CN109506940B - Impeller type radial oil collecting ring test method for civil aviation engine lubricating oil system - Google Patents
Impeller type radial oil collecting ring test method for civil aviation engine lubricating oil system Download PDFInfo
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- CN109506940B CN109506940B CN201811470296.8A CN201811470296A CN109506940B CN 109506940 B CN109506940 B CN 109506940B CN 201811470296 A CN201811470296 A CN 201811470296A CN 109506940 B CN109506940 B CN 109506940B
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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
- G01M15/00—Testing of engines
Abstract
The invention discloses a testing method of an impeller type radial oil collecting ring of a civil aircraft engine lubricating oil system, which provides a testing method for researching the influence of the difference of an oil collecting ring structure and different oil supply pressures, oil supply temperatures, nozzle installation angles and test rotating speeds on the oil supply efficiency of an aircraft engine, obtaining the optimal matching of the oil collecting ring structure and the oil supply pressures, the oil supply temperatures, the oil supply angles and the test rotating speeds and obtaining the optimal oil collecting ring performance, thereby meeting the requirement of the design of the impeller type radial oil collecting ring of the modern civil aircraft engine.
Description
Technical Field
The invention belongs to the field of a civil aviation engine lubricating oil system, and particularly relates to a testing method for an impeller type radial oil collecting ring of the civil aviation engine lubricating oil system, which is mainly used for a performance test of the impeller type radial oil collecting ring of the civil aviation engine lubricating oil system.
Background
The main shaft bearing of the aircraft engine is one of the key parts on the engine, and the working performance and the service life of the bearing are directly influenced by the lubrication condition of the bearing. Because the high-pressure rotor bearing has small space, the DN value is high, and the lubrication difficulty is high. The oil collecting ring structure is generally adopted in the field of civil aviation engines, and the problems can be well solved. The oil receiving ring oil receiving port on the fixed nozzle and the rotary main shaft has a certain angle, lubricating oil is sprayed into the oil receiving ring through the nozzle under certain oil supply pressure, oil spray holes with different apertures are formed in the oil receiving ring, and the lubricating oil is fed into oil supply points on different positions under the action of certain rotating speed and centrifugal force, so that a series of key problems of small space, high DN value and high lubrication difficulty of a high-pressure rotor bearing are effectively solved. Therefore, the oil collecting ring is an indispensable key component in an aircraft engine lubricating oil system and is extremely important to the design of the aircraft engine. In order to master the influence of the difference of the oil collecting ring structure and the different oil supply pressure, oil supply temperature, nozzle installation angle and test rotating speed on the oil supply efficiency of the aircraft engine, the optimal matching of the oil collecting ring structure, the oil supply pressure, the oil supply temperature, the oil supply angle and the test rotating speed is sought, the optimal oil collecting ring performance is obtained, and the oil collecting ring test of the aircraft engine lubricating oil system is essential. Meanwhile, the oil collecting ring performance test is developed and verified, the method is a main method and an important means for comprehensively, completely and effectively verifying the oil collecting ring performance of the lubricating oil system at present, and is a necessary and important ring for designing the oil collecting ring of the lubricating oil system of the civil aircraft engine.
Disclosure of Invention
The purpose of the invention is as follows: the invention relates to a method for testing the performance of an impeller type radial oil collecting ring of a lubricating oil system of a civil aircraft engine, which is used for researching the difference of an oil collecting ring structure and the influence of different oil supply pressures, oil supply temperatures, nozzle installation angles and test rotating speeds on the oil supply efficiency of the aircraft engine, obtaining the optimal matching between the optimal oil collecting ring structure and the oil supply pressures, the oil supply temperatures, the oil supply angles and the test rotating speeds, and obtaining the optimal oil collecting ring performance, thereby meeting the design requirement of the impeller type radial oil collecting ring of the modern civil aircraft engine.
The technical scheme of the invention is as follows:
the impeller type radial oil collecting ring test method for the civil aviation engine lubricating oil system comprises the following steps: the first step is as follows: starting each subsystem, wherein each subsystem comprises a cooling water pump, an air compressor and a test main structure fulcrum bearing for returning oil to the pump; the second step is that: starting a test lubricating oil supply and return oil pump; the third step: starting a driving system, and adjusting the rotating speed of the main shaft to be less than 5000r/min for low-speed operation; the fourth step: starting a test lubricating oil heating device, heating the test lubricating oil, and heating the lubricating oil to set the target temperature; the fifth step: when the temperature of the test lubricating oil reaches the requirement, starting the lubricating oil to keep the temperature, and adjusting the oil supply pressure of the test lubricating oil to the test pressure; and a sixth step: after the oil supply temperature and the oil supply pressure of the test lubricating oil meet the requirements and are stable, adjusting the test rotating speed to the test rotating speed; seventhly, after each test parameter meets the test requirement, stably running for not less than 5min, starting a two-position three-way electromagnetic valve control program, and collecting oil of an oil collecting ring; and eighth step, collecting the oil recovery rate for not less than 1min, and simultaneously recording each test parameter, and ninth step: after the first group of oil recovery rate is collected, continuously collecting the oil recovery rate under the same test rotating speed, oil supply flow, oil supply temperature and oil supply pressure, and repeatedly measuring for 3 times; the tenth step: and after all the oil receiving rates are collected, measuring the collected oil receiving volume by using the measuring cup, recording related parameters and storing the test data in a tidy way.
