CN205843960U - A kind of aero-engine high-speed bearing high/low temperature lubrication test device - Google Patents
A kind of aero-engine high-speed bearing high/low temperature lubrication test device Download PDFInfo
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- CN205843960U CN205843960U CN201620718498.XU CN201620718498U CN205843960U CN 205843960 U CN205843960 U CN 205843960U CN 201620718498 U CN201620718498 U CN 201620718498U CN 205843960 U CN205843960 U CN 205843960U
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Abstract
This utility model relates to high-speed bearing performance test technical field, discloses a kind of aero-engine high-speed bearing high/low temperature lubrication test device.Carry out to realize the synchronization of lubrication simulation and environment temperature simulation, preferably simulating the operating mode of bearing actual motion, device of the present utility model is composed in series by oil supply system (1), heating system (2), pilot system (3), oil return cooling system (4) and cycle cooling system (5)；Lubricating oil can select be used alone electrically heated rod (106) or use electrically heated rod (106) and electric heater (203) to heat simultaneously by solenoid directional control valve (201) according to target operating condition；Main fuel tank (101) and auxiliary fuel tank (401) are independently arranged, and utilize the first circulating pump (405) to carry out local and dispel the heat, utilize the second circulating pump (501) to be circulated heat radiation.Device is controlled by this utility model by host computer, PLC and multiple sensor, automaticity height and simple in construction, it is simple to operation, is beneficial to promote.
Description
Technical field
This utility model relates to high-speed bearing performance test technical field, a kind of aero-engine high speed shaft
Hold high/low temperature lubrication test device.
Background technology
Aero-engine high-speed bearing, when carrying out endurancing, needs the work condition environment to high-speed bearing to carry out mould
Intend, generally carry out load simulated, lubrication simulation and temperature simulation.In utility application book (CN201410448781.0)
Describe a kind of bearings synthesis dynamic performance test apparatus and method of testing thereof, wherein lubrication simulation by volume control device and
Pressure control device controls the lubrication of bearing, and temperature simulation realizes bearing ambient temperature by resistive heater or heating furnace
Control.Utility application book (CN201210556215.2) describes oscillating bearing high and low temperature environment life test
Machine, wherein environmental simulation realizes the simulation of bearing environment by environmental cabinet and temperature sensor.In above-mentioned utility model application all
It is that the simulation of lubrication and ambient temperature is implemented respectively, process of the test can not well be simulated aero-engine high speed shaft
Hold real work condition environment.
Utility model content
This utility model aims to provide a kind of aero-engine high-speed bearing high/low temperature lubrication test device, will lubrication and ring
Simulate while the temperature of border and realized by this device, more conform to the actual operating mode of aero-engine high-speed bearing.
For solve above technical problem, this device include oil supply system, heating system, pilot system, oil return cooling system,
Cycle cooling system and control system, described oil supply system includes main fuel tank, dosing pump, the first filter, the first differential pressure signaling
Device, the first temperature sensor, electrically heated rod, the first liquid level relay, pressure transducer and effusion meter, described first temperature sensing
Device, electrically heated rod and the first liquid level relay are arranged in described main fuel tank, and the oil-feed port of described main fuel tank passes through fuel feed pump
Road is sequentially connected with described dosing pump, the first filter and heating system, wherein between described first filter and heating system
Oil feed line on be also disposed with described pressure transducer and effusion meter, described first differential pressure transmitter device is connected to the first mistake
The import and export two ends of filter；Described heating system includes solenoid directional control valve, the second temperature sensor, electric heater, the 3rd temperature
Sensor, after the effusion meter that the entrance of described solenoid directional control valve is connected on oil feed line, the first of described solenoid directional control valve
Outlet is sequentially connected with the second temperature sensor, electric heater, three-temperature sensor and pilot system, described solenoid directional control valve
Second outlet is connected with the oil feed line between described electric heater and three-temperature sensor, and described electric heater intracavity is arranged
