A method for determining an air gas turbine engine oil filter cartridge replacement period

Abstract

The application discloses a method for determining the replacement period of an aviation gas turbine engine oil filter element, comprising the following steps: S2, obtaining the data of the kinematic viscosity, density p and dynamic viscosity v of the oil changing with the oil supply temperature according to the oil brand used by the aviation gas turbine engine; S3, establishing the relational expression of the oil volume flow of different types of gas turbine engines and the oil filter pressure difference and oil supply temperature based on relevant test data; S4, continuously calculating the oil flow of the engine according to the relational expression, the real-time measured oil filter front and rear pressure and oil supply temperature; S5, taking the oil flow of the first engine steady operation after replacing the filter element as the reference, calculating the increase proportion of the continuously monitored oil flow as the oil filter clogging ratio along with the engine operation; S6, when reaching the same engine speed, if the clogging ratio reaches the set value, it is determined that the oil filter needs to be replaced. The application can accurately determine the replacement period of the oil filter.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aviation gas turbine engines, in particular, to a method for determining the replacement cycle of an aviation gas turbine engine oil filter element. BACKGROUND

[0002] At present, aviation gas turbine engines usually adopt a closed cycle oil system, which is generally composed of oil supply, oil return and ventilation systems. A typical aviation gas turbine engine oil supply system includes an oil tank, an oil pump, a radiator, an oil filter front pressure sensor, an oil filter assembly (including an oil filter element), an oil filter rear pressure / temperature sensor, a nozzle and an oil pipeline between each accessory.

[0003] The oil filter element, as a main accessory of the oil system, has the main function of filtering impurities in the oil and providing clean oil to each lubrication point of the engine. During the use of the engine, the main sources of impurities are as follows: friction and wear of friction pairs and corrosion, oil coking or sludge. After the engine runs for a long time, impurities in the oil accumulate in the oil filter element, and the flow resistance of the oil flowing through the filter element gradually increases. When the pressure difference before and after the oil filter element reaches the opening pressure value of the bypass valve, the oil can flow through the bypass of the oil filter element to each lubrication point, but the unfiltered oil will cause safety hazards to the normal operation of the engine. Therefore, determining the replacement cycle of the oil filter element is crucial to the safe operation of the engine.

[0004] The current replacement cycle of the oil filter element is fixed usage time or replacement of the filter element according to the pressure difference before and after the oil filter element during testing by relevant professionals, but both have disadvantages:

[0005] Fixed usage time for filter replacement, there are certain differences in the engine itself and the use environment, the pollution degree of the filter element varies, and there may be early or late replacement of the filter element.

[0006] The method of determining the replacement cycle based on the pressure difference before and after the oil filter element is relatively reasonable, but the method may be greatly affected by the oil supply temperature. Under the same filter clogging condition, the same oil flow passes through the filter element, the pressure difference is larger when the oil temperature is low, and the pressure difference is smaller when the oil temperature is high. Using the pressure difference of the oil filter element to determine the replacement cycle also has the problems of early or late replacement of the filter element. SUMMARY

[0007] The present application provides a method for determining the replacement cycle of an aviation gas turbine engine oil filter element to solve the technical problem that the existing methods for determining the replacement cycle of the oil filter element all have the problems of early or late replacement of the filter element.

[0008] The technical solution adopted by the present application is as follows:

[0009] A method for determining the replacement cycle of an aviation gas turbine engine oil filter element, comprising the steps of:

[0010] S2, according to the oil mark used by the aviation gas turbine engine, obtaining the data of the kinematic viscosity, density p and dynamic viscosity v of the oil changing with the oil supply temperature;

[0011] S3, based on the engine whole machine bench test data or oil filter component test data, the relationship between the oil volume flow of different types of gas turbine engines and the oil filter pressure difference and the oil supply temperature is established, and the test data includes engine speed Ng, oil supply pressure before oil filter Pm1, oil supply pressure after oil filter Pm2 and oil supply temperature Tm;

[0012] S4, according to the relationship, the real-time measured pressure before and after the oil filter and the oil supply temperature, the oil flow of the aviation gas turbine engine is continuously calculated;

[0013] S5, taking the oil flow of the first engine steady operation after replacing the filter element as the reference, the increase ratio of the continuously monitored oil flow with the engine operation is calculated as the blockage ratio of the oil filter;

[0014] S6, when reaching the same engine speed, if the blockage ratio reaches the set value, it is determined that the oil filter needs to be replaced.

[0015] Further, it further comprises the steps of:

[0016] S1, according to the measurement needs, the positions of the pressure and temperature measuring points are determined, wherein the temperature sensor is arranged at the front or rear position of the oil filter, and the pressure sensor is arranged at the front and rear positions of the oil filter.

