CN108678938B - Performance degradation test method for airborne fuel pump - Google Patents
Performance degradation test method for airborne fuel pump Download PDFInfo
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- CN108678938B CN108678938B CN201810439209.6A CN201810439209A CN108678938B CN 108678938 B CN108678938 B CN 108678938B CN 201810439209 A CN201810439209 A CN 201810439209A CN 108678938 B CN108678938 B CN 108678938B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B51/00—Testing machines, pumps, or pumping installations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M37/00—Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
- F02M37/04—Feeding by means of driven pumps
- F02M37/08—Feeding by means of driven pumps electrically driven
Abstract
The invention provides a performance degradation test method for an onboard fuel pump. The nominal voltage of the on-board fuel pump was determined to be 115V, the high voltage to be 122V, and the low voltage to be 105V. And (4) selecting outlet pressure, vibration and temperature which can reflect the performance of the fuel pump most, monitoring, and setting a shutdown threshold value to judge whether the fuel pump fails. And (3) making an electrical stress cycle experimental section, wherein 25% of time input voltage is high voltage, 50% of time input voltage is nominal voltage, the rest 25% of time input voltage is low voltage, and the input voltage changes of the three experimental stages form an electrical stress cycle of a complete period. The experimental scheme is scientific and reasonable, overcomes the defects that only the failure time is recorded in the service life experiment of the fuel pump, the change condition of the product performance is ignored, and the like, and can be used for predicting the service life of the airborne fuel pump.
Description
Technical Field
The invention relates to a life prediction technology of an airborne fuel pump based on performance degradation, in particular to a performance degradation test method of the airborne fuel pump.
background
With the rapid development of the scientific and technological level, the precision of manufacturing industry and the emergence of novel composite materials, products with high reliability and long service life are more and more widely applied in the fields of aerospace, electronic industry, information industry and other industries. However, as the reliability of products is improved, for the products, enough failure life data can hardly be obtained through a life test or an accelerated life test, and even a zero failure phenomenon occurs, so that the life prediction of the long-life products is difficult to be carried out by using the traditional life prediction theory based on big data. However, the product performance degradation process contains a large amount of reliable, accurate and useful key information related to the product life, so that the product life needs to be predicted by starting from the change of product performance parameters, acquiring degradation data through a performance degradation test, and analyzing the degradation process of the product function by using the degradation data.
The on-board fuel pump is one of the core accessories of the fuel system and is one of the typical representatives of high-reliability and long-life electromechanical products on an airplane, and can provide fuel with specified flow and pressure for an engine, and the working state of the on-board fuel pump directly influences the safety and reliability of the fuel system.
In the prior art, the research focus is on fault diagnosis of the fuel pump, and due to the lack of effective test means and data of performance degradation, research literature on performance degradation tests of the fuel pump is less common.
In the similar products, the aviation hydraulic pump generally selects the rotating speed and the oil pollution degree as sensitive stress, but the applicant finds that the increase of the rotating speed of the fuel pump can cause the deflection of the working point of the pump to be larger and generate cavitation phenomenon, so the rotating speed is not suitable for being used as the sensitive stress; the aviation hydraulic pump is high in oil circulation rate and more in abrasive particle residue, but oil of the fuel pump is only circulated in a part of oil paths, so that the abrasive particles are few, the cleanliness is good, the oil pollution degree is not suitable for being used as sensitive stress, and therefore the aviation hydraulic pump method is not suitable for an airborne fuel pump. The research of the performance degradation test scheme of the airborne fuel pump needs to be carried out, the defects that no effective test means and no failure data exist in the life prediction of the fuel pump are overcome, the degradation data describing the degradation rule of the fuel pump is obtained, and therefore the characteristics of the life and the reliability of the fuel pump are deduced.
Disclosure of Invention
Aiming at the problems in the prior art, the applicant intensively studies from the following aspects and finally determines and provides a performance degradation test method for an airborne fuel pump:
(1) Stress of screening test: the stress influencing the service life of the fuel pump mainly comprises three types of rotating speed, particulate pollutants and electric stress, the working point of the pump is greatly deviated due to the increase of the rotating speed of the fuel pump, and the pump cannot normally work due to the cavitation phenomenon, so that the rotating speed is not suitable for being used as sensitive stress; the oil of the fuel pump is only circulated in a part of oil ways, the abrasive particles are few, the cleanliness is good, the acceleration efficiency of the particle pollution degree is low, and therefore the fuel pump is not suitable for being used as sensitive stress, and the electric stress is selected as test stress on the premise that the failure mechanism of the fuel pump does not change.