Preferably, the target temperature in the fourth step is 80 ℃.
Preferably, the test pressure in the fifth step is 0.2-0.5 MPa.
Preferably, the test pressure in the fifth step is 0.3 MPa.
Preferably, 11800rpm to 12300rpm is used as the test rotation speed in the sixth step.
Preferably, the test parameters in the eighth step include test rotation speed, oil supply flow, oil supply temperature and oil supply pressure.
The invention has the beneficial effects that: the test method provided by the invention is used for researching the influence of the difference of the oil collecting ring structure and the different oil supply pressure, oil supply temperature, nozzle installation angle and test rotating speed on the oil supply efficiency of the aircraft engine, obtaining the optimal matching between the oil collecting ring structure and the oil supply pressure, the oil supply temperature, the oil supply angle and the test rotating speed, and obtaining the optimal oil collecting ring performance, so that the test method is provided, and the design requirement of the impeller type radial oil collecting ring of the modern civil aircraft engine is met.
Drawings
FIG. 1 is a graph showing the variation of the oil recovery rate with the rotation speed under the conditions of a nozzle injection angle of 55 degrees, a lubricating oil pressure of 0.3MPa and a lubricating oil temperature (80 +/-2) DEG C.
Detailed Description
The invention will be further described with reference to the accompanying drawings.
The whole test process is illustrated by taking a simulated engine state test as an example as follows:
the oil collecting ring test piece of the test is characterized in that the nozzle number is XXX and the nozzle spraying angle is 55 degrees according to the oil collecting ring component XX. The oil supply pressure is 0.3MPa, and the oil supply temperature is (80 +/-2) DEG C. The test conditions are shown in Table 1, and the operation procedures are as follows:
TABLE 1 test conditions
| Serial number | Pressure before nozzle (MPa) | Rotational speed (rpm) |
| 1 | 0.3 | 8989 |
| 2 | 0.3 | 11841 |
| 3 | 0.3 | 12257 |
| 4 | 0.3 | 12430 |
| 5 | 0.3 | 12771 |
| 6 | 0.3 | 12912 |
| 7 | 0.3 | 13558 |
The first step is as follows: starting each subsystem (cooling water pump, air compressor, test main structure pivot bearing for oil return pump.
The second step is that: the test lubricant supply and return pump is started.
The third step: and starting a driving system, and adjusting the rotating speed of the main shaft to 3000r/min for low-speed operation.
The fourth step: starting the test lubricating oil heating device, heating the test lubricating oil, and heating the lubricating oil to 80 ℃.
The fifth step: and when the temperature of the test lubricating oil meets the requirement, starting the lubricating oil for heat preservation, and adjusting the oil supply pressure of the test lubricating oil to 0.3 MPa.
And a sixth step: after the oil supply temperature and the oil supply pressure of the test lubricating oil reach the requirements and are stable, the test rotating speed is adjusted to the values specified in the table 1.
The seventh step: and (3) when each test parameter meets the value shown in the table 1, stably running for 5min, starting a two-position three-way electromagnetic valve control program, and collecting oil of the oil collecting ring.
Eighth step: the oil recovery rate acquisition time is 20s, and simultaneously, all test parameters (test rotating speed, oil supply flow, oil supply temperature and oil supply pressure) are recorded.
The ninth step: after the first group of oil recovery rate is collected, the oil recovery rate under the same test rotating speed, oil supply flow, oil supply temperature and oil supply pressure is continuously collected and measured for 3 times repeatedly.
The tenth step: and after all the oil receiving rates are collected, measuring the collected oil receiving volume by using the measuring cup, recording related parameters and storing the test data in a tidy way.
And (3) completing an oil receiving rate test simulating the engine state according to parameters shown in the table 1 in sequence according to the signals, and calculating the oil receiving efficiency under different working conditions.