[0017] Further, the step S3 specifically comprises the steps of:

[0018] S31, selecting the oil supply pressure Pm1 before the oil filter, the oil supply pressure Pm2 after the oil filter and the oil supply temperature Tm corresponding to the different gas turbine rotor speeds of the engine during the test process;

[0019] S32, calculating the flow resistance of the oil filter and obtaining the density p and dynamic viscosity v data of the oil at different oil supply temperatures according to the relationship between the change of the main physical properties of the oil with temperature:

[0020] p=f(Tm)

[0021] v=f(Tm);

[0022] S33, establishing the fitting relationship between the empirical coefficient K value and the dynamic viscosity v of the oil:

[0023] According to engineering experience, the relationship between flow resistance and oil volume flow is:

[0024]

[0025] wherein: Δp is the flow resistance of the oil filter, Q is the volume flow of the oil, K is an empirical coefficient, which is fitted as a function of the dynamic viscosity;

[0026] S34, a relationship between the oil volume flow of the aero gas turbine engine and the oil filter pre- and post-pressure, the oil supply temperature is established according to the obtained empirical coefficient K, which is used for calculating the oil flow:

[0027]

[0028] wherein: ρ is the density of the oil, Q is the volume flow of the oil, K is an empirical coefficient, both K and ρ are functions of the oil supply temperature Tm.

[0029] Further, in step S31, the collected data is subjected to multi-point average processing when the engine is operated at different fuel turbine rotor speeds, corresponding to the oil filter pre-supply pressure Pm1, the oil filter post-supply pressure Pm2, and the oil supply temperature Tm during the test process.

[0030] Further, the fitting process of the empirical coefficient K includes the following steps:

[0031] S331, before this step, the engine or the vehicle pipeline needs to be modified, and the oil volume flow at different engine states is measured;

[0032] S332, when the oil flows through the oil filter, the flow resistance of the oil filter is obtained according to the pressure difference before and after the filter;

[0033] S333, according to the engine whole machine bench test data, the empirical coefficient K value between the oil volume flow and the flow resistance at different fuel turbine speeds is obtained;

[0034] S334, a fitting relationship between the empirical coefficient K value and the oil dynamic viscosity v is established, which is a linear relationship:

[0035] K = (A * v + B) * 10 -3 = (A * f(Tm) + B) * 10 -3

[0036] wherein, A and B are coefficients, A = 0.05746, B = 0.10999.

[0037] Further, for other types of engines other than the whole machine bench test, a correction coefficient K1 is determined based on the ratio of the calculation result and the theoretical design flow of the oil pump, and the calculation result is corrected, which is used for calculating the oil flow:

[0038]

[0039] The application further provides an aviation gas turbine engine oil filter element replacement cycle determination device, which comprises:

[0040] An oil parameter change with temperature data acquisition module is configured to acquire data of kinematic viscosity, density p and dynamic viscosity v of the oil changing with oil supply temperature according to an oil brand used by the aviation gas turbine engine;

[0041] An oil flow calculation formula establishment module is configured to establish a relationship formula of oil volume flow of different types of gas turbine engines, oil filter pressure difference and oil supply temperature based on engine whole machine bench test data or oil filter component test data, wherein the test data comprises engine speed Ng, oil supply pressure before the oil filter Pm1, oil supply pressure after the oil filter Pm2 and oil supply temperature Tm;

[0042] An oil flow calculation module is configured to continuously calculate the oil flow of the aviation gas turbine engine according to the relationship formula, the real-time measured pressure before and after the oil filter and the oil supply temperature;

[0043] A clogging ratio calculation module is configured to take the oil flow of the first engine steady operation after the filter element is replaced as a reference, and calculate the increase ratio of the continuously monitored oil flow as the clogging ratio of the oil filter with the engine operation;

[0044] An oil filter replacement judgment module is configured to determine that the oil filter needs to be replaced when the clogging ratio reaches a set value when reaching the same engine speed.

[0045] Further, the application further comprises:

[0046] A measuring point position determination module is configured to determine the positions of the pressure and temperature measuring points according to the measurement needs, wherein the temperature sensor is arranged at the front or rear position of the oil filter, and the pressure sensor is arranged at the front and rear positions of the oil filter.

[0047] The application further provides an electronic device, which comprises a memory, a processor and a computer program stored in the memory and capable of running on the processor, and the processor implements the steps of the aviation gas turbine engine oil filter element replacement cycle determination method when the computer program is executed.

[0048] The application further provides a storage medium, which comprises a stored program, and the program controls the device where the storage medium is located to execute the steps of the aviation gas turbine engine oil filter element replacement cycle determination method when the program is executed.