There is the 4th temperature sensor；Described oil return cooling system include auxiliary fuel tank, oil well pump, the second filter, the second differential pressure transmitter device,
First circulating pump, the first Air cooler, the 3rd filter, the 3rd differential pressure transmitter device, the second liquid level relay and the 5th temperature sensing
Device, described second liquid level relay and the 5th temperature sensor be arranged in described auxiliary fuel tank, and the entrance of described oil well pump leads to
Crossing the second filter to be connected with the oil sump of pilot system, outlet is connected with auxiliary fuel tank, and described second differential pressure transmitter device is connected to the
The import and export two ends of tow filtrator, the first exit and entrance stating circulating pump be connected to the both sides of auxiliary fuel tank, described
One Air cooler and the 3rd filter are successively set on the circulation line between the first circulation delivery side of pump and auxiliary fuel tank, and described
Three differential pressure transmitter devices are connected to the import and export two ends of the 3rd filter；Described cycle cooling system include the second circulating pump, second
Air cooler, the 4th filter and the 4th differential pressure transmitter device, the entrance of described second circulating pump is connected with auxiliary fuel tank, exports by pipe
Road is connected with described second Air cooler, the 3rd filter and main fuel tank successively, and described 4th differential pressure transmitter device is connected to the 4th mistake
The import and export two ends of filter；Described control system includes the host computer at Integrated Human Machine Interaction interface, PLC, the first temperature controller and
Two temperature controllers, described PLC includes CPU, I/O module, A/D module, and described host computer realizes two-way communication with the CPU of PLC, described
First differential pressure transmitter device, the second differential pressure transmitter device, the 3rd differential pressure transmitter device, the 4th differential pressure transmitter device, the first liquid level relay and
The signal of the second liquid level relay inputs with the digital signal of PLC respectively and is connected, described dosing pump, oil well pump, the first circulating pump,
The control system of the fault alarm of the second circulating pump, solenoid directional control valve and human-computer interaction interface is defeated with the digital signal of PLC respectively
Go out connected, described first temperature sensor, the second temperature sensor, three-temperature sensor, the 4th temperature sensor, the 5th temperature
The signal of degree sensor, pressure transducer and effusion meter inputs with the analogue signal of PLC respectively and is connected, the control of described electrically heated rod
Signal processed is connected with the analog signal output of PLC by the first temperature controller, and described electrically heated control signal device is by the second temperature
Control instrument is connected with the analog signal output of PLC.
Preferably, described oil supply system oil feed line between the first filter and pressure transducer is disposed with
First check valve and flow speed control valve, the oil feed line between pressure transducer and effusion meter is provided with the first ball valve；Described confession
Oil system also includes an overflow valve, and the entrance of this overflow valve is connected to the fuel feed pump between described first check valve and flow speed control valve
Lu Shang, outlet is connected to main fuel tank；Described main fuel tank is provided with the first liquidometer, and the pouring orifice of main fuel tank is provided with the first air
Filter, is additionally provided with the first Pressure gauge at the pressure transducer of oil feed line；Described first filter is twin-tub filter,
Described electrically heated rod quantity is two.
Preferably, the electric heater of described heating system is between the second temperature sensor and three-temperature sensor
The second check valve and the 3rd check valve it is disposed with on oil feed line；Second outlet of described solenoid directional control valve is single by the 4th
It is connected on the oil feed line between described 3rd check valve and three-temperature sensor to valve；Described three-temperature sensor with
The second ball valve it is additionally provided with on oil feed line between pilot system.
Preferably, the return line between described oil sump and oil well pump is provided with the 3rd ball valve；Described first Air cooler
Import and the first circulating-pump outlet between circulation line on be provided with the second Pressure gauge, the outlet of the first Air cooler and second
The first thermometer it is provided with on circulation line between filter inlet；Described auxiliary fuel tank is provided with the second liquidometer, auxiliary fuel tank
Pouring orifice be provided with the second air filter.
