CN108254181A - A kind of bearing impact pilot system and experimental method - Google Patents
A kind of bearing impact pilot system and experimental method Download PDFInfo
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- CN108254181A CN108254181A CN201711298147.3A CN201711298147A CN108254181A CN 108254181 A CN108254181 A CN 108254181A CN 201711298147 A CN201711298147 A CN 201711298147A CN 108254181 A CN108254181 A CN 108254181A
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- turbine
- bearing
- combustion chamber
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The present invention provides a kind of bearing impact pilot systems, including air compressor machine, air accumulator, regulating valve, combustion chamber, fast three-way valve, counterbalance valve, turbine, bearing test device, current vortex excitation loading system, brake system and control system, the air compressor machine, air accumulator, regulating valve, combustion chamber, fast three-way valve and counterbalance valve are sequentially connected, the fast three-way valve is also connect with turbine, turbine is connect with bearing test device, simultaneously equipped with current vortex excitation loading system and brake system on the bearing test device.The power input unit of experimental condition of the present invention is turbine, is done work by the high temperature and pressure air heated by combustion chamber to turbine, drives turbine.The input work of turbine can determine that can be adjusted, the input work of turbine is very big by the amount of fuel and air supply for spraying into combustion chamber, can meet the anxious acceleration request of rotor-bearing system.
Description
Technical field
The invention belongs to field of electromechanical technology, more particularly, to a kind of bearing impact pilot system and experimental method.
Background technology
The bearing arrangement of turbogenerator is the kernel component of most critical, and bullet is sprayed with whirlpool, for fanjet,
Bearing arrangement is even more important.Some are sprayed by the bullet of cartridge start with whirlpool, fanjet, in the stage of gunpowder work, turbine hair
The rotor of motivation can accelerate to fire speed in several seconds have to go to the toilet.Moreover, engine overload degree is high, starting stage bearing system
System insufficient lubrication, these situations are likely to cause the earlier damage of bearing.
Suddenly accelerate to study starting stage under different bearing arrangements, different bearing lubrication conditions to propeller for turboprop machine bearing
Influence caused by system needs to find bearing arrangement test method that is targeted, being capable of simulated firing operating mode.
Invention content
In view of this, the present invention is directed to propose a kind of bearing impact pilot system and experimental method, for studying bullet whirlpool
Spray, fanjet are under starting stage, anxious accelerating mode, the different bearing arrangements of bearing arrangement, different bearing lubrication conditions
The influence caused by turbogenerator bearing arrangement.
In order to achieve the above objectives, the technical proposal of the invention is realized in this way：
A kind of bearing impact pilot system, including air compressor machine, air accumulator, regulating valve, combustion chamber, fast three-way valve, back pressure
Valve, turbine, bearing test device, current vortex excitation loading system, brake system and control system, the air compressor machine, air accumulator,
Regulating valve, combustion chamber, fast three-way valve and counterbalance valve are sequentially connected, and the fast three-way valve is also connect with turbine, turbine and axis
Experimental rig connection is held, current vortex excitation loading system and brake system are equipped with simultaneously on the bearing test device.
Further, the bearing test device includes supporter and bearing bore, is toroidal cavity inside the supporter,
And one side is open；Test bearing, bearing bore and current vortex excitation are radially installed successively from inside to outside in the toroidal cavity
Loading system；The turbine wheel shaft of the turbine passes through the axle center of supporter, and end is equipped with Flywheel disc, the supporter outer end peace
Fill the brake system for braking Flywheel disc.
Further, the current vortex excitation loading system includes permanent magnet and stator coil, table on the outside of the bearing bore
The circumferentially fixed permanent magnet in face, the circumferentially fixed installation stator coil of the supporter inner surface opposite with permanent magnet.
Further, the brake system include hydraulic oil pipe, caliper, piston, the first friction plate, the first friction plate and
Guide rail, the front end of the caliper are equipped with the inner cavity for setting the piston, and rear end is equipped with the forceps-like arrangement of a bottom opening, tong-like
The left and right sides in structure sets first friction plate and the second friction plate respectively；The upper end of the caliper is fixed by guide rail
On supporter, caliper can be moved along guide rail direction, and the piston is connect with the first friction plate, the first friction plate and second
Flywheel disc is clipped in the middle by friction plate, but does not contact, and the front end of the inner cavity enters fuel-flow control piston by hydraulic oil pipe
Position.
