7 by suitable frock, therefore the blade import inside/outside diameter size of impeller 1 can reduce, and flow does not have the greatest impact, as shown in Figure 5, what dotted line represented is traditional impeller 1 design, and solid line represents the improvement design of the present embodiment.Nose cone 106 profiles are streamlined, not only can reduce the gas flow loss, the stall phenomenon that can also avoid blade to occur in the import outer radius, and then the spendable effective coverage of pressurized machine and performance are improved, in addition, the various stress that 106 pairs of centrifugal force of fairshaped nose cone bring make moderate progress, and have effectively prolonged 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 a kind of latch mandrel formula impeller of the present embodiment, and as seen from the figure, the position of blind hole 102 is away from maximum stress district 103, so that compare with the impeller 1 with blind screw hole the working life of impeller 1, basically identical.
A kind of impeller of the present embodiment and the linkage structure of turbine shaft, comprise that an end is fixed on the turbine shaft 2 on the turbine 6, above-mentioned latch mandrel formula impeller 1 and thrust housing 7, for impeller 1 is rotated, the axle head 202 of turbine shaft 2 and blind hole 102 interference fit on the impeller 1, through calculating and experiment, only need the aperture of blind hole 102 is suitably got final product less than the external diameter of turbine shaft 2.Turbine shaft 2 is provided with ring-shaped step 204 with corresponding section, narrow groove 104 position; when pressurized machine is worked; impeller 1 is because backside gas pressure often can be greater than impeller 1 inlet pressure, and this moment, impeller 1 may move to its inlet end, if mobile excessive; impeller 1 will contact, wear and tear and damage with pressure shell; 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 snaps in the ring-shaped step 204.Demand according to moment of torsion, be processed with a pair or more of parallel surface 203 on the axle head 202 of turbine shaft 2, 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 of, the distance that the every pair of parallel surface is 203 is all less than the aperture of blind hole 102, and the length of parallel surface 203 must be appropriate, exhaust when being used for installing, guarantee simultaneously blind hole 102 interference fit of axle head 202 with the impeller 1 of turbine shaft 2, the material hardness of turbine shaft 2 is greater than the material hardness of impeller 1.As shown in figure 12, on the one hand, when turbine shaft 2 cooperates with impeller 1, blind hole 102 interior section material production plastic deformations be forced to expand, and contact segment still are not in elastic state, original size is unaffected, the internal diameter shape of blind hole 102 has not been circular under the effect of interference power, the possibility that does not get loose or slide between turbine shaft 2 and the impeller 1, and transmitting torque rotates impeller 1 effectively; On the other hand, when impeller 1 was loaded onto turbine shaft 2, the air in the blind hole 102 can be discharged via parallel surface 203 and the space in the blind hole 102, avoids causing the difficulty of fit on.Because impeller 1 is completely fixed on the turbine shaft 2, the rear end face of impeller 1 is pressed on the thrust housing 7, makes whole rotor assembly form securely one, does not need to adopt to be threaded the amount of unbalance that can not bring extra screw-threaded coupling to produce.All be processed with chamfering on the axle head 202 of turbine shaft 2 and the blind hole 102 of impeller 1, be convenient to the installation of turbine shaft and impeller.Because impeller 1 is little with the processing dimension restriction of turbine shaft 2, 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.
The basic structure of a kind of latch mandrel formula impeller 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, is processed with two pairs of parallel surfaces 203 on the axle head 202 of turbine shaft 2.
The basic structure of a kind of latch mandrel formula impeller 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, is processed with three pairs of parallel surfaces 203 on the axle head 202 of turbine shaft 2.
During intermediate rotor assembly general assembly among the present invention, with impeller 1 vertical depression, make turbine shaft 2 enter blind hole 102, because be equipped with chamfering on the axle head 202 of blind hole 102 and turbine shaft 2, therefore turbine shaft 2 is easy to enter blind hole 102, and make material generation plastic deformation in the blind hole 102; At this moment, the rear of impeller 1 enters the inner chamber 701 of thrust housing 7, extrusion, and snap in the 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 the thrust housing 7, makes whole rotor assembly basically form securely one.The linkage structure of a kind of latch mandrel formula impeller of the present invention and this impeller and turbine shaft, not only impeller 1 and turbine shaft 2 easy processings, assembling are fast, the amount of unbalance of rotor assembly is low, economic benefit is high, and impeller 1 is little with the processing dimension restriction of turbine shaft 2, can be applied on the very little impeller of external diameter 1, technological scheme of the present invention can effectively be improved the performance of pressurized machine and prolong fatigue life simultaneously.