(2) Determining the stress level: the electric stress is selected as the test stress, the current of a fuel pump motor is increased rapidly due to overhigh electric stress, the efficiency is reduced, the heating is serious, and the fuel pump motor is burnt due to overlow electric stress, so the set test stress level is selected between the stress level of a product in normal work and the working limit of the product under the stress. The nominal voltage of the onboard fuel pump was determined to be 115V, the high voltage was 122V and the low voltage was 105V according to the specifications of reliability identification and acceptance tests (GJB899A-2009) on helicopter electrical stress.
(3) the test method and the failure criterion are as follows: the method comprises the steps of analyzing the influence of the faults of a motor of the airborne fuel pump, selecting parameters which can reflect the performance of the fuel pump most according to main fault phenomena to monitor, wherein the parameters comprise outlet pressure, temperature, vibration and the like, and formulating corresponding shutdown thresholds to judge that the fuel pump fails. The motor fault is the most main fault mode of the fuel pump, which can cause insufficient outlet pressure, violent motor vibration and abnormal temperature rise, so that the performance of the fuel pump is reflected by detecting three parameters of the outlet pressure, the vibration and the temperature. Because the vibration is usually accompanied by the abnormal synchronous occurrence of the outlet pressure signal and the temperature signal, when the threshold value is established, the failure of the fuel pump is judged by considering that the average value of the outlet pressure is less than 80 percent of the normal outlet pressure or the temperature exceeds the normal temperature range by 5 DEG C
(4) And (3) establishing a test section: and determining a test profile according to the stress level and the actual working condition of the onboard fuel pump, wherein the test profile is a graph of the electrical stress parameter for direct test and the time. The input voltage is high voltage 25% of the time, nominal voltage 50% of the time and low voltage 25% of the time, and the input voltage changes in the three test stages form a complete cycle of electrical stress cycle.
Based on the research and analysis, the technical scheme of the invention is as follows:
the method for testing the performance degradation of the onboard fuel pump is characterized by comprising the following steps: the electric stress is used as a test stress, and the nominal voltage of a fuel pump tested in the test is determined to be 115V, the high voltage is 122V, and the low voltage is 105V; applying a cyclic electrical stress to a test fuel pump motor, wherein a period of an electrical stress cycle curve is: continuously outputting 122V high voltage for 2.5 hours to a test fuel pump motor, continuously outputting 115V nominal voltage for 5 hours to the test fuel pump motor, and continuously outputting 105V low voltage for 2.5 hours to the test fuel pump motor; and acquiring a pressure signal, a vibration signal and a temperature signal of the outlet of the fuel pump to be tested in the test process, and judging whether the fuel pump fails or not according to a set outlet pressure threshold and a set temperature threshold.
further preferred scheme, the onboard fuel pump performance degradation test method is characterized in that: the criterion for judging whether the test fuel pump fails is as follows: and when the average value of the outlet pressure is less than 80% of the normal outlet pressure or the temperature exceeds the normal temperature range by 5 ℃, judging that the test fuel pump fails.
Further preferred scheme, the onboard fuel pump performance degradation test method is characterized in that: the adopted test device comprises a fuel oil system, a program-controlled power supply, a sensor system, a signal acquisition system and a control operation display system;
the fuel system comprises an oil storage tank, a test oil tank, an electromagnetic valve, a one-way valve and a pipeline; the oil outlet of the oil storage tank is connected with an input pipeline of the test oil tank through an electromagnetic valve; the test fuel pump is arranged in the test fuel tank; an output pipeline of the test oil tank is connected to an oil filling port of the oil storage tank through a one-way valve to form a closed loop and simulate an airplane fuel pump oil filling circulation process;
The program control power supply supplies power to the electromagnetic valve, the test fuel pump and the sensor system;
the sensor system comprises two vibration sensors, a temperature sensor, a pressure sensor and a high-precision pipeline flowmeter; the two vibration sensors are respectively arranged in the center of a top cover of a motor shell of the test fuel pump and on the side wall of the motor shell of the test fuel pump; the temperature sensor is immersed in fuel oil in the test oil tank and is attached to the side wall of a motor shell of the test fuel pump; the pressure sensor is arranged on an output pipeline of the test oil tank through the adapter tube and is positioned between an outlet of the test oil tank and the one-way valve; the high-precision pipeline flowmeter is arranged in an output pipeline of the test oil tank and is positioned between the pressure sensor and the one-way valve;
The signal acquisition system acquires an outlet pressure signal output by the pressure sensor, an acceleration signal output by the vibration sensor, a temperature signal output by the temperature sensor, a flow signal output by the pipeline flowmeter, and a voltage signal and a current signal which are provided for testing a fuel pump motor in the programmable power supply;
The control operation display system receives and displays the signals acquired by the signal acquisition system, sends control signals to the programmable power supply, and controls the programmable power supply to apply an electric stress load to the output voltage of the motor of the test pump according to a set electric stress cycle curve.