The test method of above-mentioned bearing impact pilot system, includes the following steps：
Step 1, test bearing is mounted on bearing test device, sets parameter；
Step 2, by control system, the position that the unlatching of fast three-way valve is connected to combustion chamber with counterbalance valve starts whirlpool
The lubricating system of wheel starts air compressor machine；
Step 3, when the pressure of air accumulators is to rated pressure, then regulating valve is opened, under small flow status, combustion chamber point
Fire；
Step 4, instruction is provided by control system, the position that fast three-way Vavle switching is made to be connected to combustion chamber with turbine,
During this experiment, secondary speed steeply rises, and turbine drives bearing experimental rig completes bearing impact experiment；
Step 5, it when detecting that turbine reaches bearing test maximum speed by speed probe, is provided by control system
Instruction, the position that fast three-way Vavle switching is made to be connected to combustion chamber with counterbalance valve, while brake system is controlled to work, turbine drop
Speed；
Step 6, combustion chamber is stopped working, the position that fast three-way Vavle switching is made to be connected to combustion chamber with turbine, is closed later empty
Press, the lubricating system of turbine, control system.
Relative to the prior art, device and method of the present invention has the advantage that：
Bullet is sprayed the present invention with whirlpool, fanjet is under starting stage, anxious accelerating mode for studying, and bearing arrangement is not
Same bearing arrangement, different bearing lubrication conditions are influenced caused by turbogenerator bearing arrangement.The power of the experimental condition is defeated
Enter unit for turbine, done work by the high temperature and pressure air heated by combustion chamber to turbine, drive turbine.The input work of turbine can
Determine that can be adjusted, the input work of turbine is very big, can meet by the amount of fuel and air supply that spray into combustion chamber
The anxious acceleration request of rotor-bearing system.And since turbine wheel shaft is lubricated using floating bearing, more turn can be sponged
Sub uneven leakage energy is small to the vibration effect of test bearing.
Description of the drawings
The attached drawing for forming the part of the present invention is used to provide further understanding of the present invention, schematic reality of the invention
Example and its explanation are applied for explaining the present invention, is not constituted improper limitations of the present invention.In the accompanying drawings：
Fig. 1 is the structure principle chart of bearing impact pilot system described in the embodiment of the present invention；
Fig. 2 is turbine described in the embodiment of the present invention, bearing test device, current vortex excitation loading system, brake system
Installation diagram.
Specific embodiment
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the present invention can phase
Mutually combination.
The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
A kind of bearing impact pilot system, as shown in Figure 1, including air compressor machine 1, air accumulator 2, regulating valve 3, combustion chamber 4, fast
Fast triple valve 5, counterbalance valve 6, turbine 7, bearing test device 8, current vortex excitation loading system 9, brake system 10 and control system
System 11, the air compressor machine 1, air accumulator 2, regulating valve 3, combustion chamber 4, fast three-way valve 5 and counterbalance valve 6 are sequentially connected, described fast
Fast triple valve 5 is also connect with turbine 7, and turbine 7 is connect with bearing test device 8, simultaneously equipped with electricity on the bearing test device 8
It is vortexed excitation loading system 9 and brake system 10.
As shown in Fig. 2, the bearing test device 8 includes supporter 81 and bearing bore 82,81 inside of supporter is
Toroidal cavity, and one side is open；Test bearing, 82 and of bearing bore are radially installed successively from inside to outside in the toroidal cavity
Current vortex excitation loading system 9；The turbine wheel shaft of the turbine 7 passes through the axle center of supporter 81, and end is equipped with Flywheel disc 11, institute
The installation of 81 outer end of supporter is stated for braking the brake system 10 of Flywheel disc 11.
The current vortex excitation loading system 9 includes permanent magnet 91 and stator coil 92,82 outer surface of bearing bore
Circumferentially fixed permanent magnet 91, the circumferentially fixed installation stator coil 92 of the supporter 81 inner surface opposite with permanent magnet 91.
The brake system 10 includes hydraulic oil pipe 12, caliper 13, piston 14, the first friction plate 15, the second friction plate
16 and guide rail 17, the front end of the caliper 13 is equipped with the inner cavity for setting the piston 14, and rear end is equipped with the pincers of a bottom opening
Shape structure, the left and right sides in forceps-like arrangement set 15 and second friction plate 16 of the first friction plate respectively；The caliper
13 upper end is fixed on by guide rail 17 on supporter 81, and caliper 13 can be moved along 17 direction of guide rail, the piston 14 and
One friction plate 15 connects, and Flywheel disc 11 is clipped in the middle, but do not contact by the first friction plate 15 and the second friction plate 16, the inner cavity
The front end position into fuel-flow control piston 14 that passes through hydraulic oil pipe 12.
