CN209228681U - The thrust disc component of turbocompressor - Google Patents
The thrust disc component of turbocompressor Download PDFInfo
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- CN209228681U CN209228681U CN201821889301.4U CN201821889301U CN209228681U CN 209228681 U CN209228681 U CN 209228681U CN 201821889301 U CN201821889301 U CN 201821889301U CN 209228681 U CN209228681 U CN 209228681U
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Abstract
The utility model relates to turbocompressors, more particularly to a kind of thrust disc component of turbocompressor, including thrust disc and shaft, the shaft is multi-diameter shaft, including the first rank axis, second-order axis, third rank axis and fourth order axis, the thrust disc includes main thrust disk and secondary thrust disc, and the pair thrust disc is located on second-order axis, and secondary thrust disc and shaft are integrally formed；The main thrust disk is located on third rank axis, is fixed by screw and shaft；It is additionally provided with the annular retaining ring that location collar and location collar lean on the third rank axis, is arranged with bearing on the fourth order axis.By this thrust disc component, the problem of thrust disc in the prior art is prone to wear, loosens can effectively solve, the assembly efficiency of thrust disc component can be improved, extend the service life of thrust disc component.
Description
Technical field
The utility model relates to turbocompressors, more particularly to a kind of thrust disc component of turbocompressor.
Background technique
Thrust disc is in the form of transition fit before and after the front and back thrust disc of turbocompressor, and is connected by key and is mounted on master
On axis, the installation and removal of thrust disc are extremely inconvenient, and installation and removal when easy damaged thrust disc and main shaft contact surface, make
At scrapping for components.If front and back thrust disc is connect using interference fit with main shaft, hot jacket thrust disc is needed, thrust disc is easily led to
Deformation, be unable to ensure the flatness of thrust disc.It is connect if front and back thrust disc is gap-matched with main shaft, easily leads to thrust
Disk can shake in main shaft, increase the shaft vibration of rotor.
In the prior art, it proposes authorization and is disclosed as CN202531477U, authorization publication date is on November 14th, 2012
Chinese utility model patent file, to solve above-mentioned technical problem, technical solution disclosed in the patent document is as follows:
A kind of thrust disc location structure, more precisely for belong to the front and back thrust disc location structure on turbocompressor main shaft comprising
Main shaft and the forward thrust disk and back pressure disk being set on the main shaft, wherein the forward thrust disk and back pressure disk are reducing axis；
Further, the forward and backward thrust disc transition fit is set on the main shaft, and between the forward and backward thrust disc and main shaft
Key connection is respectively adopted；Thrust washer and locking nut are additionally provided on the main shaft to lock the forward and backward thrust disc；It is described
Main shaft is multi-diameter shaft, and the forward thrust disk is positioned on the step position of the main shaft, and axle sleeve, institute are provided between forward and backward thrust disc
It states thrust washer and locking nut is set to the end of the back pressure disk；Clearance fit between the axle sleeve and the main shaft.
Above-mentioned technical proposal is in actual use, it may appear that following problems:
(1) the forward and backward thrust disc transition fit is set on the main shaft, and the forward and backward thrust disc and main shaft it
Between key connection is respectively adopted, since axial thrust can increase extremely, thrust disc is easily loosened, impeller be easy scrape or seriously by
Damage, run stability are poor.
(2) thrust disc is mounted in shaft, due to there are the influence of machining accuracy and assembly precision, thrust disc and shaft
Verticality is poor, and thrust disc is easy uneven wear.
Summary of the invention
In order to solve the above technical problems, the utility model proposes a kind of thrust disc component of turbocompressor, it can be effective
It solves the problems, such as that thrust disc is prone to wear in the prior art, loosen, the assembly efficiency of thrust disc component can be improved, extend thrust
The service life of disk component.