advantageous effects
The invention provides a performance degradation test method for an onboard fuel pump, which is used for obtaining degradation data describing a degradation rule of the fuel pump so as to deduce the service life and reliability characteristics of the fuel pump. Three stresses affecting the service life of the fuel pump are analyzed, wherein the normal work of the fuel pump is affected by the rotating speed, the acceleration efficiency of the particle pollution degree is low, and therefore the electrical stress is selected as the experimental stress. According to the reliability identification and acceptance experiment standard, the nominal voltage of the onboard fuel pump is determined to be 115V, the high voltage is determined to be 122V, and the low voltage is determined to be 105V. Because the motor fault is used as the most main fault mode of the airborne fuel pump, the insufficient outlet pressure, the violent motor vibration and the abnormal temperature rise can be caused, so that the outlet pressure, the vibration and the temperature which can reflect the performance of the fuel pump most are selected for monitoring, and the shutdown threshold value is set to judge whether the fuel pump fails or not. And (3) making an electrical stress cycle experimental section, wherein 25% of time input voltage is high voltage, 50% of time input voltage is nominal voltage, the rest 25% of time input voltage is low voltage, and the input voltage changes of the three experimental stages form an electrical stress cycle of a complete period. The experimental scheme is scientific and reasonable, overcomes the defects that only the failure time is recorded in the service life experiment of the fuel pump, the change condition of the product performance is ignored, and the like, and can be used for predicting the service life of the airborne fuel pump.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
the above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: schematic experimental section;
FIG. 2: experimental process flow chart.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
the onboard fuel pump is one of core components in an onboard fuel system and is used for oil transportation of a heat dissipation subsystem and oil transportation of an oil supply tank, and the fuel pump is required to ensure the flow and pressure requirements of the system in the oil transportation process. The main operating parameters of the fuel pump are shown in table 1:
TABLE 1 Fuel Pump Primary operating parameters
The fuel pump comprises oil pump and motor two parts, and the motor is relatively abominable because of operational environment, and the vibration is great, often has the oil and water to corrode, and the maintenance of being inconvenient for becomes the leading failure mode. The stresses affecting the service life of the fuel pump mainly comprise three types of rotation speed, particulate pollutants and electric stress, and specific analysis is shown in table 2.
TABLE 2 stress comparison analysis
According to the analysis of table 2, the increase of the rotation speed of the fuel pump causes the deviation of the working point of the pump to be large, and the pump cannot work normally due to the cavitation phenomenon, so that the rotation speed is not suitable for being used as sensitive stress. And the oil liquid of the fuel pump only circulates in a part of oil ways, so that the abrasive particles are few, the cleanliness is good, the acceleration efficiency of the particle pollution degree is low, and the acceleration efficiency is not suitable for being used as sensitive stress, so that the electrical stress is selected as experimental stress.
According to the analysis of table 2, electrical stress was chosen as experimental stress in combination with the primary failure mode. The stator magnetic flux of the fuel pump motor is close to a saturated state due to overhigh electric stress, the current is greatly increased, the efficiency of the motor is reduced, the heating is serious, the rotating speed of the motor is reduced when the voltage is too low, the heat dissipation efficiency is reduced, and the motor is easily burnt out due to the phenomenon of locked rotor. The test stress level is therefore chosen between the stress level at which the product is operating normally and the operating limit of the product at that stress. The following data in table 3 were used according to the specifications of the reliability identification and acceptance test (GJB899A-2009) for helicopter electrical stress:
TABLE 3 range of variation of electrical stress
According to the analysis of Table 3, the nominal voltage of the on-board fuel pump was 115V, the high voltage was 122V, and the low voltage was 105V in the on-board fuel pump performance degradation experiments.