[0049] The application has the following beneficial effects:

[0050] The method for determining the replacement period of the oil filter element of the aviation gas turbine engine of the present application proposes to use the data of the engine's own pressure and temperature sensors, or only increase the pressure or temperature measuring points, calculate the oil supply flow rate through the empirical formula of the oil flow rate, judge the clogging degree of the filter element through the increase rate of the oil flow rate, and then determine the replacement period of the filter element. Compared with the method of directly using the pressure difference before and after the oil filter element, the method has the following advantages:

[0051] 1. The influence of the oil supply temperature can be eliminated. The dynamic viscosity changes significantly in the low temperature range when the oil supply temperature is different, which makes the pressure difference before and after the oil filter element larger. Under the same clogging condition, the oil filter pressure difference of the engine tested in winter is obviously larger than that in summer.

[0052] 2. Different engines have different configurations, and the pressure difference of the oil filter is different under the same pollution degree. Using the same oil filter pressure difference to judge the replacement period of the filter element has the risk of early or late replacement. The present application uses the increase rate of the oil flow rate calculated by the theoretical formula as the clogging ratio of the oil filter to make the judgment. Since the present method monitors the increase rate of the calculated flow rate, the same oil filter pressure difference is not used to judge the replacement period of the filter element, so the influence of the configuration difference of the engine can be eliminated, thereby accurately determining the replacement period of the oil filter and avoiding early or late replacement of the filter element, and ensuring the safe operation of the engine.

[0053] 3. The method does not affect or as little as possible affects the technical state of the engine, has little effect on the effectiveness of the engine test; compared with installing a flowmeter, installing a pressure or temperature sensor has much smaller modification difficulty, reduces a large amount of time and economic cost, and the pressure and temperature sensors are commonly used measuring devices, the quantity is sufficient, and are not limited by resources, and are highly adaptable.

[0054] In addition to the purposes, features and advantages described above, the present application has other purposes, features and advantages. The present application will be further described below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0055] The drawings that form a part of the present application are used to provide a further understanding of the present application, the schematic embodiments of the present application and the description thereof are used to explain the present application, and do not constitute an improper limitation on the present application. In the drawings:

[0056] Figure 1 is the flow chart of the method for determining the replacement period of the oil filter element of the aviation gas turbine engine of the preferred embodiment of the present application.

[0057] Figure 2 is the flow chart of the method for determining the replacement period of the oil filter element of the aviation gas turbine engine of another preferred embodiment of the present application.

[0058] Figure 3 is a filter working time and oil pressure difference relationship curve diagram.

[0059] Figure 4 is a filter working time and oil supply temperature relationship curve diagram.

[0060] Figure 5 is a filter working time and calculated flow relationship curve diagram.

[0061] Figure 6 is a filter working time and calculated flow increase ratio relationship curve diagram.

[0062] Figure 7 is a lubricating oil dynamic viscosity and calculated empirical coefficient fitting schematic diagram.

[0063] Figure 8 is a calculated lubricating oil volume flow and flowmeter measurement relative error schematic diagram.

[0064] Figure 9 is a data comparison schematic diagram during a certain engine test.

[0065] Figure 10 is an aviation gas turbine engine lubricating oil filter replacement cycle determination device component module schematic diagram of a preferred embodiment of the present application.

[0066] Figure 11 is an aviation gas turbine engine lubricating oil filter replacement cycle determination device component module schematic diagram of another preferred embodiment of the present application.

[0067] Figure 12 is an electronic device entity schematic block diagram of a preferred embodiment of the present application.

[0068] Figure 13 is an internal structure diagram of a computer device of a preferred embodiment of the present application. DETAILED DESCRIPTION

[0069] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different manners as defined and covered below.

[0070] As shown in Figure 1 , a preferred embodiment of the present application provides an aviation gas turbine engine lubricating oil filter replacement cycle determination method, comprising the steps of:

[0071] S2, according to the lubricating oil grade used by the aviation gas turbine engine, obtaining the data of the kinematic viscosity, the density p and the dynamic viscosity v of the lubricating oil changing with the lubricating oil supply temperature;

[0072] S3, based on engine whole machine bench test data or oil filter component test data, a relationship between the oil volume flow of different types of gas turbine engines and the differential pressure of the oil filter and the oil supply temperature is established, and the test data includes engine speed Ng, oil filter before oil supply pressure Pm1, oil filter after oil supply pressure Pm2, and oil supply temperature Tm;

[0073] S4, according to the relationship, the real-time measured pressure before and after the oil filter and the oil supply temperature, the oil flow of the aviation gas turbine engine is continuously calculated;

[0074] S5, taking the oil flow of the first engine steady operation after replacing the filter element as the reference, the increase ratio of the continuously monitored oil flow as the filter clogging ratio is calculated along with the engine operation;

[0075] S6, when reaching the same engine speed, if the clogging ratio reaches a set value, for example, the set value is 0.3, it is determined that the oil filter needs to be replaced.