The utility model is realized by using following technical proposals:
The thrust disc component of turbocompressor, including thrust disc and shaft, it is characterised in that: the shaft is multi-diameter shaft,
Including the first rank axis, second-order axis, third rank axis and fourth order axis, the thrust disc includes main thrust disk and secondary thrust disc, institute
It states secondary thrust disc to be located on second-order axis, the pair thrust disc and shaft are integrally formed；The main thrust disk is located at third rank axis
On, main thrust disk is equipped with several through-holes, and screw passes through the through-hole on main thrust disk, main thrust disk is fixed with shaft；It is described
The annular retaining ring for being additionally provided with location collar on third rank axis, leaning with location collar, the annular retaining ring and main thrust disk phase
It is close to, is arranged with bearing on the fourth order axis, the bearing includes transverse bearing and thrust bearing, described thrust bearing one end
It offsets with the radial end face of third rank axis, one end offsets with transverse bearing, for limiting the displacement of shaft in the axial direction.
The diameter of the first rank axis is greater than the diameter of second-order axis, and the diameter of second-order axis is greater than the straight of third rank axis
Diameter, the diameter of third rank axis are greater than the diameter of fourth order axis.
The pair thrust disc is located on second-order axis, and is close to the radial end face of the first rank axis.
The radial end face of the second-order axis is equipped with the hole to match with the through-hole of main thrust disk, and screw passes through main thrust disk
On through-hole, main thrust disk and the radial end face of second-order axis are fixed.
The third rank axis is equipped with first annular positioning groove, and annular retaining ring is correspondingly provided with the second circular orientation groove, fixed
Position retainer ring is set within first annular positioning groove and the second circular orientation groove.
Axle sleeve is additionally provided on second-order axis, the axle sleeve is located between the main thrust disk and secondary thrust disc.
It is clearance fit between the axle sleeve and second-order axis.
The axle sleeve is made of 45# steel.
The main thrust disk is equipped with 6 through-holes.
The main thrust disk is made of stainless steel material.
Compared with prior art, the beneficial effects of the utility model are shown:
1, the secondary thrust disc and shaft are integrally formed, and can be reduced assembly process, improve assembly efficiency, and guarantee secondary thrust
Disk does not loosen in the process of running, ensure that the stability of its operation；Secondly, fixed main thrust disk with shaft by screw,
Utilize location collar and annular retaining ring, it is ensured that the operation stability of main thrust disk and the accuracy of positioning；The bearing includes diameter
To bearing and thrust bearing, for limiting the displacement of shaft in the axial direction.Pass through location collar, annular retaining ring and bearing
It cooperates, multiple reinforcing, positioning is carried out to thrust disc, in addition secondary thrust disc and shaft are integrally formed, it is ensured that thrust disc assembly
When accuracy, it is ensured that thrust disc is not easy to loosen, and reduces impeller and occurs to scrape or the probability that is badly damaged.
2, the diameter of shaft successively successively decreases, convenient for reducing the loss of material and saving space, convenient for assembly.
3, secondary thrust disc is located on second-order axis, and is close to the radial end face of the first rank axis, the radial end face of the first rank axis
Secondary thrust disc is supported, secondary thrust disk detachment or offset are avoided.
4, main thrust disk and the radial end face of second-order axis are fixed, convenient for fixing, keeps assembly simpler, secondly second-order
The radial end face of axis is supported main thrust disk, and main thrust disk is avoided to deviate.
5, the third rank axis is equipped with first annular positioning groove, and annular retaining ring is correspondingly provided with the second circular orientation groove,
Location collar is set within first annular positioning groove and the second circular orientation groove, it is ensured that main thrust disk accurate positioning, it will not
Offset.
6, it is equipped with axle sleeve, protects shaft, reduces friction, reduces vibration, and play the role of axially position.
7, its use is improved for protecting axle sleeve and second-order axis for clearance fit between the axle sleeve and second-order axis
Service life.