Below schematically the present invention and mode of execution thereof are described, this description does not have restricted, and shown in the accompanying drawing also is one of embodiments of the present invention, and actual structure is not limited to this.So, if those of ordinary skill in the art is enlightened by it, in the situation that do not break away from the invention aim, without the creationary mode of structure similar to this technological scheme and the embodiment of designing, all should belong to protection scope of the present invention.
Claims (10)
1. latch mandrel formula impeller, comprise blade, nose cone (106) and be arranged on the blind hole (102) of impeller (1) rear, the dead in line of the axis of described blind hole (102) and impeller (1) is characterized in that: described impeller (1) rear offers the narrow groove (104) of one or more equably.
2. a kind of latch mandrel formula impeller according to claim 1, it is characterized in that: an end of described narrow groove (104) extends to the end of impeller (1), and the other end processes diameter greater than the circular hole of narrow groove (104) width.
3. a kind of latch mandrel formula impeller according to claim 2, it is characterized in that: described nose cone (106) profile is streamlined.
4. a kind of latch mandrel formula impeller according to claim 3, it is characterized in that: described narrow groove (104) is set to 3 or 4 or 6.
5. a kind of latch mandrel formula impeller according to claim 4, it is characterized in that: the material of described impeller (1) is aluminum or aluminum alloy.
6. the linkage structure of an impeller and turbine shaft, it is characterized in that: comprise that an end is fixed on the turbine shaft (2) on the turbine (6), the described impeller of claim 1 to 5 any one (1) and thrust housing (7), blind hole (102) interference fit on the axle head (202) of described turbine shaft (2) and the impeller (1), be processed with a pair or more of parallel surface (203) on the axle head (202) of described turbine shaft (2), form a non-circular geometric cross section, described turbine shaft (2) is provided with ring-shaped step (204) with narrow groove (104) corresponding section, position, 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 snaps in the ring-shaped step (204).
7. the linkage structure of a kind of impeller according to claim 6 and turbine shaft is characterized in that: the distance between described every pair of parallel surface (203) is all less than the aperture of blind hole (102), the exhaust when being used for installing.
8. the linkage structure of a kind of impeller according to claim 7 and turbine shaft, it is characterized in that: the rear end face of described impeller (1) is pressed on the thrust housing (7).
9. the linkage structure of a kind of impeller according to claim 8 and turbine shaft is characterized in that: all be processed with chamfering on the axle head (202) of described turbine shaft (2) and the blind hole (102) of impeller (1).
10. the linkage structure of a kind of impeller according to claim 9 and turbine shaft, it 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 |
|---|---|---|---|
| CN201310336424.0A CN103362557B (en) | 2013-08-05 | 2013-08-05 | The linkage structure of a kind of impeller and turbine shaft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Publication Number | Publication Date |
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| CN103362557A true CN103362557A (en) | 2013-10-23 |
| CN103362557B CN103362557B (en) | 2016-04-20 |
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| Application Number | Title | Priority Date | Filing Date |
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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 (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109944643A (en) * | 2013-07-19 | 2019-06-28 | 普莱克斯技术有限公司 | Connector for the compressor directly driven |
| US11143199B2 (en) | 2017-11-15 | 2021-10-12 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Compressor impeller, compressor, and turbocharger |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US3961867A (en) * | 1973-04-06 | 1976-06-08 | Holset Engineering Company Limited | Rotatable assembly with rotor abraded by seal ring |
| JPS56159600A (en) * | 1980-05-09 | 1981-12-08 | Mitsubishi Heavy Ind Ltd | Impeller fitting structure |
| US4986733A (en) * | 1989-10-30 | 1991-01-22 | Allied-Signal, Inc. | 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 |
| CN101535600A (en) * | 2006-11-29 | 2009-09-16 | 博格华纳公司 | 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 |
-
2013
- 2013-08-05 CN CN201310336424.0A patent/CN103362557B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3961867A (en) * | 1973-04-06 | 1976-06-08 | Holset Engineering Company Limited | Rotatable assembly with rotor abraded by seal ring |
| JPS56159600A (en) * | 1980-05-09 | 1981-12-08 | Mitsubishi Heavy Ind Ltd | Impeller fitting structure |
| US4986733A (en) * | 1989-10-30 | 1991-01-22 | Allied-Signal, Inc. | 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 |
| CN101535600A (en) * | 2006-11-29 | 2009-09-16 | 博格华纳公司 | 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 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109944643A (en) * | 2013-07-19 | 2019-06-28 | 普莱克斯技术有限公司 | Connector for the compressor directly driven |
| US11143199B2 (en) | 2017-11-15 | 2021-10-12 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Compressor impeller, compressor, and turbocharger |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103362557B (en) | 2016-04-20 |
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