[0076] The aviation gas turbine engine oil filter element replacement cycle determination method of the embodiment proposes to use the engine itself pressure and temperature sensor data, or only increase the pressure or temperature measuring point, calculate the oil supply flow through the empirical formula of the oil flow, judge the clogging degree of the filter element through the increase ratio of the oil flow, and then determine the replacement cycle of the filter element. Compared with directly using the differential pressure method before and after the oil filter element, the method mainly has the following advantages:

[0077] 1, the influence of the oil supply temperature can be excluded, the dynamic viscosity changes obviously in the low temperature range under different oil supply temperatures, and then the differential pressure before and after the oil filter element is large, and under the same clogging condition, the differential pressure of the oil filter of the engine tested in winter is obviously larger than that in summer;

[0078] 2, due to the differences in the configurations of different engines, the differential pressure of the oil filter under the same pollution degree is different, and the same differential pressure of the oil filter element is used to judge the replacement cycle of the filter element, which has the risk of early or late replacement. The application uses the increase ratio of the oil flow calculated by the theoretical formula as the clogging ratio of the oil filter to judge, since the method monitors the increase ratio of the calculated flow, the same differential pressure of the oil filter element is not used to judge the replacement cycle of the filter element, so the influence of the configuration difference of the engine can be excluded, thereby accurately determining the replacement cycle of the oil filter, avoiding early or late replacement of the filter element, and ensuring the safe operation of the engine.

[0079] 3. This method does not affect or has minimal impact on the engine's technical condition and has little impact on the effectiveness of engine testing. Compared with installing a flow meter, installing a pressure or temperature sensor is much easier to modify, reducing a lot of time and economic costs. Pressure and temperature sensors are commonly used measuring devices, are available in sufficient quantities, are not limited by resources, and are highly adaptable.

[0080] like Figure 2 As shown in another preferred embodiment of this application, the method for determining the replacement cycle of the aviation gas turbine engine lubricating oil filter element further includes the following steps:

[0081] S1. Determine the positions of pressure and temperature measuring points according to the measurement requirements. The temperature sensor is set in front of or behind the oil filter, and the pressure sensor is set in front of or behind the oil filter.

[0082] To calculate the lubricating oil flow rate, a pressure sensor needs to be installed before and after a certain component, and a temperature sensor needs to be installed before or after the component. It is recommended to choose an oil filter as the lubricating oil temperature fluctuates less. Avoid choosing components with large lubricating oil temperature variations, such as radiators.

[0083] Typically, pressure sensors are installed before and after the oil filter in aviation gas turbine engines. The pressure loss is used to determine the blockage of the oil filter element. Temperature sensors are placed before or after the oil filter to monitor the oil supply temperature of the lubrication system. We can directly use the pressure and temperature data measured by the engine's own sensors for analysis.

[0084] If the pressure before and after the lubricating oil filter or the lubricating oil supply temperature of the aviation gas turbine engine is not measured, pressure and temperature measuring points can be added before or after the lubricating oil filter depending on the engine type. The temperature of the lubricating oil measuring point can indicate the temperature of the lubricating oil when it flows through the lubricating oil filter element.

[0085] In another preferred embodiment of this application, step S3 specifically includes the following steps:

[0086] S31. Select the oil supply pressure Pm1 before the oil filter, the oil supply pressure Pm2 after the oil filter, and the oil supply temperature Tm corresponding to the engine running at different combustion rotor speeds during the test.

[0087] S32. Calculate the flow resistance of the lubricating oil filter and, based on the relationship between the main physical properties of lubricating oil and temperature, obtain the density ρ and dynamic viscosity v of the lubricating oil at different oil supply temperatures:

[0088] ρ=f(Tm)

[0089] v = f(Tm);

[0090] S33. Establish the fitting relationship between the empirical coefficient K and the dynamic viscosity v of lubricating oil:

[0091] According to engineering experience, the relationship between flow resistance and oil volume flow is:

[0092]

[0093] Wherein: Δp is the flow resistance of the oil filter, Q is the volume flow of the oil, K is an empirical coefficient, which is fitted as a function based on dynamic viscosity;

[0094] S34, according to the obtained empirical coefficient K, the relationship between the oil volume flow of the aero gas turbine engine and the oil supply temperature before and after the oil filter is established, which is used for calculating the oil flow:

[0095]

[0096] Wherein: ρ is the density of the oil, Q is the volume flow of the oil, K is an empirical coefficient, and K and ρ are both functions of the oil supply temperature Tm.