Preferably, the circulation line between import and second circulating-pump outlet of described second Air cooler is provided with the 3rd
Pressure gauge, the circulation line between outlet and the 3rd filter inlet of the second Air cooler is provided with the second thermometer.
Preferably, described first Pressure gauge, the second Pressure gauge and the 3rd Pressure gauge are connected with pipeline by a valve respectively.
Beneficial effect
This utility model can fully simulate actual lubrication and the ambient temperature conditions of aero-engine high-speed bearing；
The ambient temperature of high-speed bearing is simulated, by original lubricating system and environment mould by the temperature controlling lubricating oil
Plan system unites two into one so that the structure of pilot system is the simplest, compact.
Use independent heater that lubricating oil is heated, and switch oil circuit by solenoid directional control valve, it is achieved that be high
Gentle cunning and the timely of low-temperature lubrication replace, and meet the actual lubrication circumstances of aero-engine height bearing.
It is provided with a multiple table, the most intuitively reads parameters.
Supply reservoir and oil return fuel tank are independently arranged, and centre utilizes circulating pump to carry out the circulation of fluid so that high temperature lubricating
Oil can dispel the heat rapidly after entering oil return fuel tank so that the oil temperature in fuel feeding fluid path is consistently lower than 80 degree, the most permissible
Utilize the hydraulic pressure signal collection of common model and control element and carry out observing and controlling, will not because of high temperature affect the collection of Hydraulic Elements with
Control accuracy, and cost-effective.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model；
Fig. 2 is oil supply system structural representation of the present utility model；
Fig. 3 is heating system structural representation of the present utility model；
Fig. 4 is oil return cooling system structure schematic diagram of the present utility model；
Fig. 5 is cycle cooling system structural representation of the present utility model；
Fig. 6 is Control system architecture schematic diagram of the present utility model；
Fig. 7 is control flow chart of the present utility model；
Labelling in figure: 1, oil supply system, 101, main fuel tank, 102, dosing pump, the 103, first filter, the 104, first pressure reduction
Signalling generator, the 105, first temperature sensor, 106, electrically heated rod, the 107, first liquid level relay, 108, pressure transducer, 109,
Effusion meter, the 110, first check valve, 111, flow speed control valve, the 112, first ball valve, 113, overflow valve, the 114, first liquidometer, 115,
First air filter, the 116, first Pressure gauge, 2, heating system, 201, solenoid directional control valve, the 202, second temperature sensor,
203, electric heater, 204, three-temperature sensor, the 205, the 4th temperature sensor, the 206, second check valve, the 207, the 3rd is single
To valve, the 208, the 4th check valve, the 209, second ball valve, 3, pilot system, 301, oil sump, 4, oil return cooling system, 401, secondary oil
Case, 402, oil well pump, the 403, second filter, the 404, second differential pressure transmitter device, the 405, first circulating pump, 406, first is air-cooled
Machine, the 407, the 3rd filter, the 408, the 3rd differential pressure transmitter device, the 409, second liquid level relay, the 410, the 5th temperature sensor,
411, the 3rd ball valve, the 412, second Pressure gauge, the 413, first thermometer, the 414, second liquidometer, the 415, second air filter,
5, cycle cooling system, the 501, second circulating pump, the 502, second Air cooler, the 503, the 4th filter, the 504, the 4th differential pressure signaling
Device, the 505, the 3rd Pressure gauge, the 506, second thermometer, 6, control system.
Detailed description of the invention
As shown in Figures 1 to 6, a kind of aero-engine high-speed bearing high/low temperature lubrication test device of the present utility model is excellent
The embodiment of choosing includes oil supply system 1, heating system 2, pilot system 3, oil return cooling system 4, cycle cooling system 5 and control
System 6 processed.