The experimentation of above-mentioned pilot system is：
Step 1, with gently rotary flywheel disk 11, the assembling of inspection debugging bearing arrangement are transported manually at brake system 10
Turn situation, check whether there is catching phenomenon.Check each connecting line, if having loosening, whether the support of bearing test device 8 is firm
Gu whether sensor secured by calibration, sensor installation, whether cooling water, machine oil and fuel oil can regular supplies.Start
Test bearing is first mounted on bearing test device 8 by test-bed control system 11, for experiment subject, sets bearing
Lubricants capacity, bearing arrangement structural parameters, 9 parameter of current vortex excitation loading system, bearing test maximum speed；
Step 2, by test-bed control system 11, fast three-way valve 5 is opened to combustion chamber 4 and is connected with counterbalance valve 6
Position.Start turbine lubrication system (according to the sequence of oil-feed pump after first scavenge oil pump), and oil temperature and pressure is waited for reach
Specified stationary value.When oil temperature reaches rated value, start air compressor machine 1；
Above-mentioned two step is also the preparation stage of experiment.
Step 3, as 2 pressure of air accumulators to rated pressure (generally 0.1Mpa), then regulating valve 3 is opened, in small flow
Under (the generally 10%-15% of rated chamber flow) state, combustion chamber 4 is lighted a fire；The fuel feeding of Collaborative Control combustion chamber 4 later
Amount, 3 aperture of regulating valve, 6 aperture of counterbalance valve make air mass flow, temperature, pressure that combustion chamber 4 exports reach regulation requirement；Experiment
When, bearing test parameter corresponding for the turbojet engine of 1000daN thrusts, the air mass flow that general combustion chamber 4 exports is
2kg/s, temperature 1000K, pressure 0.6Mpa；
Step 4, instruction is provided by control system 11, fast three-way valve 5 is made to be switched to the position that combustion chamber 4 is connected with turbine 7
It puts, during this experiment, 7 rotating speed of turbine steeply rises, and turbine 7 drives bearing test device 8 to complete bearing impact experiment；
Step 5, when detecting that turbine 7 reaches bearing test maximum speed by speed probe, by control system 11
Instruction is provided, fast three-way valve 5 is made to be switched to the position that combustion chamber 4 is connected with counterbalance valve 6, while provide brake instruction, is braked
System 10 works, 7 reduction of speed of turbine；
Step 6, combustion chamber 4 is flame-out, fast three-way valve 5 is made to be switched to the position that combustion chamber 4 is connected with turbine 7, cold blowing 5 is arrived
8 minutes, air compressor machine 1, turbine lubrication system, control system 11 were closed later；
Step 7, test bearing is taken out from bearing test device 8, is decomposed, carry out test result analysis work.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
With within principle, any modification, equivalent replacement, improvement and so on should all be included in the protection scope of the present invention god.
Claims (5)
1. a kind of bearing impact pilot system, it is characterised in that：Including air compressor machine, air accumulator, regulating valve, combustion chamber, quick three
Port valve, counterbalance valve, turbine, bearing test device, current vortex excitation loading system, brake system and control system, the pneumatics
Machine, air accumulator, regulating valve, combustion chamber, fast three-way valve and counterbalance valve are sequentially connected, and the fast three-way valve also connects with turbine
It connects, turbine is connect with bearing test device, simultaneously equipped with current vortex excitation loading system and brake on the bearing test device
System.
2. a kind of bearing impact pilot system according to claim 1, it is characterised in that：The bearing test device includes
Supporter and bearing bore, the supporter inside is toroidal cavity, and one side is open；Radially from interior in the toroidal cavity
Test bearing, bearing bore and current vortex excitation loading system are installed successively outward；The turbine wheel shaft of the turbine passes through supporter
Axle center, end are equipped with Flywheel disc, and the brake system for braking Flywheel disc is installed in the supporter outer end.
3. a kind of bearing impact pilot system according to claim 2, it is characterised in that：The current vortex excitation loading system
System includes permanent magnet and stator coil, the circumferentially fixed permanent magnet of bearing bore outer surface, the supporter and permanent magnet phase
To the circumferentially fixed installation stator coil of inner surface.