[0097] In another preferred embodiment of the application, in step S31, during the test process, the oil supply pressure Pm1 before the oil filter, the oil supply pressure Pm2 after the oil filter, and the oil supply temperature Tm corresponding to different fuel and gas turbine rotor speeds of the engine are selected, and the collected data is processed by multi-point averaging to reduce the measurement error of the sensor and improve the accuracy of the data.

[0098] In another preferred embodiment of the application, the fitting process of the empirical coefficient K includes the following steps:

[0099] S331, before performing this step, the engine or the pipeline of the test bench needs to be modified, and the oil volume flow of the engine in different states is measured;

[0100] S332, when the oil flows through the oil filter, the flow resistance of the oil filter is obtained according to the pressure difference before and after the filter;

[0101] S333, according to the engine test bench data, the empirical coefficient K value between the oil volume flow and the flow resistance at different fuel and gas turbine speeds is obtained;

[0102] S334, the fitting relationship between the empirical coefficient K value and the oil dynamic viscosity v is established, which is a linear relationship:

[0103] K=(A*v+B)*10 -3 =(A*f(Tm)+B)*10 -3

[0104] Wherein, A and B are coefficients, A=0.05746, and B=0.10999.

[0105] In another preferred embodiment of the present application, for other engine models other than the whole machine bench test, the correction coefficient K1 is determined based on the ratio of the calculation results and the theoretical design flow of the oil pump to correct the calculation results, which is used to calculate the oil flow:

[0106]

[0107] For other engine models, due to the differences in the structure of the oil filter, if the formula is directly applied, there will be some differences between the calculated volume flow and the actual situation. Designers can correct the calculation results based on the ratio of the calculation value and the theoretical design flow of the oil pump, and introduce the correction coefficient K1 to correct the calculation results, so as to calculate the accurate oil flow.

[0108] Embodiment

[0109] Based on the whole machine test data of a certain turbo-shaft engine, the empirical formula of oil flow, oil filter assembly pressure difference and oil supply temperature is established, the change of calculated oil flow is continuously monitored, the change of oil filter plugging degree with the increase of engine use time is determined, and then the replacement cycle of oil filter is determined.

[0110] 1. The oil pressure before and after the oil filter assembly in the oil supply system of the turbo-shaft engine is measured, and the oil temperature after the oil filter assembly is measured.

[0111] 2. The empirical formula of oil flow, oil filter assembly pressure difference and oil supply temperature is established by using the test data of another turbo-prop engine:

[0112]

[0113] Wherein: K and p are both functions of oil supply temperature Tm:

[0114] K = (0.05746 * v + 0.10999) * 10 -3 = (0.05746 * f(Tm) + 0.10999) * 10 -3 .

[0115] 3. The change trend of the calculated oil flow of the engine is continuously monitored, and the calculation results are shown in Table 1 (part):

[0116] Table 1

[0117] Date Test time Atmospheric temperature Ngr ECU_Pm1 ECU_Pm2 ECU_Tm Differential pressure Calculated flow rate Filter working time Increase ratio of calculated flow rate h ℃ MPa MPa ℃ MPa L / min h ％ 20230725 8.84 33.7 0.9 0.492 0.445 87.2 0.047 14.05 16.04 0.000 20230729 31.57333 29.5 0.9 0.518 0.466 81.9 0.052 13.92 38.77333 -0.926 20230805 41.8 29.7 0.9 0.503 0.452 85.8 0.051 14.22 49 1.215

[0118] At the same physical speed (0.9), with the increase of use time, the pressure difference before and after the oil filter element tends to gradually increase (see Figure 3 );

[0119] But due to the whole test time is long, atmospheric temperature gradually decreases (from summer to winter), the oil supply temperature exists certain difference (see Figure 4 ), therefore the differential pressure value exists certain fluctuation, if directly with differential pressure value to determine the replacement cycle, may cause early (winter) or late (summer) replacement oil filter element;

[0120] If with the oil flow through the theoretical experience formula as monitoring object, can see, with the engine running time increases, based on filter element before and after the differential pressure and oil supply temperature calculation oil volume flow is gradually increasing (see Figure 5 ). And the oil supply temperature change (see Figure 4 ), the influence on the calculation volume flow is smaller, therefore based on oil flow increase proportion determines the replacement cycle of oil filter element is more reasonable.

[0121] If with the calculation oil flow increase 30% as limit value, the first filter element's service time is about 450 hours, the second filter element's test time is about 550 hours (see Figure 6 ).

[0122] Engine oil flow calculation method:

[0123] 1, the oil used is Feima II synthetic lubricating oil, the main physical properties can refer to 4106 or 4050 in table 2 below.

