CN106323550A - Novel rotation type sealing ring performance test machine - Google Patents
Novel rotation type sealing ring performance test machine Download PDFInfo
- Publication number
- CN106323550A CN106323550A CN201510370327.2A CN201510370327A CN106323550A CN 106323550 A CN106323550 A CN 106323550A CN 201510370327 A CN201510370327 A CN 201510370327A CN 106323550 A CN106323550 A CN 106323550A
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- main shaft
- sealing ring
- flange seat
- rear end
- bearing
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Abstract
The invention relates to a novel rotation type sealing ring performance test machine, which comprises a headstock and a main shaft. The excircle of the main shaft is provided with a stepped shaft. The two ends of the stepped shaft are sleeved with a bearing. The main shaft passes through sidewalls at the two sides of the headstock. The sidewalls on the two sides of the headstock are provided with bearing pedestals and the bearing is arranged on the bearing pedestals. The rear end of the main shaft is in sleeved connection with a belt pulley. The belt pulley is connected with the output end of a deceleration motor through a belt. The front end of the main shaft is connected with a flange seat, and the front end of the flange seat is connected with an experimental shaft. The front end of the experimental shaft is sleeved with a sealing ring. A cavity is filled with liquid and the main shaft is a hollow spindle. The rear end of the hollow spindle is provided with a cold air inlet port. According to the technical scheme of the invention, the novel rotation type sealing ring performance test machine is simple in structure and convenient in operation. The hollow spindle is adopted and an air-blast cooling device is arranged at the rear end of the hollow spindle. Therefore, the temperature of the bearing during the high-speed rotation of the hollow spindle can be effectively reduced.
Description
Technical field
The present invention relates to a kind of sealing ring performance aircraft, particularly relate to a kind of New Rotary sealing ring performance aircraft.
Background technology
Sealing ring performance aircraft is the sealing property for measuring sealing ring, by main shaft motoring ring test axle high speed rotating, seals cavity and maintains static, and the offset certain to testing axle, observes the permeability phenomenon of sealing ring after spin for some time.It is usually and to carry out testing in the environment of without dust.But existing sealing ring performance aircraft structure is complicated, inconvenient operation, in the course of the work, main shaft and the rotary shaft bearing when high speed rotating can produce high temperature, thus can have impact on test effect and service life.
Summary of the invention
For drawbacks described above, it is an object of the invention to provide a kind of simple in construction, easy to operate, it is possible to reduce the temperature that high speed rotating produces, it is ensured that a kind of New Rotary sealing ring performance aircraft of test requirements document.
For this technical solution adopted in the present invention it is:
Including main spindle box and main shaft, the cylindrical of described main shaft is provided with multidiameter, the two ends of described multidiameter are cased with bearing, described main shaft is through the sidewall of main spindle box both sides, the sidewall of described main spindle box both sides is provided with bearing block, described bearing is arranged on bearing block, the rear end of described main shaft is socketed with belt wheel, described belt wheel is connected with the outfan of reducing motor by belt, the front end of main shaft connects flange seat, the front end of described flange seat connects test axle, the front end of test axle is cased with sealing ring, described sealing ring is within the cavity, described cavity is built with liquid, described main shaft is hollow spindle, the rear end of described hollow spindle is provided with cold wind inlet port.
Further, described flange seat rear end be provided with axial installing hole, the front end of described main shaft is stretched in the axially mounted hole of flange seat, and the sidewall of the rear end of described flange seat is provided with lock-screw for mounting flange seat.
Further, the front end of described flange seat is provided with stepped hole, the outer wall of described stepped hole is provided with some regulation screwed holes, on described regulation screwed hole, regulation screw is installed, the centre of described test axle is provided with flange and is connected with flange seat, the rear end of described flange is provided with boss, and described boss extend in the stepped hole of flange seat front end, and the boss of flange is locked by regulation screw.
Further, described cold wind inlet port is provided with blast cooling device.
Further, described main spindle box is rack-mount.
The invention have the advantage that
Present configuration is simple, easy to operate, by using hollow spindle, and set up blast cooling device in the rear end of hollow spindle, can effectively reduce the temperature that hollow spindle high speed rotating makes bearing produce, by setting up regulation screw on the outer wall of flange seat, rotary shaft is carried out the adjustment of offset, it is possible to meet test requirements document.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention.
Figure 1 is main spindle box, 2 is main shaft, 3 is bearing, 4 is belt wheel, 5 is belt, 6 is reducing motor, 7 is flange seat, 8 is test axle, 9 is sealing ring, 10 is cavity, 11 is liquid, 12 is cold wind inlet port, 13 is lock-screw, 14 is regulation screw, 15 is flange, 16 is boss, 17 is support.
