CN105319060B - Nitrogen blows pilot system - Google Patents
Nitrogen blows pilot system Download PDFInfo
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- CN105319060B CN105319060B CN201510848262.8A CN201510848262A CN105319060B CN 105319060 B CN105319060 B CN 105319060B CN 201510848262 A CN201510848262 A CN 201510848262A CN 105319060 B CN105319060 B CN 105319060B
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- valve
- fuel tank
- sensor
- tested device
- pressurized fuel
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Abstract
The present invention relates to a kind of nitrogen to blow pilot system, including experimental rig and host computer, and the experimental rig is equipped with pressurized fuel tank, and pressurized fuel tank is connect with pressurization air source, fuel tank and tested device, tested device connection driving air source；The experimental rig is equipped with sensor, and sensor is wirelessly connected with host computer.The present invention disclosure satisfy that factory needing, it can realize the computer control during the nitrogen of turbine pump under room temperature blows experiment and experiment, it can complete to the project testings such as rotating speed, turbine pump startup time, rotor-end vibration, turbine pump acceleration under pressure, maximum stream flow under turbine pump driving bleed pressure, zero delivery rotating speed, deadhead pressure, maximum stream flow, maximum stream flow, equipment quality is stablized, and disclosure satisfy that production needs.
Description
Technical field
The present invention relates to a kind of testing stands, blow pilot system with nitrogen more particularly to a kind of turbine pump.
Background technology
It is to turbine pump driving bleed pressure, zero delivery rotating speed, deadhead pressure, maximum stream flow, max-flow that nitrogen, which blows experiment,
The projects such as rotating speed, turbine pump startup time, rotor-end vibration, turbine pump acceleration are tested under amount lower pressure, maximum stream flow,
To meet the needs of turbine pump development and batch production task.
Currently, with the increase of turbine pump yield, station is obviously insufficient, restricts production efficiency, and population unit is right
High-speed turbine pump simulation takes whole vibration measuring mode to check and accept when checking and accepting, and existing testing stand has been unable to meet novel in test function
Number product test needs.
Invention content
The present invention is directed to problems of the prior art, provides a kind of nitrogen and blows pilot system, solves the prior art
Middle testing equipment cannot be satisfied the problem of product test needs.
Technical scheme is as follows:
Nitrogen blows pilot system, including experimental rig and host computer, and the experimental rig is equipped with pressurized fuel tank, pressurized fuel tank
It is connect with pressurization air source, fuel tank and tested device, tested device connection driving air source；The experimental rig is equipped with sensor,
Sensor is wirelessly connected with host computer.
Between the air chamber and pressurization air source of the pressurized fuel tank successively be equipped with intake valve, pressure reducing valve I, hand-operated valve I and
Check valve.
The fluid chamber of the pressurized fuel tank is connected by electromagnetic valve I, electromagnetic valve II and tested device arrival end；Described
Fuel tank is connected with electromagnetic valve I, pressurized fuel tank and electromagnetic valve II respectively by threeway, and electric-motor pump is equipped between threeway and electromagnetic valve II
With filter III.
The fluid chamber of the pressurized fuel tank passes sequentially through filter II, filter I is connected with safety valve II, safety valve II
It is connected with servo valve, servo valve is connected with tested device outlet end；Safety valve II and between tested device outlet end be equipped with electricity
Magnet valve IV and air bleeding valve I, air bleeding valve II；The piston exhaust ports of the pressurized fuel tank are connected with air bleeding valve III.
Air bleeding valve I, air bleeding valve II and the air bleeding valve III is connected with waste collection slot.
It is equipped with electromagnetic valve II I and pressure reducing valve II between the tested device and driving air source.
The air chamber of the pressurized fuel tank is connected with air bleeding valve IV and safety valve I, and the fluid chamber of pressurized fuel tank is connected with
Hand-operated valve II.
The sensor includes displacement sensor, pressure sensor, temperature sensor, speed probe, acceleration biography
Sensor and vibrating sensor.
The displacement sensor is connected with pressurized fuel tank；There are four the pressure sensor settings, pressure sensor I
It is connected with pressurized fuel tank, pressure sensor II is connected with tested device entrance, and pressure sensor III drives air source with tested device
Import is connected, and pressure sensor IV is connected with tested device outlet end；There are three the temperature sensor settings, temperature sensing
Device I is connected with pressurized fuel tank, and temperature sensor II is connected with tested device entrance, and temperature sensor III is exported with tested device
End is connected；Speed probe, acceleration transducer and the vibrating sensor is connected with tested device.
Lifting hanging ring is housed, experimental rig bottom carries Castor structure, castor locking machine at the top of the experimental rig
Structure.