[0124] Table 2 calculation formula of main physical properties of commonly used domestic lubricating oil with temperature change

[0125]

[0126] 2, select the data of oil volume flow, oil filter assembly inlet oil pressure, oil filter assembly outlet oil pressure and oil supply temperature corresponding to the engine running at different fuel and speed during the test (see table 3), in order to reduce the sensor measurement error, usually the above original data is processed by 25 point average.

[0127] Table 3

[0128]

[0129]

[0130] 3, calculate the flow resistance of oil filter assembly and obtain the kinematic viscosity, density and dynamic viscosity data of oil at different oil supply temperature according to the relationship between the change of main physical properties of lubricating oil with temperature.

[0131] Note: For the change relationship formula of lubricating oil other than the above table, it can be obtained from the distributor or estimated by using the domestic lubricating oil relationship formula with similar physical properties. In this example, the relationship formula of 4106 lubricating oil is used (see Table 4).

[0132] Table 4

[0133]

[0134]

[0135] The fitting formula of the dynamic viscosity of the lubricating oil and the calculation experience coefficient is established (see Figure 7 ).

[0136] K = (0.05746 * dynamic viscosity + 0.10999) * 10 -3 .

[0137] 4、The relationship formula of the volume flow of the turboprop engine lubricating oil and the pressure before and after the oil filter, the lubricating oil supply temperature is established, the volume flow of the lubricating oil and the flow meter measurement are consistent, and the maximum relative error is 2.5% (see Figure 8 ) :

[0138]

[0139] Wherein: K and p are both functions of the lubricating oil supply temperature Tm:

[0140] K = (0.05746 * dynamic viscosity + 0.10999) * 10 -3 = (0.05746 * f (Tm) + 0.10999) * 10 -3

[0141] 5、The experience formula is applied to other tests of the engine, and the change trend of the calculated volume flow of the lubricating oil and the measured volume flow is consistent in the entire running process, and the maximum relative error is 5% (see Figure 9 ).

[0142] As shown in Figure 10 , another preferred embodiment of the present application also provides a device for determining the replacement period of the lubricating oil filter element of an aero gas turbine engine, comprising:

[0143] A lubricating oil parameter change with temperature data acquisition module is configured to obtain the data of the kinematic viscosity, the density p and the dynamic viscosity v of the lubricating oil changing with the lubricating oil supply temperature according to the lubricating oil brand used by the aero gas turbine engine;

[0144] The lubricating oil flow rate calculation formula establishing module is configured to establish a relationship formula of the lubricating oil volume flow rate of different types of gas turbine engines and the lubricating oil filter pressure difference and the lubricating oil supply temperature based on engine overall bench test data or lubricating oil filter component test data, and the test data includes an engine speed Ng, a lubricating oil filter front supply oil pressure Pm1, a lubricating oil filter rear supply oil pressure Pm2, and a lubricating oil supply temperature Tm.

[0145] The lubricating oil flow rate calculation module is configured to continuously calculate the lubricating oil flow rate of the aviation gas turbine engine according to the relationship formula, the real-time measured lubricating oil filter front and rear pressures and the lubricating oil supply temperature.

[0146] The blockage ratio calculation module is configured to take the lubricating oil flow rate of the first engine steady operation after the filter element is replaced as a reference, and calculate an increase ratio of the continuously monitored lubricating oil flow rate as the blockage ratio of the lubricating oil filter as the engine operates.

[0147] The lubricating oil filter replacement judgment module is configured to determine that the lubricating oil filter needs to be replaced when the blockage ratio reaches a set value if the same engine speed is reached, and the set value is 0.3.

[0148] As shown in Figure 11 , in another preferred embodiment of the present application, the aviation gas turbine engine lubricating oil filter element replacement cycle determination device further comprises:

[0149] The measuring point position determination module is configured to determine the pressure and temperature measuring point positions according to the measurement needs, wherein the temperature sensor is arranged at the front or rear position of the lubricating oil filter, and the pressure sensor is arranged at the front and rear positions of the lubricating oil filter, respectively.

[0150] As shown in Figure 12 , another preferred embodiment of the present application further provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, and the processor implements the steps of the aviation gas turbine engine lubricating oil filter element replacement cycle determination method in the above-mentioned embodiments when executing the computer program.

[0151] As shown in Figure 13 , another preferred embodiment of the present application further provides a computer device, which can be a terminal or a living body detection server, and the internal structure diagram thereof can be as shown in Figure 13The computer device shown in the figure includes a processor, a memory and a network interface connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operating system and the computer program in the non-volatile storage medium to run. The network interface of the computer device is used to communicate with other computer devices outside through network connection. The computer program is executed by the processor to implement the steps of the above-mentioned aviation gas turbine engine oil filter replacement cycle determination method.