Detailed description of the invention
Below in conjunction with specification drawings and specific embodiments, the utility model is described in further detail,
In:
Fig. 1 is the detailed maps of the utility model；
Marked in the figure:
1, the first rank axis, 2, second-order axis, 3, third rank axis, 4, fourth order axis, 5, main thrust disk, 6, secondary thrust disc, 7,
Screw, 8, location collar, 9, annular retaining ring, 10, transverse bearing, 11, thrust bearing, 12, axle sleeve.
Specific embodiment
Embodiment 1
As the utility model basic embodiment, the utility model includes the thrust disc component of turbocompressor, including
Thrust disc and shaft, the shaft are multi-diameter shaft, including the first rank axis 1, second-order axis 2, third rank axis 3 and fourth order axis 4, institute
Stating thrust disc includes main thrust disk 5 and secondary thrust disc 6, and the pair thrust disc 6 is located on second-order axis 2, the pair thrust disc 6 and
Shaft is integrally formed；The main thrust disk 5 is located on third rank axis 3, and main thrust disk 5 is equipped with several through-holes, and screw 7 passes through master
Through-hole on thrust disc 5 fixes main thrust disk 5 with shaft；Location collar 8 and positioning card are additionally provided on the third rank axis 3
The annular retaining ring 9 that circle 8 leans, the annular retaining ring 9 are close to 5 phase of main thrust disk, are arranged with axis on the fourth order axis 4
It holds, the bearing includes transverse bearing 10 and thrust bearing 11, the radial end face of described 11 one end of thrust bearing and third rank axis 3
It offsets, one end offsets with transverse bearing 10, for limiting the displacement of shaft in the axial direction.
Embodiment 2
As one better embodiment of the utility model, the utility model includes the thrust disc component of turbocompressor, packet
Including thrust disc and shaft, the shaft is multi-diameter shaft, including the first rank axis 1, second-order axis 2, third rank axis 3 and fourth order axis 4,
The thrust disc includes main thrust disk 5 and secondary thrust disc 6, and the pair thrust disc 6 is located on second-order axis 2, the pair thrust disc 6
It is integrally formed with shaft；The main thrust disk 5 is located on third rank axis 3, and main thrust disk 5 is equipped with several through-holes, and screw 7 passes through
Through-hole on main thrust disk 5 fixes main thrust disk 5 with shaft；Location collar 8 and positioning are additionally provided on the third rank axis 3
The annular retaining ring 9 that retainer ring 8 leans, the annular retaining ring 9 are close to 5 phase of main thrust disk, are arranged with axis on the fourth order axis 4
It holds, the bearing includes transverse bearing 10 and thrust bearing 11, the radial end face of described 11 one end of thrust bearing and third rank axis 3
It offsets, one end offsets with transverse bearing 10, for limiting the displacement of shaft in the axial direction.
The diameter of the first rank axis 1 is greater than the diameter of second-order axis 2, and the diameter of second-order axis 2 is greater than third rank axis 3
Diameter, the diameter of third rank axis 3 are greater than the diameter of fourth order axis 4.
Secondary thrust disc 6 is located on second-order axis 2, and is close to the radial end face of the first rank axis 1.
The radial end face of the second-order axis 2 is equipped with the hole to match with the through-hole of main thrust disk 5, and screw 7 passes through featured
Through-hole on power disk 5 fixes main thrust disk 5 and the radial end face of second-order axis 2.
Embodiment 3
As another better embodiment of the utility model, the utility model includes the thrust disc component of turbocompressor,
Including thrust disc and shaft, the shaft is multi-diameter shaft, including the first rank axis 1, second-order axis 2, third rank axis 3 and fourth order axis
4, the thrust disc includes main thrust disk 5 and secondary thrust disc 6, and the pair thrust disc 6 is located on second-order axis 2, the pair thrust
Disk 6 and shaft are integrally formed；The main thrust disk 5 is located on third rank axis 3, and main thrust disk 5 is equipped with several through-holes, screw 7
Through-hole on main thrust disk 5 fixes main thrust disk 5 with shaft；Be additionally provided on the third rank axis 3 location collar 8, with
The annular retaining ring 9 that location collar 8 leans, the annular retaining ring 9 are close to 5 phase of main thrust disk, are arranged on the fourth order axis 4
There is bearing, the bearing includes transverse bearing 10 and thrust bearing 11, the radial direction of described 11 one end of thrust bearing and third rank axis 3
End face offsets, and one end offsets with transverse bearing 10, for limiting the displacement of shaft in the axial direction.