Oil supply system 1 includes main fuel tank 101, dosing pump the 102, first filter the 103, first differential pressure transmitter device 104, first
Temperature sensor 105, electrically heated rod the 106, first liquid level relay 107, pressure transducer 108, effusion meter 109, first are unidirectional
Valve 110, flow speed control valve the 111, first ball valve 112, overflow valve the 113, first liquidometer the 114, first air filter 115 and the first pressure
Power table 116；Wherein the first filter 103 is twin-tub filter, and its simple in construction is easy to use, and band bypass valve and filter element are dirty
Dye blocking signalling generator, to reach to ensure the purpose of security of system.Electrically heated rod 106 quantity is two, beneficially in main fuel tank 101
The quick heat temperature raising of lubricating oil.The pouring orifice of main fuel tank 101 is provided with the first air filter 115, is used in air filtering
Steam and impurity.The oil-feed port of described main fuel tank 101 by oil feed line be sequentially connected with dosing pump the 102, first filter 103,
First check valve 110, flow speed control valve the 111, first ball valve 112, effusion meter 109 and heating system 2, wherein the first differential pressure transmitter device
The 104 import and export two ends being arranged on the first filter 103, measure its inlet and outlet pressure, detect whether unobstructed, if need to change filter
Core.Pressure transducer 108 and the first Pressure gauge 116 are arranged on the oil feed line between flow speed control valve 111 and the first ball valve 112.
First temperature sensor 105, electrically heated rod the 106, first liquid level relay 107 and the first liquidometer 114 are arranged at described master
In fuel tank 101, measure the parameters that profit in main fuel tank 101 is changed oil, and teletransmission PLC or for on-the-spot reading.Oil supply system 1 is also wrapped
Including an overflow valve 113, the entrance of this overflow valve 113 is connected to the oil feed line between the first check valve 110 and flow speed control valve 111
On, outlet is connected to main fuel tank 101, and in dosing pump 102 flow restriction control system, dosing pump 102 provides constant flow rate, when
When system pressure increases, traffic demand can be made to reduce.Now overflow valve 113 is opened, and makes excess traffic overflow back main fuel tank 101, protects
The inlet pressure of card overflow valve 113, i.e. ensures that pump discharge pressure is constant.
Heating system 2 includes solenoid directional control valve the 201, second temperature sensor 202, electric heater the 203, the 3rd temperature sensing
Device 204, four temperature sensor 205, the second check valve the 206, the 3rd check valve the 207, the 4th check valve 208 and the second ball valve 209.
4th temperature sensor 205 is arranged on electric heater 203 intracavity.Solenoid directional control valve 201 is enough switches over control to lubricant passage way,
Achieve being switched fast between high temperature lubricating, low-temperature lubrication, after the effusion meter 109 that its entrance is connected on oil feed line,
Its first outlet be sequentially connected with second temperature sensor the 202, second check valve 206, electric heater the 203, the 3rd check valve 207,
Three-temperature sensor the 204, second ball valve 209 and pilot system 3, the second outlet of solenoid directional control valve 201 is single by the 4th
It is connected on the oil feed line between the 3rd check valve 207 and three-temperature sensor 204 to valve 209.Described several check valve
Setting can effectively prevent high/low temperature lubricating oil from flowing backwards in oil feed line.Use independent electric heater 203 to lubricating oil
Heat, and switch oil circuit by solenoid directional control valve 201, it is achieved that high temperature lubricating and the timely of low-temperature lubrication replace, symbol
Close the actual lubrication circumstances of aero-engine height bearing.