[0152] Those skilled in the art can understand that, Figure 13 The structure shown in the figure is only a block diagram of part of the structure related to the scheme of the present application, and does not constitute a limitation on the computer device to which the scheme of the present application is applied. The specific computer device can include more or fewer components than those shown in the figure, or combine certain components, or have a different component arrangement.

[0153] The preferred embodiment of the present application also provides a storage medium including a stored program, which, when executed, controls the device where the storage medium is located to perform the steps of the aviation gas turbine engine oil filter replacement cycle determination method in the above-mentioned embodiments.

[0154] It should be noted that the steps shown in the flowchart of the figure can be executed in a computer system such as a set of computer executable instructions, and although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that here.

[0155] The functions of the method of the present embodiment, if realized in the form of software function units and sold or used as independent products, can be stored in one or more computer readable storage media. Based on such understanding, the part of the prior art to which the present embodiment contributes or part of the technical solution can be embodied in the form of a software product stored in a storage medium, including a number of instructions for causing a computer device (which can be a personal computer, a server, a mobile computing device or a network device, etc.) to execute all or part of the steps of the method described in the various embodiments of the present application. The aforementioned storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and various media that can store program codes.

[0156] Those skilled in the art will appreciate that embodiments of the application can be readily used as software, hardware, or a combination of software and hardware. In one embodiment, the application can be implemented in software and / or firmware. In addition, those skilled in the art will further appreciate that the application can be implemented as a method, apparatus, or computer program product. Therefore, embodiments of the application can take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects all generally referred to herein as a "circuit" or "module." Furthermore, embodiments of the application can take the form of a computer program product on a computer-readable storage medium having computer program code embodied in the storage medium. The computer program code can cause a computer, processor, or other programmable data processing apparatus to effect the steps in the functionality described herein.

[0157] The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. Figure 1 The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. Figure 1 The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks.

[0158] The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. Figure 1 The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. Figure 1 The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks.

[0159] The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. Figure 1 The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. Figure 1 The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks. The computer program instructions can also be loaded onto a computer, other programmable data processing apparatus, or other programmable data processing devices to cause a series of operational steps to be performed on the computer, other programmable apparatus or other programmable devices to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide processes for implementing the functions specified in the flowchart block or blocks.

[0160] Although preferred embodiments of the application have been described herein, it will be apparent to those skilled in the art that various modifications can be made within the scope of the application. Accordingly, the appended claims are intended to embrace all such modifications and variations as fall within the scope of the application.

[0161] Obviously, many modifications and variations of the present application are possible in light of the above teachings. It is, therefore, to be understood that within the scope of the appended claims and their equivalents, the application can be practiced otherwise than as specifically described.

Claims

1. A method for determining the replacement cycle of an oil filter element for an aviation gas turbine engine, characterized in that, Including the following steps: S1. Determine the positions of pressure and temperature measuring points according to the measurement requirements. The temperature sensor is set in front of or behind the lubricating oil filter, and the pressure sensor is set in front of and behind the lubricating oil filter, respectively. S2. Based on the grade of lubricating oil used in aero gas turbine engines, obtain the kinematic viscosity and density of the lubricating oil. ρ Data on the dynamic viscosity v as a function of lubricating oil supply temperature; S3. Based on the test data of the engine whole bench or the test data of the lubricating oil filter component, establish the relationship between the lubricating oil volume flow rate and the lubricating oil filter pressure difference and the lubricating oil supply temperature of different models of gas turbine engines. The test data include engine speed Ng, lubricating oil supply pressure before lubricating oil filter Pm1, lubricating oil supply pressure after lubricating oil filter Pm2, and lubricating oil supply temperature Tm. S4. Based on the aforementioned relationship, the real-time measured pressures before and after the lubricating oil filter, and the lubricating oil supply temperature, continuously calculate and obtain the lubricating oil flow rate of the aviation gas turbine engine. S5. Using the lubricating oil flow rate during the first steady-state engine operation after filter replacement as a benchmark, calculate the percentage increase in the continuously monitored lubricating oil flow rate as the engine runs, and use this as the lubricating oil filter clogging ratio. S6. When the same engine speed is reached, if the blockage ratio reaches the set value, it is determined that the lubricating oil filter needs to be replaced. Step S3 specifically includes the following steps: S31. Select the oil supply pressure Pm1 before the oil filter, the oil supply pressure Pm2 after the oil filter, and the oil supply temperature Tm corresponding to the engine running at different combustion rotor speeds during the test. S32. Calculate the flow resistance of the lubricating oil filter and, based on the relationship between the main physical properties of lubricating oil and temperature, obtain the density of the lubricating oil at different oil supply temperatures. ρ Dynamic viscosity v data: ρ = f (Tm) v =f (Tm); S33. Establish the fitting relationship between the empirical coefficient K and the dynamic viscosity v of lubricating oil: Based on engineering experience, the relationship between flow resistance and lubricating oil volumetric flow rate is as follows: ； Where: ∆p is the flow resistance of the lubricating oil filter, Q is the volumetric flow rate of the lubricating oil, K is an empirical coefficient, and the fit is a function based on dynamic viscosity; S34. Based on the obtained empirical coefficient K, establish the relationship between the volumetric flow rate of lubricating oil in aero-gas turbine engines and the pressure before and after the lubricating oil filter, as well as the lubricating oil supply temperature, for use in calculating the lubricating oil flow rate: ； in: ρ Let be the density of the lubricating oil, Q be the volumetric flow rate of the lubricating oil, and K be an empirical coefficient. K and ρ Both are functions of the lubricating oil supply temperature Tm.

