CN109580209B - Testing device for life test of fuel oil radiator of aircraft alternating-current generator - Google Patents
Testing device for life test of fuel oil radiator of aircraft alternating-current generator Download PDFInfo
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- CN109580209B CN109580209B CN201910024285.5A CN201910024285A CN109580209B CN 109580209 B CN109580209 B CN 109580209B CN 201910024285 A CN201910024285 A CN 201910024285A CN 109580209 B CN109580209 B CN 109580209B
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Abstract
The invention discloses a test device for testing the service life of a lubricating oil burning radiator of an aircraft alternating-current generator, which comprises a lubricating oil side normal temperature system, a lubricating oil side high temperature system, a fuel oil side normal temperature system, a fuel oil side high temperature system, a refrigerating system, an automatic control system and an environment cabin. The technical scheme can realize the flow, pressure, temperature and environment temperature cyclic fatigue test of various lubricating oil radiators, under the test system, high-temperature, high-pressure and large-flow lubricating oil is introduced into a product, after the test condition is stable, automatic switching is carried out through an automatic control system, and low-temperature, low-pressure and small-flow lubricating oil is introduced into the product, so that the influences of the flow, pressure and temperature of the lubricating oil on the airplane to the service life of the product are simulated through the impact of the verification of the flow, pressure and temperature of the oil, the test flow, pressure and temperature automatically detect, adjust and collect and record detection points on a pipeline through the automatic control system, and the collection parameter feedback control and data record of the detection points are carried out.
Description
Technical Field
The invention belongs to the technical field of simulation test, relates to a simulation test technology of flow-pressure-temperature three-comprehensive impact, and particularly relates to a life test testing device for a combustion sliding radiator of an aircraft alternating-current generator.
Background
An aircraft alternator fuel radiator is an accessory on the engine for heat dissipation in the aircraft fuel system. In the prior flow-pressure-temperature three-comprehensive impact testing technology, an independent oil tank is adopted for supplying oil while lubricating oil, an independent oil tank is adopted for supplying oil while fuel oil is adopted for supplying oil, a tubular heater is adopted for heating, when a product is tested, the temperature is required to be heated to a maximum set value, the flow and the pressure simultaneously reach the maximum set values, the pressure and the flow are simultaneously adjusted to minimum set values after the maximum values of the flow, the temperature and the pressure are ensured to be simultaneously stabilized, the temperature of oil liquid begins to cool the oil liquid to the minimum set value through circulating water, and once circulation is finished after the flow, the temperature and the pressure of minimum set conditions are stabilized. The oil liquid heating rate is small in the test, the circulating water cooling rate is small, and because the oil liquid temperature is continuously switched between the high temperature condition and the low temperature condition, the oil liquid needs to be heated and cooled every time, so that the cycle time period of one cycle is too long (about 45 minutes), the flow-pressure-temperature three comprehensive impact tests are few, thousands of times and more thousands of times, and the requirements of the product development progress can not be met by the existing test conditions.
In order to solve the problem of product development progress, a more scientific, effective and practical testing device must be provided on the premise of not influencing the product service life examination so as to ensure that the test is more accurate, rapid, convenient and true on the premise of not influencing the product service life examination.
Disclosure of Invention
In order to solve the problems, the testing device can achieve the purposes of carrying out faster testing under the condition of testing requirements, automatically collecting and recording the parameters required by the testing after the testing parameters are set, and has the advantages of accurate and fast testing result, convenient assembly and disassembly and better guarantee of the product quality and the development progress.
The invention is realized by the following technical scheme:
a testing device for a service life test of a lubricating oil burning radiator of an aircraft alternating-current generator comprises an environment cabin, wherein the environment cabin is respectively connected with a lubricating oil side low-temperature system, a lubricating oil side high-temperature system, a fuel oil side low-temperature system and a fuel oil side high-temperature system;
the environment cabin, the lubricating oil side low-temperature system and the lubricating oil side high-temperature system form a lubricating oil side loop;
and the environment cabin, the fuel side low-temperature system and the fuel side high-temperature system form a fuel side loop.
