A dynamic operation matching method based on an aero-engine altitude table air source unit

Abstract

The application discloses a dynamic operation matching method based on an aero-engine altitude test stand air source unit, and comprises the following steps: determining a first carrier air supply capacity, a second carrier air supply capacity and a total carrier air extraction capacity of a test carrier; determining whether the first carrier air supply capacity of the test carrier matches a first product air supply capacity of a test product, wherein the first product air supply capacity is an air supply flow rate that the test product can provide under different air supply pressures; determining whether the second carrier air supply capacity of the test carrier matches a second product air supply capacity of the test product, wherein the second product air supply capacity is an air supply flow rate that the test product can provide under different air supply temperatures; and determining whether the total carrier air extraction capacity of the test carrier matches a total product air extraction capacity of the test product, wherein the total product air extraction capacity is an air supply flow rate that the test product can provide under different air extraction pressures.

Description

Technical Field

[0001] This invention relates to the field of large-scale industrial software technology, and more specifically, to a dynamic operation matching method based on an aero-engine high-altitude air source unit. Background Technology

[0002] Test gas supply is one of the important components of high-altitude simulation and ground testing of aero-engines. Currently, aero-engine testing uses a centralized gas supply system, which is responsible for supplying gas for both the whole engine test and the test of individual components. It is characterized by uninterrupted operation throughout the year, multiple tasks carried out in succession, diversified processes, and a wide variety of equipment.

[0003] The test gas supply system needs to handle dozens of test gas supply tasks every week. The conventional queuing mode can no longer meet the current requirements. The issuance of multiple gas supply parallel tasks requires a lot of technical analysis work. Conducting research on dynamic control technology of high-altitude test gas source units can automatically, efficiently and more reliably implement relevant tasks, and provide strong support for the scientific arrangement of tests.

[0004] The gas supply system is large and complex, with each piece of equipment operating on a single line. Any uncontrollable link will greatly affect the normal operation of the engine test. The gas supply system is similar to the flight control system of a civil aircraft. It is necessary to grasp the real-time dynamics of the entire system in order to provide comprehensive and solid information support for the correct issuance of test commands. The research on dynamic control technology of test gas supply is to carry out related work.

[0005] The high-altitude test gas supply system is complex, with numerous pieces of equipment. In addition to conducting testing missions each year, it also undertakes a significant amount of maintenance, upkeep, and repair work. Because the gas supply system is centralized, maintenance work can generally only be scheduled during breaks in testing. Given the consistently heavy workload throughout the year, maximizing resource and time efficiency through effective methods to ensure the implementation of maintenance work is crucial. Research on dynamic control technology for test gas supply can provide a basis for sound decision-making and is an objective necessity for modern equipment management.

[0006] With the development of engine research and development, the management and control of testing also need to improve the level of lean management. Procedural, automated, and intelligent diagnosis, judgment, and information sharing are becoming increasingly important for such a complex system as gas supply.

[0007] However, the existing gas supply system has a low level of testing and equipment management, resulting in low utilization of testing equipment and low testing efficiency and poor quality. Summary of the Invention

[0008] To address at least one of the problems described in the background section, the present invention provides a dynamic operation matching method based on the high-altitude air source unit of an aero-engine.

[0009] According to one aspect of the present invention, a dynamic operation matching method based on an aero-engine high-altitude test air source unit is provided, comprising:

[0010] Determine the first carrier gas supply capacity, the second carrier gas supply capacity, and the total carrier gas extraction capacity of the test carrier, wherein the first carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply pressures, the second carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply temperatures, and the total carrier gas extraction capacity is the gas flow rate that the test carrier can provide under different gas extraction pressures.

[0011] Determine whether the first carrier gas supply capacity of the test carrier matches the first product gas supply capacity of the test sample, wherein the first product gas supply capacity is the gas flow rate that the test sample can provide under different gas supply pressures;

[0012] Determine whether the gas supply capacity of the second carrier of the test carrier matches the gas supply capacity of the second product of the test sample, wherein the gas supply capacity of the second product is the gas flow rate that the test sample can provide at different gas supply temperatures;

[0013] Determine whether the total pumping capacity of the test carrier matches the total pumping capacity of the test product, wherein the total pumping capacity of the product is the air supply flow rate that the test product can provide under different pumping pressures.

[0014] Optionally, the second carrier gas supply capacity includes the carrier positive temperature gas supply capacity and the carrier negative temperature gas supply capacity, wherein the carrier positive temperature gas supply capacity is the gas flow rate that the test carrier can provide at different positive temperatures, and the carrier negative temperature gas supply capacity is the gas flow rate that the test carrier can provide at different negative temperatures.