The present invention has the following advantages：
It disclosure satisfy that factory needing, can realize that the nitrogen of turbine pump under room temperature blows the computer control during experiment and experiment
System can be completed to push turbine pump driving bleed pressure, zero delivery rotating speed, deadhead pressure, maximum stream flow, maximum stream flow
Project testings, the equipment quality such as rotating speed, turbine pump startup time, rotor-end vibration, turbine pump acceleration are steady under power, maximum stream flow
It is fixed, it disclosure satisfy that production needs.
Description of the drawings
Fig. 1 is the principle schematic diagram of the present invention.
In figure, 1, check valve, 2, hand-operated valve I, 3, pressure reducer I, 4, intake valve, 5, air bleeding valve IV, 6, safety valve I, 7, mistake
Filter I, 8, filter II, 9, displacement sensor, 10, piston, 11, hand-operated valve II, 12, pressure sensor I, 13, pressure sensing
Device II, 14, temperature sensor I, 15, temperature sensor II, 16, temperature sensor III, 17, electromagnetic valve I, 18, electromagnetic valve II,
19, threeway, 20, electric-motor pump, 21, filter III, 22, speed probe, 23, acceleration transducer, 24, pressure sensor
III, 25, vibrating sensor I, 26, vibrating sensor II, 27, electromagnetic valve II I, 28, electromagnetic valve I V, 29, air bleeding valve III, 30,
Air bleeding valve I, 31, air bleeding valve II, 32, pressure sensor IV, 33, servo valve, 34, safety valve II, 35, waste collection slot, 36, subtract
Depressor II, 37, stacked switch, 38, pressurized fuel tank, 39, tested device, 40, pressurization air source, 41, fuel tank, 42, driving air source.
Specific implementation mode
In order to better illustrate the effect of the present invention, it is illustrated below with specific example.
Embodiment 1
As shown, nitrogen blows pilot system, including experimental rig and host computer, the experimental rig is equipped with pressurized fuel tank
38, pressurized fuel tank 38 is connect with pressurization air source 40, fuel tank 41 and tested device 39, tested device connection driving air source 42；It is described
Experimental rig be equipped with sensor, sensor and host computer are wirelessly connected.
Intake valve 4, pressure reducing valve I3, hand-operated valve I2 are equipped between the air chamber and pressurization air source of the pressurized fuel tank successively
With check valve 1.
The fluid chamber of the pressurized fuel tank is connect by electromagnetic valve I 17, electromagnetic valve II 18 with tested device arrival end；
The fuel tank is connected with electromagnetic valve I, pressurized fuel tank and electromagnetic valve II respectively by threeway 19, is set between threeway and electromagnetic valve II
There are electric-motor pump 20 and filter III 21.
The fluid chamber of the pressurized fuel tank passes sequentially through filter II 8, filter I 7 is connected with safety valve II34, peace
Full valve II is connected with servo valve 33, and servo valve 33 is connected with tested device outlet end；Safety valve II with tested device outlet end
Between be equipped with electromagnetic valve I V28 and air bleeding valve I 30, air bleeding valve II 31；10 gas vent of piston of the pressurized fuel tank is connected with
Air bleeding valve III 29.
Air bleeding valve I, air bleeding valve II and the air bleeding valve III is connected with waste collection slot 35.
It is equipped with electromagnetic valve II I27 and pressure reducing valve II36 between the tested device 39 and driving air source 42.
The air chamber of the pressurized fuel tank is connected with air bleeding valve IV 5 and safety valve I 6, and the fluid chamber of pressurized fuel tank connects
It is connected to hand-operated valve II 11.
The sensor includes displacement sensor, pressure sensor, temperature sensor, speed probe, acceleration biography
Sensor and vibrating sensor.
The displacement sensor 9 is connected with pressurized fuel tank；There are four the pressure sensor settings, pressure sensor
I12 is connected with pressurized fuel tank, and pressure sensor II13 is connected with tested device entrance, pressure sensor III24 and tested device
Gas source inlet is driven to be connected, pressure sensor IV32 is connected with tested device outlet end；The temperature sensor is provided with three
A, temperature sensor I14 is connected with pressurized fuel tank, and temperature sensor II15 is connected with tested device entrance, temperature sensor
III16 is connected with tested device outlet end；Speed probe 22, acceleration transducer 23 and the vibrating sensor I, vibration
Sensor II is connected with tested device.
Lifting hanging ring is housed, experimental rig bottom carries Castor structure, castor locking machine at the top of the experimental rig
Structure.