The third rank axis 3 is equipped with first annular positioning groove, and annular retaining ring 9 is correspondingly provided with the second circular orientation groove,
Location collar 8 is set within first annular positioning groove and the second circular orientation groove.Fuel feeding is also provided on the bearing
Hole, for being passed through lubricating oil and by lubricating oil directed radial bearing 10 and thrust bearing 11.
Embodiment 4
As the another better embodiment of the utility model, the utility model includes the thrust disc component of turbocompressor,
Including thrust disc and shaft, the shaft is multi-diameter shaft, including the first rank axis 1, second-order axis 2, third rank axis 3 and fourth order axis
4, the thrust disc includes main thrust disk 5 and secondary thrust disc 6, and the pair thrust disc 6 is located on second-order axis 2, the pair thrust
Disk 6 and shaft are integrally formed；The main thrust disk 5 is located on third rank axis 3, and main thrust disk 5 is equipped with several through-holes, screw 7
Through-hole on main thrust disk 5 fixes main thrust disk 5 with shaft；Be additionally provided on the third rank axis 3 location collar 8, with
The annular retaining ring 9 that location collar 8 leans, the annular retaining ring 9 are close to 5 phase of main thrust disk, are arranged on the fourth order axis 4
There is bearing, the bearing includes transverse bearing 10 and thrust bearing 11, the radial direction of described 11 one end of thrust bearing and third rank axis 3
End face offsets, and one end offsets with transverse bearing 10, for limiting the displacement of shaft in the axial direction.
The diameter of the first rank axis 1 is greater than the diameter of second-order axis 2, and the diameter of second-order axis 2 is greater than third rank axis 3
Diameter, the diameter of third rank axis 3 are greater than the diameter of fourth order axis 4, and the diameter of shaft successively successively decreases, convenient for reducing the loss of material
And space is saved, convenient for assembly.
Secondary thrust disc 6 is located on second-order axis 2, and is close to the radial end face of the first rank axis 1.
The radial end face of the second-order axis 2 is equipped with the hole to match with the through-hole of main thrust disk 5, and screw 7 passes through featured
Through-hole on power disk 5 fixes main thrust disk 5 and the radial end face of second-order axis 2.
The third rank axis 3 is equipped with first annular positioning groove, and annular retaining ring 9 is correspondingly provided with the second circular orientation groove,
Location collar 8 is set within first annular positioning groove and the second circular orientation groove.
In the process of running, axial force direction in starting and normal operation can become turbocompressor with load
Change, thrust disc is there are main thrust disk 5 and secondary thrust disc 6, and main thrust disk 5 bears bigger axial force, because of the stress of secondary thrust disc 6
Direction to the left, therefore is arranged the first rank axis 1 in left side and is positioned.Main thrust disk 5 is positioned by second-order axis 2, and right side utilizes
It is fixed in location collar 8 and annular retaining ring 9.
The bearing is equipped with oil supplying hole, for being passed through lubricating oil and by lubricating oil directed radial bearing 10 and thrust bearing
11。
Axle sleeve 12 is additionally provided on second-order axis 2, the axle sleeve 12 is located between the main thrust disk 5 and secondary thrust disc 6；Institute
Stating is clearance fit between axle sleeve 12 and second-order axis 2, and the axle sleeve 12 is made of 45# steel.
The main thrust disk 5 is made of stainless steel material, can be equipped with 6 through-holes above.