Oil return cooling system 4 include auxiliary fuel tank 401, oil well pump the 402, second filter the 403, second differential pressure transmitter device 404,
First circulating pump the 405, first Air cooler the 406, the 3rd filter the 407, the 3rd differential pressure transmitter device the 408, second liquid level relay
409, the 5th temperature sensor the 410, the 3rd ball valve the 411, second Pressure gauge the 412, first thermometer the 413, second liquidometer 414 and
Second air filter 415.Wherein the second liquid level relay the 409, the 5th temperature sensor 410 and the second liquidometer 414 are all provided with
Put in described auxiliary fuel tank 401, measure the parameters that profit in auxiliary fuel tank 401 is changed oil, and teletransmission PLC or for on-the-spot reading.Secondary
The pouring orifice of fuel tank 401 is provided with the second air filter 415, the steam being used in air filtering and impurity.Oil well pump 402
Entrance passes sequentially through the second filter 403 and the 3rd ball valve 411 is connected with the oil sump 301 of pilot system 3, outlet and auxiliary fuel tank
401 are connected, it is achieved by lubricating oil suction auxiliary fuel tank 401 used in oil sump 301, the second differential pressure transmitter device 404 is connected to
The import and export two ends of the second filter 403, measure its inlet and outlet pressure, detect whether unobstructed, if need to change filter element.For realizing
The circulation cooling of auxiliary fuel tank 401 internal lubrication oil, ad hoc is equipped with the first circulating pump 405, and its exit and entrance is respectively separated connection
The second Pressure gauge 404 it is provided with, at it on the both sides of auxiliary fuel tank 401, the circulation line between its entrance and auxiliary fuel tank 401
The first Air cooler the 406, the 3rd filter 407 and the first temperature is set gradually on circulation line between outlet and auxiliary fuel tank 401
Table 413, described 3rd differential pressure transmitter device 408 is connected to the import and export two ends of the 3rd filter 407.
Cycle cooling system 5 includes that second circulating pump the 501, second Air cooler the 502, the 4th filter the 503, the 4th pressure reduction is sent out
News device the 504, the 3rd Pressure gauge 505 and the second thermometer 506.In order to realize lubricating oil between main fuel tank 101 and auxiliary fuel tank 401
Circulation and take into account heat radiation, the entrance of the second circulating pump 501 is connected with auxiliary fuel tank 401, and circulation line betwixt is provided with the
Three Pressure gauges 505, export by circulation line successively with second Air cooler the 502, second thermometer the 506, the 3rd filter 407 and
Main fuel tank 101 connects, and the 4th differential pressure transmitter device 504 is connected to the import and export two ends of the 4th filter 503.
Control system 6 includes the host computer at Integrated Human Machine Interaction interface, PLC, the first temperature controller and the second temperature controller, described
PLC includes that CPU, I/O module, A/D module, described host computer realize two-way communication, described first differential pressure signaling with the CPU of PLC
Device the 104, second differential pressure transmitter device the 404, the 3rd differential pressure transmitter device the 408, the 4th differential pressure transmitter device the 504, first liquid level relay 107
And second the signal of liquid level relay 409 input with the digital signal of PLC respectively and be connected, described dosing pump 102, oil well pump 402,
The control system of the fault alarm of first circulating pump the 405, second circulating pump 501, solenoid directional control valve 201 and human-computer interaction interface is divided
Not exporting with the digital signal of PLC and be connected, described first temperature sensor the 105, second temperature sensor the 202, the 3rd temperature passes
The signal of sensor the 204, the 4th temperature sensor the 205, the 5th temperature sensor 410, pressure transducer 108 and effusion meter 109 divides
Not inputting with the analogue signal of PLC and be connected, the control signal of described electrically heated rod 106 is by the simulation of the first temperature controller with PLC
Signal output is connected, and described electrically heated control signal device is connected with the analog signal output of PLC by the second temperature controller.
Above-mentioned first Pressure gauge the 116, second Pressure gauge 412 and the 3rd Pressure gauge 505 are respectively by a valve and pipeline phase
Even, when instrument is damaged, only need to screw a valve the most replaceable.
This utility model simulates the ambient temperature of high-speed bearing by the temperature controlling lubricating oil, by original lube system
System and environmental simulation system unite two into one so that the structure of pilot system is the simplest, compact.Use independent heater to profit
Lubricating oil heats, and switches oil circuit by solenoid directional control valve, it is achieved that high temperature lubricating and the timely of low-temperature lubrication replace, symbol
Close the actual lubrication circumstances of aero-engine height bearing, fully simulate actual lubrication and the environment of aero-engine high-speed bearing
Temperature case.Main fuel tank 101 of the present utility model and auxiliary fuel tank 401 are independently arranged, and utilize the first circulating pump 405 to carry out local and dissipate
Heat, utilizes the second circulating pump 501 to be circulated heat radiation so that the oil temperature in fuel feeding fluid path is consistently lower than 80 degree, so can be in order to
Hydraulic pressure signal collection and control element by common model carry out observing and controlling, will not affect collection and the control of Hydraulic Elements because of high temperature
Precision processed, and cost-effective.In preferred embodiment of the present utility model, it is additionally provided with a multiple table, execute-in-place people can be made
Member intuitively reads parameters by a table, thus fast reaction, improve running efficiency and the security performance of equipment.