Detailed description of the invention
nullA kind of New Rotary sealing ring performance aircraft，Including main spindle box 1 and main shaft 2，The cylindrical of described main shaft 2 is provided with multidiameter，The two ends of described multidiameter are cased with bearing 3，Described main shaft 2 is through the sidewall of main spindle box 1 both sides，The sidewall of described main spindle box 1 both sides is provided with bearing block，Described bearing 3 is arranged on bearing block，The rear end of described main shaft 2 is socketed with belt wheel 4，Described belt wheel 4 is connected with the outfan of reducing motor 6 by belt 5，The front end of main shaft 2 connects flange seat 7，The front end of described flange seat 7 connects test axle 8，The front end of test axle 8 is cased with sealing ring 9，Described sealing ring 9 is positioned at cavity 10，Described cavity 10 is built with liquid 11，Described main shaft 2 is hollow spindle，The rear end of described hollow spindle is provided with cold wind inlet port 12，Further，Described flange seat 7 rear end be provided with axial installing hole，The front end of described main shaft 2 is stretched in the axially mounted hole of flange seat 7，The sidewall of the rear end of described flange seat 7 is provided with lock-screw 13 for mounting flange seat 7，Further，The front end of described flange seat 7 is provided with stepped hole，The outer wall of described stepped hole is provided with some regulation screwed holes，Regulation screw 14 is installed on described regulation screwed hole，The centre of described test axle 8 is provided with flange 15 and is connected with flange seat 7，The rear end of described flange 15 is provided with boss 16，Described boss 16 extend in the stepped hole of flange seat 7 front end，The boss 16 of flange 15 is locked by regulation screw 14，Further，Described cold wind inlet port 12 is provided with blast cooling device，Further，Described main spindle box 1 is arranged on support 17.
By installing blast cooling device in the rear end of hollow spindle, cold wind is made to reduce, in entering hollow spindle, the heating produced because of high speed rotating, the boss 16 of test axle 8 rear end is arranged in the stepped hole of flange seat 7 front end, and by the regulation screw 14 on stepped hole outer wall, test axle 8 is carried out the adjustment of required offset, with satisfied test demand, the front end face of flange 15 rear end face in the middle part of test axle 8 and flange seat 7 is locked by bolt.
Claims (5)
1. a New Rotary sealing ring performance aircraft, it is characterized in that, including main spindle box and main shaft, the cylindrical of described main shaft is provided with multidiameter, the two ends of described multidiameter are cased with bearing, described main shaft is through the sidewall of main spindle box both sides, the sidewall of described main spindle box both sides is provided with bearing block, described bearing is arranged on bearing block, the rear end of described main shaft is socketed with belt wheel, described belt wheel is connected with the outfan of reducing motor by belt, the front end of main shaft connects flange seat, the front end of described flange seat connects test axle, the front end of test axle is cased with sealing ring, described sealing ring is within the cavity, described cavity is built with liquid, described main shaft is hollow spindle, the rear end of described hollow spindle is provided with cold wind inlet port.
A kind of New Rotary sealing ring performance aircraft the most according to claim 1, it is characterized in that, described flange seat rear end be provided with axial installing hole, the front end of described main shaft is stretched in the axially mounted hole of flange seat, and the sidewall of the rear end of described flange seat is provided with lock-screw for mounting flange seat.
A kind of New Rotary sealing ring performance aircraft the most according to claim 1, it is characterized in that, the front end of described flange seat is provided with stepped hole, the outer wall of described stepped hole is provided with some regulation screwed holes, being provided with regulation screw on described regulation screwed hole, the centre of described test axle is provided with flange and is connected with flange seat, and the rear end of described flange is provided with boss, described boss extend in the stepped hole of flange seat front end, and the boss of flange is locked by regulation screw.
A kind of New Rotary sealing ring performance aircraft the most according to claim 1, it is characterised in that described cold wind inlet port is provided with blast cooling device.
A kind of New Rotary sealing ring performance aircraft the most according to claim 1, it is characterised in that described main spindle box is rack-mount.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510370327.2A CN106323550A (en) | 2015-06-30 | 2015-06-30 | Novel rotation type sealing ring performance test machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510370327.2A CN106323550A (en) | 2015-06-30 | 2015-06-30 | Novel rotation type sealing ring performance test machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106323550A true CN106323550A (en) | 2017-01-11 |
Family
ID=57722719
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510370327.2A Pending CN106323550A (en) | 2015-06-30 | 2015-06-30 | Novel rotation type sealing ring performance test machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106323550A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108613801A (en) * | 2018-04-26 | 2018-10-02 | 安徽皖南新维电机有限公司 | A kind of motor connecting cartridge waterproof washer durability degree test device |
| CN109916705A (en) * | 2018-12-31 | 2019-06-21 | 江苏明珠试验机械有限公司 | High temperature high pressure oil seal rotating performance testing machine |
| CN112362245A (en) * | 2020-11-02 | 2021-02-12 | 东毓(宁波)油压工业有限公司 | Automatic calibration oil seal jig for rotary head base |
-
2015
- 2015-06-30 CN CN201510370327.2A patent/CN106323550A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108613801A (en) * | 2018-04-26 | 2018-10-02 | 安徽皖南新维电机有限公司 | A kind of motor connecting cartridge waterproof washer durability degree test device |
| CN109916705A (en) * | 2018-12-31 | 2019-06-21 | 江苏明珠试验机械有限公司 | High temperature high pressure oil seal rotating performance testing machine |
| CN112362245A (en) * | 2020-11-02 | 2021-02-12 | 东毓(宁波)油压工业有限公司 | Automatic calibration oil seal jig for rotary head base |
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Legal Events
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| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170111 |