The analysis of the test method is to determine reasonable test parameters according to the fault influence of the motor to reflect the performance of the fuel pump, and the fault influence of the motor of the fuel pump is shown in the table 4.
TABLE 4 Motor Fault effects
According to the fault influence analysis of table 4, the test parameters of outlet pressure, vibration and temperature are determined for the fault phenomena of insufficient pressure, severe motor vibration and abnormal temperature rise.
The system comprises a corresponding test equipment fuel system, a program control power supply, a sensor system, a signal acquisition system and a control operation display system;
the fuel system comprises an oil storage tank, a test oil tank, an electromagnetic valve, a one-way valve and a pipeline; the oil outlet of the oil storage tank is connected with an input pipeline of the test oil tank through an electromagnetic valve; the test fuel pump is arranged in the test fuel tank; an output pipeline of the test oil tank is connected to an oil filling port of the oil storage tank through a one-way valve to form a closed loop and simulate an airplane fuel pump oil filling circulation process;
The program control power supply supplies power to the electromagnetic valve, the test fuel pump and the sensor system;
The sensor system comprises two vibration sensors, a temperature sensor, a pressure sensor and a high-precision pipeline flowmeter; the two vibration sensors are respectively arranged in the center of a top cover of a motor shell of the test fuel pump and on the side wall of the motor shell of the test fuel pump; the temperature sensor is immersed in fuel oil in the test oil tank and is attached to the side wall of a motor shell of the test fuel pump; the pressure sensor is arranged on an output pipeline of the test oil tank through the adapter tube and is positioned between an outlet of the test oil tank and the one-way valve; the high-precision pipeline flowmeter is arranged in an output pipeline of the test oil tank and is positioned between the pressure sensor and the one-way valve;
The signal acquisition system acquires an outlet pressure signal output by the pressure sensor, an acceleration signal output by the vibration sensor, a temperature signal output by the temperature sensor, a flow signal output by the pipeline flowmeter, and a voltage signal and a current signal which are provided for testing a fuel pump motor in the programmable power supply;
The control operation display system receives and displays the signals acquired by the signal acquisition system, sends control signals to the programmable power supply, and controls the programmable power supply to apply an electric stress load to the output voltage of the motor of the test pump according to a set electric stress cycle curve.
The location of the test sites and shutdown thresholds in this example are determined by outfield investigations and are shown in table 5.
TABLE 5 test parameters and thresholds
According to the selected experimental stress and stress level, an electrical stress cycle experimental profile of fig. 1 is formulated, and the electrical stress of the working state of the equipment is changed according to the following requirements:
The first experimental stage: the input voltage is high voltage 25% of the time
And (3) a second experiment stage: the 50% time input voltage is the nominal voltage
and a third experimental stage: the input voltage is low for the rest 25 percent of the time
The input voltage changes of the three experimental phases constitute a complete electrical stress cycle, which is repeated throughout the experimental period.
Referring to the flow chart of the experimental steps in FIG. 2, the experimental steps are as follows:
1) and regulating the output of the programmable power supply to a nominal voltage, operating the test fuel pump for 200 hours, and measuring parameters such as vibration, outlet pressure and the like of the test fuel pump in a normal state.
2) The programmable power supply is regulated to output high voltage, and a first experimental stage is started for 2.5 hours.
3) and regulating the output of the programmable power supply to the nominal voltage, and starting a second experimental stage for 5.0 hours.
4) and regulating the output of the programmable power supply to a low voltage, and starting a third experimental stage for 2.5 hours.
5) Repeating 2) -4) until the product is down.