Control method such as Fig. 7 institute of a kind of aero-engine high-speed bearing high/low temperature lubrication experiment device of the present utility model
Show and comprise the following steps:
Step one: network communication state between detection host computer and PLC, is manually entered the temperature control of high/low temperature lubricating arrangement
Index processed, or artificial selection's pilot project reads temperature Con trolling index from experiment process.
Step 2: the I/O communication module of detection PLC and A/D communication module are to the first differential pressure transmitter device (104), the first liquid
Position relay (107), the second differential pressure transmitter device (404), the second liquid level relay (409), the 3rd differential pressure transmitter device (408), the
Four differential pressure transmitter devices (504), the first temperature sensor (105), the second temperature sensor (202), three-temperature sensor
(204), the 4th temperature sensor (205), the 5th temperature sensor (410), pressure transducer (108) and effusion meter (109)
Signals collecting, and be uploaded to host computer by network communication and carry out human-computer interaction interface and show, in order to monitor and debug.
Step 3: the signal received is analyzed processing by host computer, finishing man-machine interaction function and high/low temperature lubrication
The lubrication temperature controlled quentity controlled variable of system calculates, and exports control instruction, and control instruction passes through the output of PLC to the first temperature controller and second
Temperature controller.
Step 4: judge lubricating oil temperature span of control, when lubricating oil temperature control index is less than 80 degree, selects electrically heated rod
(106) heat；When lubricating oil temperature control index is higher than 80 degree, select to be total to for electrically heated rod (106) and electric heater (203)
With heating；The switching of high temperature lubricating and low-temperature lubrication is realized by solenoid directional control valve (201) switching oil circuit.
Step 5: judge main fuel tank respectively by the first liquid level relay (107) and the second liquid level relay (409)
And the liquid level feedback information of auxiliary fuel tank (401), the first liquid level relay (107) and the second liquid level relay (409) (101)
With output liquid level low signal and ultralow signal；When main fuel tank (101) liquid level is low, opens the second circulating pump (501), work as auxiliary fuel tank
(401), when liquid level is low, the second circulating pump (501) work is stopped.
Step 6: carry out emergent shutdown according to temperature, liquid level signal and judge, if lubricating oil temperature is beyond set-point temperature
When 10%, report to the police and shut down；When supply reservoir or the ultralow signal of oil return oil tank liquid level being detected, report to the police and shut down.According to test
Flow process judges whether to terminate test, then terminates test in man machine interface display as terminated to test.