The oil recovery rate of the engine with the oil recovery ring and the nozzle in the engine state is shown in figure 1 along with the change curve of the rotating speed under the conditions that the injection angle of the nozzle is 55 degrees, the lubricating oil pressure is 0.3MPa and the lubricating oil temperature is (80 +/-2) DEG C.
The principle is as follows: during the oil collecting ring test, when the test rotating speed, the oil supply temperature and the oil supply pressure do not meet the requirements, the normally open valve end of the two-position three-way electromagnetic valve returns the lubricating oil to the main oil return tank pipeline, and the lubricating oil is pumped back to the main oil tank by the oil return pump, so that the lubricating oil system runs circularly. And when each test parameter meets the requirement of the oil recovery ring test task specification and stably runs for 5min, closing the normally open valve of the two-position three-way electromagnetic valve, opening the normally closed valve of the two-position three-way electromagnetic valve, and collecting oil recovery rate data.
Claims (5)
1. The impeller type radial oil collecting ring test method for the civil aviation engine lubricating oil system is characterized by comprising the following steps of:
the first step is as follows: starting each subsystem, wherein each subsystem comprises a cooling water pump, an air compressor and a test main structure fulcrum bearing for returning oil to the pump;
the second step is that: starting a test lubricating oil supply and return oil pump;
the third step: starting a driving system, and adjusting the rotating speed of the main shaft to be less than 5000r/min for low-speed operation;
the fourth step: starting a test lubricating oil heating device, heating the test lubricating oil, and heating the lubricating oil to set the target temperature;
the fifth step: when the temperature of the test lubricating oil reaches the requirement, starting the lubricating oil to keep the temperature, and adjusting the oil supply pressure of the test lubricating oil to the test pressure;
and a sixth step: after the oil supply temperature and the oil supply pressure of the test lubricating oil meet the requirements and are stable, adjusting the test rotating speed to the test rotating speed;
the seventh step: when each test parameter meets the test requirement, stably running for no less than 5min, starting a two-position three-way electromagnetic valve control program, and collecting oil from an oil collecting ring;
eighth step: the oil recovery rate acquisition time is not less than 1min, and simultaneously, all test parameters are recorded, wherein the test parameters comprise test rotating speed, oil supply flow, oil supply temperature and oil supply pressure;
the ninth step: after the first group of oil recovery rate is collected, continuously collecting the oil recovery rate under the same test rotating speed, oil supply flow, oil supply temperature and oil supply pressure, and repeatedly measuring for 3 times;
the tenth step: and after the oil recovery rate is collected, measuring the collected oil recovery volume by using the measuring cup, recording the oil recovery volume and storing all test data in a tidy way, wherein the test data comprises test rotating speed, oil supply flow, oil supply temperature, oil supply pressure and oil recovery volume.
2. The test method for the impeller-type radial oil-collecting ring of the civil aviation engine lubricating oil system according to claim 1, wherein the target temperature in the fourth step is 80 ℃.
3. The testing method for the impeller-type radial oil-collecting ring of the civil aviation engine lubricating oil system as claimed in claim 1, wherein the testing pressure in the fifth step is 0.2-0.5 MPa.
4. The test method for the impeller-type radial oil-collecting ring of the civil aviation engine lubricating oil system as defined in claim 3, wherein the test pressure in the fifth step is 0.3 MPa.
5. The method for testing the impeller-type radial oil-collecting ring of the civil aviation engine lubricating oil system as claimed in claim 1, wherein the test rotating speed in the sixth step is 11800rpm to 12300 rpm.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101520360A (en) * | 2009-04-10 | 2009-09-02 | 北京理工大学 | Turbocharger lubricating oil leakage detection device |
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| WO2013037865A1 (en) * | 2011-09-15 | 2013-03-21 | Universite Libre De Bruxelles | Method and device for monitoring a lubrication system |
| CN204900542U (en) * | 2015-06-04 | 2015-12-23 | 中航商用航空发动机有限责任公司 | Oil ring is radially received to main shaft bearing and impeller formula for aviation |
| CN105510037B (en) * | 2015-12-03 | 2018-03-30 | 中国航空动力机械研究所 | A kind of altitude pilot system of Aero-Engine Lubrication System and method |
| CN105675322A (en) * | 2016-01-13 | 2016-06-15 | 中国航空动力机械研究所 | Lubricating oil tank performance test system and method |
| CN206074261U (en) * | 2016-07-11 | 2017-04-05 | 中国人民解放军装甲兵工程学院 | Threst stand |
| CN108918152B (en) * | 2018-05-18 | 2020-10-23 | 中国航发湖南动力机械研究所 | Aeroengine test device |
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| CN101520360A (en) * | 2009-04-10 | 2009-09-02 | 北京理工大学 | Turbocharger lubricating oil leakage detection device |
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