Compared with the prior art, the method overcomes the defects that the life test of the fuel pump only records failure time, ignores the change condition of product performance and the like, and can obtain the degradation data describing the degradation rule of the fuel pump through the degradation test, thereby deducing the characteristics of the life and the reliability of the fuel pump. The experimental results of the invention are good.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (3)
1. a method for testing the performance degradation of an airborne fuel pump is characterized by comprising the following steps: the electric stress is used as a test stress, and the nominal voltage of a fuel pump tested in the test is determined to be 115V, the high voltage is 122V, and the low voltage is 105V; applying a cyclic electrical stress to a test fuel pump motor, wherein a period of an electrical stress cycle curve is: firstly, continuously inputting 122V high voltage for 2.5 hours to a test fuel pump motor, then continuously inputting 115V nominal voltage for 5 hours to the test fuel pump motor, and finally continuously inputting 105V low voltage for 2.5 hours to the test fuel pump motor; and acquiring a pressure signal, a vibration signal and a temperature signal of the outlet of the fuel pump to be tested in the test process, and judging whether the fuel pump fails or not according to a set outlet pressure threshold and a set temperature threshold.
2. The method for testing the performance degradation of an airborne fuel pump of claim 1, wherein: the criterion for judging whether the test fuel pump fails is as follows: and when the average value of the outlet pressure is less than 80% of the normal outlet pressure or the temperature exceeds the normal temperature range by 5 ℃, judging that the test fuel pump fails.
3. The method for testing the performance degradation of the onboard fuel pump according to claim 1 or 2, characterized in that: the adopted test device comprises a fuel oil system, a program-controlled power supply, a sensor system, a signal acquisition system and a control operation display system;
The fuel system comprises an oil storage tank, a test oil tank, an electromagnetic valve, a one-way valve and a pipeline; the oil outlet of the oil storage tank is connected with an input pipeline of the test oil tank through an electromagnetic valve; the test fuel pump is arranged in the test fuel tank; an output pipeline of the test oil tank is connected to an oil filling port of the oil storage tank through a one-way valve to form a closed loop and simulate an airplane fuel pump oil filling circulation process;
the program control power supply supplies power to the electromagnetic valve, the test fuel pump and the sensor system;
The sensor system comprises two vibration sensors, a temperature sensor, a pressure sensor and a high-precision pipeline flowmeter; the two vibration sensors are respectively arranged in the center of a top cover of a motor shell of the test fuel pump and on the side wall of the motor shell of the test fuel pump; the temperature sensor is immersed in fuel oil in the test oil tank and is attached to the side wall of a motor shell of the test fuel pump; the pressure sensor is arranged on an output pipeline of the test oil tank through the adapter tube and is positioned between an outlet of the test oil tank and the one-way valve; the high-precision pipeline flowmeter is arranged in an output pipeline of the test oil tank and is positioned between the pressure sensor and the one-way valve;
The signal acquisition system acquires an outlet pressure signal output by the pressure sensor, an acceleration signal output by the vibration sensor, a temperature signal output by the temperature sensor, a flow signal output by the pipeline flowmeter, and a voltage signal and a current signal which are provided for testing a fuel pump motor in the programmable power supply;
the control operation display system receives and displays the signals acquired by the signal acquisition system, sends control signals to the program-controlled power supply, and controls the program-controlled power supply to input voltage to the motor of the fuel pump to be tested according to a set electrical stress cycle curve so as to apply an electrical stress load.
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| CN110985258B (en) * | 2019-12-30 | 2021-05-18 | 潍柴动力股份有限公司 | High-pressure oil pump fault detection method and device |
| CN113982771B (en) * | 2020-07-27 | 2023-10-27 | 纬湃汽车电子(芜湖)有限公司 | Fuel pump life assessment method and fuel pump controller thereof |
| CN113565659A (en) * | 2021-07-20 | 2021-10-29 | 河北华北柴油机有限责任公司 | Reliability assessment method for manual fuel pump |
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| GB2276919A (en) * | 1993-04-07 | 1994-10-12 | Ford Motor Co | Testing automative fuel pump |
| CN103292982B (en) * | 2013-06-05 | 2015-06-03 | 桂林电子科技大学 | Accelerated degradation testing method for LED lamp based on step stress |
| CN206592274U (en) * | 2017-01-19 | 2017-10-27 | 郑州宇通客车股份有限公司 | A kind of service life of vacuum pump test circuit based on SECO |
| CN107816430B (en) * | 2017-09-27 | 2019-04-16 | 安徽江淮汽车集团股份有限公司 | A kind of low-temperature test system of automobile fuel pump |
| CN107956621A (en) * | 2017-12-12 | 2018-04-24 | 成都航利电气有限公司 | A kind of main fuel pump performance test device |
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