Preferably, the environment cabin has a heating function, a lubricating oil inlet interface, a lubricating oil outlet interface, a fuel oil inlet interface, a fuel oil outlet interface, a product mounting support and an oil mist purification device are arranged in the environment cabin, and an oil receiving disc and a waste oil recovery device are further arranged at the bottom of the environment cabin.
Preferably, a first oil tank and a first pump are arranged in the lubricating oil side low-temperature system, a first temperature sensor and a first liquid level sensor are mounted on the first oil tank, the first oil tank is connected with the refrigerating machine system, a first pump outlet is connected with a first overflow valve, and a first pump inlet is connected with a first filter.
Preferably, a second oil tank and a second pump are arranged in the lubricating oil side high-temperature system, a second temperature sensor and a second liquid level sensor are mounted on the second oil tank, a tubular heating pipe is mounted in the second oil tank, an outlet of the second pump is connected with a second overflow valve, and an inlet of the second pump is connected with a second filter.
Preferably, a third oil tank and a third pump are arranged in the fuel side low-temperature system, a third temperature sensor and a third liquid level sensor are mounted on the third oil tank, the third oil tank is connected with an air-cooled radiator, a third pump outlet pipeline is connected with a third overflow valve, and a third filter is mounted in a third pump inlet pipeline.
Preferably, a fourth oil tank and a fourth pump are arranged in the fuel side high-temperature system, a fourth temperature sensor and a fourth liquid level sensor are mounted on the fourth oil tank, a tubular heating pipe is mounted in the fourth oil tank, the outlet of the fourth pump is connected with a fourth overflow valve, and the inlet of the fourth pump is connected with a fourth filter.
Preferably, a first electric valve and a second electric valve are arranged in the lubricating oil side loop, an inlet of the first electric valve is connected with a lubricating oil outlet pipeline, an outlet of the first electric valve is connected with the second oil tank, an inlet of the second electric valve is connected with a lubricating oil outlet pipeline, and an outlet of the second electric valve is connected with the first oil tank.
Preferably, a third electric valve, a first pneumatic angle seat valve and a second pneumatic angle seat valve are arranged in the fuel side loop, the third electric valve is installed on a fuel outlet pipeline, an inlet of the first pneumatic angle seat valve is connected with the fuel outlet pipeline, an outlet of the first pneumatic angle seat valve is connected with a third oil tank, an inlet of the second pneumatic angle seat valve is connected with the fuel outlet pipeline, and an outlet of the second pneumatic angle seat valve is connected with a fourth oil tank.
Preferably, in the fuel side loop, a fifth temperature sensor, a first pressure sensor and a first flow sensor are mounted on a fuel inlet pipeline.
Preferably, in the oil-side circuit, a sixth temperature sensor, a second pressure sensor, and a second flow sensor are mounted on an oil inlet pipe.
The invention relates to a test device for the service life of a fuel and lubricant radiator of an aircraft alternator, which comprises an environment cabin and a product arranged in the environment cabin, wherein the environment cabin has a heating function and can simulate the environment temperature of the fuel and lubricant radiator of the aircraft alternator on an engine; and the environmental chamber is also provided with an oil mist treatment device and a waste oil recovery device. The fuel-sliding system is provided with four independent oil tanks, heating pipes (the heating pipes are tubular heating pipes) are installed in the fuel-sliding high-temperature oil tank, each oil tank is provided with an independent pump, automatic switching of high and low temperatures of fuel-sliding oil can be automatically realized, the fuel-sliding system is also provided with a refrigerator system and an air-cooled radiator system, and a temperature sensor and an overflow valve are arranged in a loop.
The test device for the service life test of the fuel oil radiator of the aircraft alternating-current generator has the following characteristics:
1. the environment cabin can create high-temperature conditions through the heating device, and can meet the simulation of various high-temperature environment temperature conditions during the service life test, thereby providing a basis for the real service life of various high-temperature environment conditions in the product development process;
2. the independent design of the high-temperature and low-temperature fuel and lubricating oil tanks can solve the problem of slow temperature rise and temperature reduction in each circulation of fuel and lubricating oil, and can quickly, accurately and effectively complete a service life assessment test without influencing the test condition; the heating device is arranged in the lubricating oil burning tank, so that automatic and cyclic heating can be realized, and the heating is faster and more uniform; the refrigerating machine system and the fan radiator in the lubricating oil burning low-temperature system are used, so that the temperature of oil in the lubricating oil burning low-temperature system is stable, the temperature rise of the oil in the lubricating oil burning low-temperature system in the test process is avoided, and the test efficiency is reduced.