Nitrogen of the present invention blows test principle and process description is as follows.
（1）Oil filling：Filling oil pipe is inserted into fuel tank, three-way magnetic valve is switched to filling position, and electromagnetic valve I is beaten
It opens, electromagnetic valve II is closed.Fresh oil can be by being filled into after filter II filterings in pressurized fuel tank.With oil mass in pressurized fuel tank
Increase, piston can drive Linear displacement transducer 9 slowly rise, when reach computer control setting value when, fill motor
Pump 20 is automatically stopped work.
（2）Exhaust:Exhaust is divided into fuel tank exhaust and pipeline exhaust.Exhaust work needs to install in subject turbine pump,
Experimental rig carries out under circulating filtration state.The a small amount of fluid being discharged through air bleeding valve can be collected into waste collection slot 35 automatically
It is interior.
It is equipped with fuel tank gas vent in the top land of pressurized fuel tank, opens fuel tank ventilation valve III, the piston in fuel tank can be
The lower slow decline used of top air pressure, being suspended in the gas at the top of fluid chamber at this time can be along the hole among piston and piston rod
Road in-line arrangement air valve discharge illustrates that fuel tank exhaust work terminates until having observed that oil spill goes out.
It is tested turbine pump discharge and is equipped with pipeline air bleeding valve I30 and air bleeding valve II31, for being discharged in turbine pump disassembly process
In be mixed into gas in pipeline.Pipeline air bleeding valve III is opened, until having observed that oil spill goes out, illustrates that pipeline exhaust work terminates.
Fuel tank exhaust should be vented while operating with pipeline, to reach better exhaust effect.
（3）Turbopump tests：Gas pressure reducer I3 is adjusted, so that its outlet is set up within the scope of 0.5~0.8MPa, opens electricity
Dynamic intake valve 4, makes nitrogen enter in the air cavity above closed pressurized fuel tank.Electromagnetic valve II 18 and electromagnetic valve I V28 are opened.
When experiment, the test procedure of TT＆C system starts electromagnetic valve II I27, and high pressure nitrogen driving turbine makes turbine pump work
Make.
Servo valve is used to be tested the outlet pressurization of turbine pump, servo valve 33 is shown in a fully open operation at this time, when turbine reaches
After rated speed, the aperture of servo valve is adjusted according to the requirement of operating condition of test, to realize the adjusting of turbine pump discharge load pressure,
TT＆C system is started to work.
If turbine pump discharge pressure exceeds design safety value, safety valve II34, which is automatically opened, makes oil be discharged into fuel tank.
One gas safety valve I6 is set in the air cavity of fuel tank, when loine pressure is when it is more than to set pressure that oil temperature, which increases,
It automatically opens to reduce pressure.
After experiment, intake valve 4 is closed, air bleeding valve IV5 is opened, fuel tank is made to be vented.Electromagnetic valve II and electromagnetic valve I V
It closes, the turbine pump that experiment finishes is removed.
Pilot system technical requirement of the present invention is as follows:
（1）Zero delivery nitrogen blows rotating speed：50±5krpm;
（2）Nitrogen blows and sprays a mouthful pressure：5±1Mpa；
（3）The pump startup time：≤1.5s；
（4）Rack driving device maximum speed：130 krpm;
（5）Pump shaft free end vibratory output：≤0.03mm；
（6）Working media：10#, 12# or 15# aircraft fluid;
（7）Operating pressure：4~6MPa is continuously adjusted;
（8）Working flow：Maximum 27L/min;
（9）Fuel-tank pressurization pressure：0.5~0.8MPa;
（10）Volume of fuel tank：10L;
（11）Drive gaseous species：Compressed nitrogen;
（12）Drive air pressure：5~8MPa;
（13）Equipment supply voltage：220V AC 50Hz;
（14）Platform system：By high-speed turbine pump testing requirement, corresponding test-bed is prepared in design and eight kinds of nitrogen blow and spray
Head；
（15）Pressure Sensor Precision is not less than ± 0.25%, and temperature sensor precision is not less than ± 0.5%, flow sensor
Precision is not less than ± 0.5%, and vibrating sensor can realize that 0-0.5mm vibration displacements measure, and realize synchronous acquisition.Wiring uses
Concentric wiring.
Above with respect to the specific descriptions of the present invention, it is merely to illustrate the present invention and is not limited to the embodiment of the present invention and is retouched
The technical solution stated.It will be understood by those of ordinary skill in the art that still can modify to the present invention or equivalent replacement,
To reach identical technique effect.Needs are used as long as meeting, all within the scope of the present invention.