In conclusion after those skilled in the art read the utility model file, skill according to the present utility model
Art scheme and technical concept are not necessarily to creative mental labour and other various corresponding conversion schemes for making, belong to practical
Novel protected range.
Claims (10)
1. the thrust disc component of turbocompressor, including thrust disc and shaft, it is characterised in that: the shaft is multi-diameter shaft, packet
The first rank axis (1), second-order axis (2), third rank axis (3) and fourth order axis (4) are included, the thrust disc includes main thrust disk (5)
With secondary thrust disc (6), the pair thrust disc (6) is located on second-order axis (2), and the pair thrust disc (6) and shaft are integrally formed；
The main thrust disk (5) is located on third rank axis (3), and main thrust disk (5) is equipped with several through-holes, and screw (7) passes through main thrust
Through-hole on disk (5) fixes main thrust disk (5) with shaft；It is additionally provided with location collar (8) on the third rank axis (3) and determines
The annular retaining ring (9) that position retainer ring (8) leans, the annular retaining ring (9) are mutually close to main thrust disk (5), the fourth order axis
(4) be arranged with bearing on, the bearing includes transverse bearing (10) and thrust bearing (11), described thrust bearing (11) one end with
The radial end face of third rank axis (3) offsets, and one end offsets with transverse bearing (10), for limiting the position of shaft in the axial direction
It moves.
2. the thrust disc component of turbocompressor according to claim 1, it is characterised in that: the first rank axis (1)
Diameter is greater than the diameter of second-order axis (2), and the diameter of second-order axis (2) is greater than the diameter of third rank axis (3), third rank axis (3)
Diameter be greater than fourth order axis (4) diameter.
3. the thrust disc component of turbocompressor according to claim 2, it is characterised in that: secondary thrust disc (6) is located at the
On second order axis (2), and it is close to the radial end face of the first rank axis (1).
4. the thrust disc component of turbocompressor according to claim 3, it is characterised in that: the second-order axis (2)
Radial end face is equipped with the hole to match with the through-hole of main thrust disk (5), and screw (7) passes through the through-hole on main thrust disk (5), will lead
Thrust disc (5) and the radial end face of second-order axis (2) are fixed.
5. the thrust disc component of turbocompressor according to claim 1 or 4, it is characterised in that: the third rank axis (3)
Equipped with first annular positioning groove, annular retaining ring (9) is correspondingly provided with the second circular orientation groove, and location collar (8) is set to first
Within circular orientation groove and the second circular orientation groove.
6. the thrust disc component of turbocompressor according to claim 5, it is characterised in that: second-order axis is also set on (2)
Have axle sleeve (12), the axle sleeve (12) is located between the main thrust disk (5) and secondary thrust disc (6).
7. the thrust disc component of turbocompressor according to claim 6, it is characterised in that: the axle sleeve (12) and second
It is clearance fit between rank axis (2).
8. the thrust disc component of turbocompressor according to claim 7, it is characterised in that: the axle sleeve (12) uses
45# steel is made.
9. the thrust disc component of turbocompressor according to claim 8, it is characterised in that: on the main thrust disk (5)
Equipped with 6 through-holes.
10. the thrust disc component of turbocompressor according to claim 9, it is characterised in that: the main thrust disk (5) is
Stainless steel material is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821889301.4U CN209228681U (en) | 2018-11-16 | 2018-11-16 | The thrust disc component of turbocompressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821889301.4U CN209228681U (en) | 2018-11-16 | 2018-11-16 | The thrust disc component of turbocompressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209228681U true CN209228681U (en) | 2019-08-09 |
Family
ID=67503248
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821889301.4U Active CN209228681U (en) | 2018-11-16 | 2018-11-16 | The thrust disc component of turbocompressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209228681U (en) |
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2018
- 2018-11-16 CN CN201821889301.4U patent/CN209228681U/en active Active
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