4. a kind of bearing impact pilot system according to claim 3, it is characterised in that：The brake system includes hydraulic pressure
Oil pipe, caliper, piston, the first friction plate, the first friction plate and guide rail, the front end of the caliper, which is equipped with, sets the piston
Inner cavity, rear end is equipped with the forceps-like arrangement of a bottom opening, and the left and right sides in forceps-like arrangement sets first friction respectively
Piece and the second friction plate；The upper end of the caliper is fixed on by guide rail on supporter, and caliper can be moved along guide rail direction,
The piston is connect with the first friction plate, and Flywheel disc is clipped in the middle, but do not contact by the first friction plate and the second friction plate, described
The position into fuel-flow control piston that the front end of inner cavity passes through hydraulic oil pipe.
5. the test method of any bearing impact pilot system of Claims 1-4, it is characterised in that include the following steps：
Step 1, test bearing is mounted on bearing test device, sets parameter；
Step 2, by control system, the position that the unlatching of fast three-way valve is connected to combustion chamber with counterbalance valve starts turbine
Lubricating system starts air compressor machine；
Step 3, when the pressure of air accumulators is to rated pressure, then regulating valve is opened, under small flow status, combustion chamber ignition；
Step 4, instruction is provided by control system, the position that fast three-way Vavle switching is made to be connected to combustion chamber with turbine, at this
During experiment, secondary speed steeply rises, and turbine drives bearing experimental rig completes bearing impact experiment；
Step 5, when detecting that turbine reaches bearing test maximum speed by speed probe, finger is provided by control system
It enables, the position that fast three-way Vavle switching is made to be connected to combustion chamber with counterbalance valve, while brake system is controlled to work, turbine reduction of speed；
Step 6, combustion chamber is stopped working, the position that fast three-way Vavle switching is made to be connected to combustion chamber with turbine, later close air compressor machine,
Lubricating system, the control system of turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711298147.3A CN108254181A (en) | 2017-12-08 | 2017-12-08 | A kind of bearing impact pilot system and experimental method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711298147.3A CN108254181A (en) | 2017-12-08 | 2017-12-08 | A kind of bearing impact pilot system and experimental method |
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| Publication Number | Publication Date |
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| CN108254181A true CN108254181A (en) | 2018-07-06 |
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ID=62722266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711298147.3A Pending CN108254181A (en) | 2017-12-08 | 2017-12-08 | A kind of bearing impact pilot system and experimental method |
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| CN (1) | CN108254181A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109187016A (en) * | 2018-10-12 | 2019-01-11 | 江苏理工学院 | A kind of rolling bearing loading device and its control method with transient impact function |
| CN111426475A (en) * | 2020-05-06 | 2020-07-17 | 湖南汉能科技有限公司 | Main shaft bearing impact test platform |
| CN114962094A (en) * | 2022-05-09 | 2022-08-30 | 潍柴动力股份有限公司 | Combustion system and control method thereof |
| CN116358865A (en) * | 2022-12-22 | 2023-06-30 | 黑龙江云造科技有限公司 | Bearing test system under high Wen Tanqing fuel environment |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109187016A (en) * | 2018-10-12 | 2019-01-11 | 江苏理工学院 | A kind of rolling bearing loading device and its control method with transient impact function |
| CN111426475A (en) * | 2020-05-06 | 2020-07-17 | 湖南汉能科技有限公司 | Main shaft bearing impact test platform |
| CN111426475B (en) * | 2020-05-06 | 2021-09-17 | 湖南汉能科技有限公司 | Main shaft bearing impact test platform |
| CN114962094A (en) * | 2022-05-09 | 2022-08-30 | 潍柴动力股份有限公司 | Combustion system and control method thereof |
| CN114962094B (en) * | 2022-05-09 | 2024-05-17 | 潍柴动力股份有限公司 | Combustion system and control method thereof |
| CN116358865A (en) * | 2022-12-22 | 2023-06-30 | 黑龙江云造科技有限公司 | Bearing test system under high Wen Tanqing fuel environment |
| CN116358865B (en) * | 2022-12-22 | 2024-06-04 | 黑龙江云造科技有限公司 | Bearing test system under high Wen Tanqing fuel environment |
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Application publication date: 20180706 |
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