Claims (1)
1. nitrogen blows pilot system, it is characterised in that including experimental rig and host computer, the experimental rig is equipped with pressurized fuel tank,
Pressurized fuel tank is connect with pressurization air source, fuel tank and tested device, tested device connection driving air source；The experimental rig is equipped with
Sensor, sensor are wirelessly connected with host computer；
The sensor includes displacement sensor, pressure sensor, temperature sensor, speed probe, acceleration transducer
And vibrating sensor；
The displacement sensor is connected with pressurized fuel tank；There are four the pressure sensor settings, pressure sensor I and increasing
Pressure oil case is connected, and pressure sensor II is connected with tested device entrance, and pressure sensor III drives gas source inlet with tested device
It is connected, pressure sensor IV is connected with tested device outlet end；There are three the temperature sensor settings, temperature sensor I
It is connected with pressurized fuel tank, temperature sensor II is connected with tested device entrance, temperature sensor III and tested device outlet end phase
Even；Speed probe, acceleration transducer and the vibrating sensor is connected with tested device；
Intake valve, pressure reducing valve I, hand-operated valve I and unidirectional are equipped between the air chamber and pressurization air source of the pressurized fuel tank successively
Valve；
The fluid chamber of the pressurized fuel tank is connected by electromagnetic valve I, electromagnetic valve II and tested device arrival end；The fuel tank
It is connected respectively with electromagnetic valve I, pressurized fuel tank and electromagnetic valve II by threeway, electric-motor pump and mistake is equipped between threeway and electromagnetic valve II
Filter III；
The fluid chamber of the pressurized fuel tank passes sequentially through filter II, filter I is connected with safety valve II, safety valve II with watch
It takes valve to be connected, servo valve is connected with tested device outlet end；Electromagnetic valve I V is equipped between safety valve II and tested device outlet end
With air bleeding valve I, air bleeding valve II；The piston exhaust ports of the pressurized fuel tank are connected with air bleeding valve III；
Air bleeding valve I, air bleeding valve II and the air bleeding valve III is connected with waste collection slot；
It is equipped with electromagnetic valve II I and pressure reducing valve II between the tested device and driving air source；
The air chamber of the pressurized fuel tank is connected with air bleeding valve IV and safety valve I, and the fluid chamber of pressurized fuel tank is connected with manually
Valve II；
Lifting hanging ring is housed, experimental rig bottom carries Castor structure, castor locking mechanism at the top of the experimental rig.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510848262.8A CN105319060B (en) | 2015-11-29 | 2015-11-29 | Nitrogen blows pilot system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510848262.8A CN105319060B (en) | 2015-11-29 | 2015-11-29 | Nitrogen blows pilot system |
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| Publication Number | Publication Date |
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| CN105319060A CN105319060A (en) | 2016-02-10 |
| CN105319060B true CN105319060B (en) | 2018-10-12 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110425189B (en) * | 2019-07-17 | 2020-10-23 | 北京精密机电控制设备研究所 | Ultrahigh-speed turbine pump and overflow valve matching test device |
| CN113638891B (en) * | 2021-04-29 | 2024-03-15 | 北京精密机电控制设备研究所 | Turbine pump test system |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101532910A (en) * | 2009-04-16 | 2009-09-16 | 北京理工大学 | Acceleration performance evaluation test method and test apparatus of turbo-charger |
| CN103954431A (en) * | 2014-04-26 | 2014-07-30 | 沈阳航天新光集团有限公司 | Flow resistance measurement test system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102607796B (en) * | 2012-03-07 | 2014-01-22 | 北京航空航天大学 | Large-size dual-heat sink nitrogen blowing system with adjustable temperature and operation method thereof |
| CN202631241U (en) * | 2012-06-13 | 2012-12-26 | 常州兰翔机械有限责任公司 | Nozzle flow testing device |
| KR101511249B1 (en) * | 2013-11-26 | 2015-04-13 | 한전케이피에스 주식회사 | Safety valve performance test methods |
| CN103868686B (en) * | 2014-03-26 | 2016-08-24 | 沈阳航天新光集团有限公司 | Charging connector service life experiment system |
| CN205192741U (en) * | 2015-11-29 | 2016-04-27 | 沈阳航天新光集团有限公司 | Nitrogen blows testing system |
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- 2015-11-29 CN CN201510848262.8A patent/CN105319060B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101532910A (en) * | 2009-04-16 | 2009-09-16 | 北京理工大学 | Acceleration performance evaluation test method and test apparatus of turbo-charger |
| CN103954431A (en) * | 2014-04-26 | 2014-07-30 | 沈阳航天新光集团有限公司 | Flow resistance measurement test system |
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