3. The use of the filter ensures the cleanliness requirement of oil in the system.
4. The oil mist treatment device can purify air, and is more environment-friendly and safer.
5. Sensors for temperature, pressure, flow and the like are arranged at important positions of the testing device, so that testing conditions and various parameters are monitored in real time, the trouble of manually adjusting various parameters by pure manpower in the prior art is eliminated, and the parameters of various testing conditions are accurately controlled; each sensor and each sensor signal joint cooperation use, are convenient for reduce the sensor circuit or standardize each sensor and walk the line, and the system line is chaotic when having avoided the test.
Drawings
Fig. 1 is a schematic view of the connection structure of the present invention.
In the figure: 1-a first liquid level sensor, 2-a first temperature sensor, 3-a refrigerator system, 4-a first tank, 5-a first filter, 6-a first pump, 7-a fourth electric valve, 8-a first check valve, 9-a fifth electric valve, 10-a second filter, 11-a second pump, 12-a seventh electric valve, 13-a second overflow valve, 14-a second temperature sensor, 15-a second liquid level sensor, 16-a fifth filter, 17-a sixth filter, 18-a first electric valve, 19-a second electric valve, 20-a first overflow valve, 21-a sixth electric valve, 22-a first pneumatic angle seat valve, 23-a second pneumatic angle seat valve, 24-a third electric valve, 25-a third pressure sensor, 26-a seventh temperature sensor, 27-a first flow sensor, 28-a first pressure sensor, 29-a fifth temperature sensor, 30-a second check valve, 31-a first three-way valve, 32-a second flow sensor, 33-a second pressure sensor, 34-a sixth temperature sensor, 35-a third pump, 36-a third overflow valve, 37-a third filter, 38-a first manual valve, 39-a third level sensor, 40-a third temperature sensor, 41-an air-cooled radiator, 42-a seventh filter, 43-a second tank, 44-a third tank, 45-an environmental chamber, 46-a fourth tank, 47-a level sensor, 48-an eighth temperature sensor, 49-a second manual valve, 50-a fourth filter, 51-a fourth pump, 52-a fourth overflow valve, 53-a second three-way valve, 54-a third one-way valve, 55-a fourth one-way valve, 56-a monitoring device, 57-an oil mist purification device and 58-a waste oil recovery device.
Detailed Description
The technical solution of the present invention is further described below with reference to the accompanying drawings, but the scope of the claimed invention is not limited thereto.
The oil mist purification device 57, the refrigerating machine system 3, and the air-cooled radiator 41 according to the present embodiment are all existing devices as long as the functions thereof meet the requirements. The test software selects labview software, the test system adopts an Ethernet module of an Ohlong, a control program is compiled according to test requirements, and other test equipment is assembled according to the requirements.
As shown in fig. 1, the components of the test device for testing the service life of the fuel-oil radiator of the aircraft alternator of the present invention include a first liquid level sensor 1, a first temperature sensor 2, a refrigerator system 3, a first oil tank 4, a first filter 5, a first pump 6, a fourth electric valve 7, a first check valve 8, a fifth electric valve 9, a second filter 10, a second pump 11, a seventh electric valve 12, a second overflow valve 13, a second temperature sensor 14, a second liquid level sensor 15, a fifth filter 16, a sixth filter 17, a first electric valve 18, a second electric valve 19, a first overflow valve 20, a sixth electric valve 21, a first pneumatic angle seat valve 22, a second pneumatic angle seat valve 23, a third electric valve 24, a third pressure sensor 25, a seventh temperature sensor 26, a first flow sensor 27, a first pressure sensor 28, a fifth temperature sensor 29, a second check valve 30, a first three-way valve 31, a second flow sensor 32, a second pressure sensor 33, a sixth temperature sensor 34, a third pump 35, a third relief valve 36, a third filter 37, a first manual valve 38, a third level sensor 39, a third temperature sensor 40, an air-cooled radiator 41, a seventh filter 42, a second oil tank 43, a third oil tank 44, an environmental chamber 45, a fourth oil tank 46, an oil level sensor 47, an eighth temperature sensor 48, a second manual valve 49, a fourth filter 50, a fourth pump 51, a fourth relief valve 52, a second three-way valve 53, a third check valve 54, a fourth check valve 55, a monitoring device 56, an oil mist purification device 57, and an oil recovery device 58.