Claims (5)
1. an aero-engine high-speed bearing high/low temperature lubrication test device, it include oil supply system (1), heating system (2),
Pilot system (3), oil return cooling system (4), cycle cooling system (5) and control system (6), it is characterised in that: described fuel feeding
System (1) includes main fuel tank (101), dosing pump (102), the first filter (103), the first differential pressure transmitter device (104), the first temperature
Degree sensor (105), electrically heated rod (106), the first liquid level relay (107), pressure transducer (108) and effusion meter (109),
Described first temperature sensor (105), electrically heated rod (106) and the first liquid level relay (107) are arranged at described main fuel tank
(101), in, the oil-feed port of described main fuel tank (101) is sequentially connected with described dosing pump (102), the first filter by oil feed line
(103) and heating system (2), wherein also depend on the oil feed line between described first filter (103) and heating system (2)
Secondary described pressure transducer (108) and the effusion meter (109) of being provided with, described first differential pressure transmitter device (104) is connected to the first mistake
The import and export two ends of filter (103)；Described heating system (2) include solenoid directional control valve (201), the second temperature sensor (202),
Electric heater (203), three-temperature sensor (204) and the 4th temperature sensor (205), described solenoid directional control valve (201)
After the effusion meter (109) that entrance is connected on oil feed line, the first outlet of described solenoid directional control valve (201) is sequentially connected with the
Two temperature sensors (202), electric heater (203), three-temperature sensor (204) and pilot system (3), described electromagnetic switch
Second outlet of valve (201) is connected with the oil feed line between described electric heater (203) and three-temperature sensor (204),
Described 4th temperature sensor (205) is arranged on electric heater (203) intracavity；Described oil return cooling system (4) includes auxiliary fuel tank
(401), oil well pump (402), the second filter (403), the second differential pressure transmitter device (404), the first circulating pump (405), the first wind
Cold (406), the 3rd filter (407), the 3rd differential pressure transmitter device (408), the second liquid level relay (409) and the 5th temperature pass
Sensor (410), described second liquid level relay (409) and the 5th temperature sensor (410) are arranged at described auxiliary fuel tank (401)
In, the entrance of described oil well pump (402) is connected with the oil sump (301) of pilot system (3) by the second filter (403), outlet
Being connected with auxiliary fuel tank (401), described second differential pressure transmitter device (404) is connected to the import and export two ends of the second filter (403), institute
The exit and entrance stating the first circulating pump is connected to the both sides of auxiliary fuel tank (401), described first Air cooler (406) and the 3rd
Filter (407) is successively set on the circulation line between outlet and the auxiliary fuel tank (401) of the first circulating pump (405), described
3rd differential pressure transmitter device (408) is connected to the import and export two ends of the 3rd filter (407)；Described cycle cooling system (5) includes
Second circulating pump (501), the second Air cooler (502), the 4th filter (503) and the 4th differential pressure transmitter device (504), described second
The entrance of circulating pump (501) is connected with auxiliary fuel tank (401), export by circulation line successively with described second Air cooler (502),
3rd filter (407) and main fuel tank (101) connect, and described 4th differential pressure transmitter device (504) is connected to the 4th filter
(503) import and export two ends；Described control system (6) includes the host computer at Integrated Human Machine Interaction interface, PLC, the first temperature controller
And second temperature controller, described PLC includes that CPU, I/O module, A/D module, described host computer realize two-way communication with the CPU of PLC,
Described first differential pressure transmitter device (104), the second differential pressure transmitter device (404), the 3rd differential pressure transmitter device (408), the 4th differential pressure signaling
The signal of device (504), the first liquid level relay (107) and the second liquid level relay (409) inputs with the digital signal of PLC respectively
It is connected, described dosing pump (102), oil well pump (402), the first circulating pump (405), the second circulating pump (501), solenoid directional control valve
(201) and the control system of fault alarm of human-computer interaction interface exports with the digital signal of PLC respectively and is connected, described first is warm
Degree sensor (105), the second temperature sensor (202), three-temperature sensor (204), the 4th temperature sensor (205), the
The signal of five temperature sensors (410), pressure transducer (108) and effusion meter (109) inputs phase with the analogue signal of PLC respectively
Even, the control signal of described electrically heated rod (106) is connected with the analog signal output of PLC by the first temperature controller, and described electricity adds
The control signal device of heat is connected with the analog signal output of PLC by the second temperature controller.
A kind of aero-engine high-speed bearing high/low temperature lubrication test device the most according to claim 1, it is characterised in that:
Described oil supply system (1) is disposed with on the oil feed line between the first filter (103) and pressure transducer (108)
One check valve (110) and flow speed control valve (111), the oil feed line between pressure transducer (108) and effusion meter (109) is arranged
There is the first ball valve (112)；Described oil supply system (1) also includes an overflow valve (113), and the entrance of this overflow valve (113) connects
On oil feed line between described first check valve (110) and flow speed control valve (111), outlet is connected to main fuel tank (101)；Described
Main fuel tank (101) is provided with the first liquidometer (114), and the pouring orifice of main fuel tank (101) is provided with the first air filter
(115), pressure transducer (108) place at oil feed line is additionally provided with the first Pressure gauge (116)；Described first filter
(103) being twin-tub filter, described electrically heated rod (106) quantity is two.