2. The method for determining the replacement cycle of the lubricating oil filter element for an aviation gas turbine engine according to claim 1, characterized in that, In step S31, during the test, the oil supply pressure Pm1 before the oil filter, the oil supply pressure Pm2 after the oil filter, and the oil supply temperature Tm corresponding to the engine running at different combustion rotor speeds are selected, and the collected data are averaged at multiple points.

3. The method for determining the replacement cycle of the lubricating oil filter element for an aviation gas turbine engine according to claim 1, characterized in that, The fitting process for the empirical coefficient K includes the following steps: S331. Before performing this step, it is necessary to modify the engine or vehicle piping and measure the lubricating oil volume flow rate under different engine conditions. S332. When lubricating oil flows through the lubricating oil filter, the flow resistance of the lubricating oil filter path is obtained based on the pressure difference before and after the filter. S333. Based on the engine bench test data, obtain the empirical coefficient K value between the lubricating oil volumetric flow rate and the flow resistance at different combustion speeds. S334. Establish the fitting relationship between the empirical coefficient K and the dynamic viscosity v of lubricating oil, and fit it into a linear relationship: K= (A * v+B)*10 -3 = (A *f (Tm) +B) *10 -3 ; Where A and B are coefficients, A=0.05746 and B=0.10999.

4. The method for determining the replacement cycle of the lubricating oil filter element for an aviation gas turbine engine according to claim 1, characterized in that, For engine models other than those tested on a full-machine bench, a correction factor K1 is determined based on the ratio of the calculated results to the theoretical design flow rate of the lubricating oil pump to correct the calculation results, which is then used to calculate the lubricating oil flow rate. 。 5. A device for determining the replacement cycle of an aviation gas turbine engine lubricating oil filter element, based on the method for determining the replacement cycle of an aviation gas turbine engine lubricating oil filter element as described in claim 1, characterized in that, include: The lubricating oil parameter variation data acquisition module is used to obtain the kinematic viscosity and density of the lubricating oil based on the grade of lubricating oil used in aero gas turbine engines. ρ Data on the dynamic viscosity v as a function of lubricating oil supply temperature; The lubricating oil flow calculation formula establishment module is used to establish the relationship between the lubricating oil volume flow rate and the lubricating oil filter pressure difference and lubricating oil supply temperature of different models of gas turbine engines based on the engine bench test data or lubricating oil filter component test data. The test data includes engine speed Ng, lubricating oil supply pressure before lubricating oil filter Pm1, lubricating oil supply pressure after lubricating oil filter Pm2, and lubricating oil supply temperature Tm. The lubricating oil flow calculation module is used to continuously calculate and obtain the lubricating oil flow of the aero gas turbine engine based on the aforementioned relationship, the real-time measured pressure before and after the lubricating oil filter, and the lubricating oil supply temperature. The clogging ratio calculation module is used to calculate the percentage increase in lubricating oil flow rate as the engine runs, based on the lubricating oil flow rate during the first steady-state operation after filter replacement. The lubricating oil filter replacement judgment module is used to determine that the lubricating oil filter needs to be replaced when the blockage ratio reaches a set value of 0.3 at the same engine speed.

6. The device for determining the replacement cycle of an aviation gas turbine engine lubricating oil filter element according to claim 5, characterized in that, Also includes: The measurement point location determination module is used to determine the location of pressure and temperature measurement points according to measurement needs. The temperature sensor is set in front of or behind the lubricating oil filter, and the pressure sensor is set in front of and behind the lubricating oil filter, respectively.

7. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the steps of the method for determining the replacement cycle of the lubricating oil filter element of an aviation gas turbine engine as described in any one of claims 1 to 4.

8. A storage medium comprising a stored program, characterized in that, When the program is running, it controls the device containing the storage medium to perform the steps of the method for determining the replacement cycle of the lubricating oil filter element of an aviation gas turbine engine as described in any one of claims 1 to 4.

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