The life test device for the lubricating oil burning radiator of the aircraft alternator comprises an environment cabin 45 and a product installed in the environment cabin 45, wherein a lubricating oil cavity of the product is connected to a lubricating oil system, and a fuel oil cavity is connected to a fuel oil system.
A product mounting bracket is erected in the environment chamber 45, so that the mounting posture of a product airplane is simulated, and the product airplane is conveniently and reliably connected with each pipeline; monitoring equipment is installed in the environment chamber 45, and the product state can be monitored in real time.
During testing, the product is mounted on a bracket in the environmental chamber 45, and is correspondingly connected with each inlet and outlet pipeline, and the chamber door is closed. The system interface is adjusted to be automatic, test parameters are set, the first manual valve 38 and the second manual valve 49 are opened, a start button is pressed, the first pump 6, the second pump 11, the third pump 35 and the fourth pump 51 are started, the second oil tank 43 and the fourth oil tank 46 are started, the environmental chamber 45 is started to heat, the seventh electric valve 12, the sixth electric valve 21 and the third electric valve 24 are opened, the fifth electric valve 9 is closed, the first three-way valve 31 and the second three-way valve 53 are opened to form the oil tanks, when the environmental temperature and the oil temperature reach the test requirement conditions, the system is automatically switched, the seventh electric valve 12 is closed, the fifth electric valve 9 and the first electric valve 18 are opened, the second three-way valve 53 is opened to form the product inlet, the second pneumatic angle seat valve 23 is opened, high-temperature fuel oil and oil cavities are respectively opened to the product for automatic circulation, when the flow rate, the pressure and the temperature reach the required values and are stable, the device is automatically switched, the fifth electric valve 9, the first electric valve 18 and the sixth electric valve 21 are closed, the second pneumatic angle seat valve 23 is closed, the fourth electric valve 7, the seventh electric valve 12 and the second electric valve 19 are opened, the first pneumatic angle seat valve 22 is opened, the second three-way valve 53 is opened to open the oil tank, the first three-way valve 31 is opened to be communicated with a product inlet, high-temperature combustion lubricating oil stops being introduced into a product, low-temperature combustion lubricating oil is respectively introduced into a product fuel oil cavity and a lubricating oil cavity for automatic circulation, when the flow, the pressure and the temperature reach minimum set required values and are stable, one circulation is finished, the system is automatically switched to a high-temperature condition, and the next circulation is continued.
When the temperature of the low-temperature oil tank in the fuel-slip system reaches the upper limit value, the refrigerating machine system 3 is started, the air-cooled radiator 41 is started, and the oil liquid is automatically circulated and cooled.
Meanwhile, the environmental chamber adjusts the temperature in the chamber as required, and the oil mist purification device 57 continuously cleans up the oil mist generated by the product under test to prevent the oil mist from being discharged into the air.
The invention can provide a comprehensive test environment capable of setting flow, pressure, temperature and ambient temperature for the fuel oil radiator of the aircraft alternator. Under the simulation environment, oil with certain flow, pressure and temperature is introduced into the fuel oil radiator of the aircraft alternator for checking the service life of the fuel oil radiator, the system automatically detects and adjusts each detection point on a pipeline and collects and records the detection point, and the service life of the fuel oil radiator of the aircraft alternator is verified by repeatedly impacting the flow, the pressure and the temperature of a fuel oil cavity and a fuel oil cavity of the fuel oil radiator of the aircraft alternator.