A kind of aero-engine high-speed bearing high/low temperature lubrication test device the most according to claim 1, it is characterised in that:
The electric heater (203) of described heating system (2) with the second temperature sensor (202) and three-temperature sensor (204) it
Between oil feed line on be disposed with the second check valve (206) and the 3rd check valve (207)；Described solenoid directional control valve (201)
The second outlet by the 4th check valve (208) be connected to described 3rd check valve (207) and three-temperature sensor (204) it
Between oil feed line on；It is additionally provided with on oil feed line between described three-temperature sensor (204) and pilot system (3)
Two ball valves (209).
A kind of aero-engine high-speed bearing high/low temperature lubrication test device the most according to claim 1, it is characterised in that:
The 3rd ball valve (411) it is provided with on return line between described oil sump (301) and oil well pump (402)；Described first Air cooler
(406) it is provided with the second Pressure gauge (412), the first wind on the circulation line between import and the first circulating pump (405) outlet
It is provided with the first thermometer (413) on circulation line between outlet and the second filter (403) import of cold (406)；Institute
Stating auxiliary fuel tank (401) and be provided with the second liquidometer (414), the pouring orifice of auxiliary fuel tank (401) is provided with the second air filter
(415).
A kind of aero-engine high-speed bearing high/low temperature lubrication test device the most according to claim 1, it is characterised in that:
It is provided with the 3rd pressure on circulation line between the import of described second Air cooler (502) and the second circulating pump (501) outlet
Table (505), the circulation line between outlet and the 3rd filter (407) import of the second Air cooler (502) is provided with second
Thermometer (506).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620718498.XU CN205843960U (en) | 2016-07-08 | 2016-07-08 | A kind of aero-engine high-speed bearing high/low temperature lubrication test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620718498.XU CN205843960U (en) | 2016-07-08 | 2016-07-08 | A kind of aero-engine high-speed bearing high/low temperature lubrication test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205843960U true CN205843960U (en) | 2016-12-28 |
Family
ID=58150472
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620718498.XU Withdrawn - After Issue CN205843960U (en) | 2016-07-08 | 2016-07-08 | A kind of aero-engine high-speed bearing high/low temperature lubrication test device |
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| Country | Link |
|---|---|
| CN (1) | CN205843960U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106053071A (en) * | 2016-07-08 | 2016-10-26 | 河南科技大学 | Aeroengine high-speed bearing high and low-temperature lubrication test apparatus and control method |
| CN109186881A (en) * | 2018-09-21 | 2019-01-11 | 中国船舶重工集团公司第七〇九研究所 | It is a kind of for detecting the experimental rig and its test method of fluid slip ring performance |
-
2016
- 2016-07-08 CN CN201620718498.XU patent/CN205843960U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106053071A (en) * | 2016-07-08 | 2016-10-26 | 河南科技大学 | Aeroengine high-speed bearing high and low-temperature lubrication test apparatus and control method |
| CN106053071B (en) * | 2016-07-08 | 2018-06-29 | 河南科技大学 | A kind of aero-engine high-speed bearing high/low temperature lubrication test device and control method |
| CN109186881A (en) * | 2018-09-21 | 2019-01-11 | 中国船舶重工集团公司第七〇九研究所 | It is a kind of for detecting the experimental rig and its test method of fluid slip ring performance |
| CN109186881B (en) * | 2018-09-21 | 2020-08-25 | 中国船舶重工集团公司第七一九研究所 | Testing device and testing method for detecting performance of fluid slip ring |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20161228 Effective date of abandoning: 20180629 |