Claims (1)
1. The utility model provides an aircraft alternator fires experimental testing arrangement of lubricant radiator life-span which characterized in that: the environment-friendly oil-gas separator comprises an environment cabin (45), wherein the environment cabin (45) is respectively connected with a lubricating oil side low-temperature system, a lubricating oil side high-temperature system, a fuel oil side low-temperature system and a fuel oil side high-temperature system;
the environment cabin (45), the lubricating oil side low-temperature system and the lubricating oil side high-temperature system form a lubricating oil side loop;
the environment cabin (45), the fuel side low-temperature system and the fuel side high-temperature system form a fuel side loop;
the environment cabin (45) has a heating function, a lubricating oil inlet interface, a lubricating oil outlet interface, a fuel oil inlet interface, a fuel oil outlet interface, a product mounting support and an oil mist purification device (57) are arranged in the environment cabin (45), and an oil receiving disc and a waste oil recovery device are further arranged at the bottom of the environment cabin (45);
a first oil tank (4) and a first pump (6) are arranged in the lubricating oil side low-temperature system, a first temperature sensor (2) and a first liquid level sensor (1) are mounted on the first oil tank (4), the first oil tank (4) is connected with a refrigerating machine system (3), an outlet of the first pump (6) is connected with a first overflow valve (20), and an inlet of the first pump (6) is connected with a first filter (5);
a second oil tank (43) and a second pump (11) are arranged in the lubricating oil side high-temperature system, a second temperature sensor (14) and a second liquid level sensor (15) are installed on the second oil tank (43), a tubular heating pipe is installed in the second oil tank (43), an outlet of the second pump (11) is connected with a second overflow valve (13), and an inlet of the second pump (11) is connected with a second filter (10);
a third oil tank (44) and a third pump (35) are arranged in the fuel side low-temperature system, a third temperature sensor (40) and a third liquid level sensor (39) are mounted on the third oil tank (44), the third oil tank (44) is connected with an air-cooled radiator (41), an outlet pipeline of the third pump (35) is connected with a third overflow valve (36), and a third filter (37) is mounted in an inlet pipeline of the third pump (35);
a fourth oil tank (46) and a fourth pump (51) are arranged in the fuel side high-temperature system, a fourth temperature sensor (48) and a fourth liquid level sensor (47) are mounted on the fourth oil tank (46), a tubular heating pipe is mounted in the fourth oil tank (46), an outlet of the fourth pump (51) is connected with a fourth overflow valve (52), and an inlet of the fourth pump (51) is connected with a fourth filter (50);
a first electric valve (18) and a second electric valve (19) are arranged in the lubricating oil side loop, the inlet of the first electric valve (18) is connected with a lubricating oil outlet pipeline, the outlet of the first electric valve (18) is connected with a second oil tank (43), the inlet of the second electric valve (19) is connected with a lubricating oil outlet pipeline, and the outlet of the second electric valve (19) is connected with the first oil tank (4);
in the oil side circuit, a sixth temperature sensor (34), a second pressure sensor (33) and a second flow sensor (32) are installed on an oil inlet pipeline;
a third electric valve (24), a first pneumatic angle seat valve (22) and a second pneumatic angle seat valve (23) are arranged in the fuel side loop, the third electric valve (24) is installed on a fuel outlet pipeline, an inlet of the first pneumatic angle seat valve (22) is connected with a fuel outlet pipeline, an outlet of the first pneumatic angle seat valve (22) is connected with a third oil tank (44), an inlet of the second pneumatic angle seat valve (23) is connected with a fuel outlet pipeline, and an outlet of the second pneumatic angle seat valve (23) is connected with a fourth oil tank (46); in the fuel side loop, a fifth temperature sensor (29), a first pressure sensor (28) and a first flow sensor (27) are installed on a fuel inlet pipeline.
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| CN201910024285.5A CN109580209B (en) | 2019-01-10 | 2019-01-10 | Testing device for life test of fuel oil radiator of aircraft alternating-current generator |
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| CN201910024285.5A CN109580209B (en) | 2019-01-10 | 2019-01-10 | Testing device for life test of fuel oil radiator of aircraft alternating-current generator |
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| CN109580209B true CN109580209B (en) | 2020-11-20 |
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| CN114486275B (en) * | 2021-12-29 | 2023-06-20 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining cold edge flow of airborne air radiator |
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