[0015] Optionally, the total pumping capacity of the carrier includes the pumping capacity of the first carrier and the pumping capacity of the second carrier, wherein the pumping capacity of the first carrier is the volumetric flow rate that the test carrier can provide under different pumping pressures, and the pumping capacity of the second carrier is the mass flow rate that the test carrier can provide under different pumping pressures.

[0016] Optionally, determining whether the gas supply capacity of the second carrier of the test carrier matches the gas supply capacity of the second product of the test sample includes:

[0017] Determine whether the positive temperature gas supply capacity of the test sample is within the range of the positive temperature gas supply capacity of the test carrier, wherein the positive temperature gas supply capacity is the gas flow rate that the test sample can provide at different positive temperatures;

[0018] Determine whether the negative temperature gas supply capacity of the test sample is within the range of the negative temperature gas supply capacity of the test carrier, wherein the negative temperature gas supply capacity is the gas flow rate that the test sample can provide at different negative temperatures.

[0019] Optionally, determining whether the total pumping capacity of the test carrier matches the total pumping capacity of the test sample includes:

[0020] Determine whether the first product pumping capacity of the test sample is within the range of the first carrier pumping capacity of the test carrier, wherein the first product pumping capacity is the pumping volume flow rate that the test sample can provide under different pumping pressures.

[0021] Determine whether the second product pumping capacity of the test sample is within the range of the second carrier pumping capacity of the test carrier, wherein the second product pumping capacity is the pumping mass flow rate that the test sample can provide under different pumping pressures.

[0022] According to another aspect of the present invention, a dynamic operation matching device based on an aero-engine high-altitude test air source unit is provided, comprising:

[0023] The determination module is used to determine the first carrier gas supply capacity, the second carrier gas supply capacity, and the total carrier gas extraction capacity of the test carrier, wherein the first carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply pressures, the second carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply temperatures, and the total carrier gas extraction capacity is the gas flow rate that the test carrier can provide under different gas extraction pressures.

[0024] The first matching module is used to determine whether the first carrier gas supply capacity of the test carrier matches the first product gas supply capacity of the test sample, wherein the first product gas supply capacity is the gas flow rate that the test sample can provide under different gas supply pressures.

[0025] The second matching module is used to determine whether the second carrier gas supply capacity of the test carrier matches the second product gas supply capacity of the test sample, wherein the second product gas supply capacity is the gas flow rate that the test sample can provide at different gas supply temperatures.

[0026] The third matching module is used to determine whether the total pumping capacity of the test carrier matches the total pumping capacity of the test product, wherein the total pumping capacity of the product is the air supply flow rate that the test product can provide under different pumping pressures.

[0027] Optionally, the second carrier gas supply capacity includes the carrier positive temperature gas supply capacity and the carrier negative temperature gas supply capacity, wherein the carrier positive temperature gas supply capacity is the gas flow rate that the test carrier can provide at different positive temperatures, and the carrier negative temperature gas supply capacity is the gas flow rate that the test carrier can provide at different negative temperatures.

[0028] Optionally, the total pumping capacity of the carrier includes the pumping capacity of the first carrier and the pumping capacity of the second carrier, wherein the pumping capacity of the first carrier is the volumetric flow rate that the test carrier can provide under different pumping pressures, and the pumping capacity of the second carrier is the mass flow rate that the test carrier can provide under different pumping pressures.

[0029] According to another aspect of the present invention, a computer-readable storage medium is provided, the storage medium storing a computer program for performing the methods described in any of the above aspects of the present invention.

[0030] According to another aspect of the present invention, an electronic device is provided, the electronic device comprising: a processor; a memory for storing executable instructions of the processor; the processor being configured to read the executable instructions from the memory and execute the instructions to implement the method described in any of the preceding aspects of the present invention.

[0031] Compared with existing technologies, this invention can be widely applied to the dynamic operation matching of gas source units for aero-engines and gas turbines, improve the testing and equipment management level of gas source supply systems, explore automated control of the process flow of gas source units for aero-engine test high-altitude test benches and dynamic control of equipment technical status, improve the utilization rate of test equipment, improve the testing efficiency and quality of test equipment, and provide technical support for the engineering application of dynamic control of gas source units for aero-engine test high-altitude test benches in the future. Attached Figure Description

[0032] Exemplary embodiments of the present invention can be more fully understood by referring to the following figures:

[0033] Figure 1 This is a flowchart illustrating a dynamic operation matching method for an aero-engine high-altitude test air source unit provided by an exemplary embodiment of the present invention.

[0034] Figure 2 This is a schematic diagram of the gas supply principle of a gas source unit provided in an exemplary embodiment of the present invention;

[0035] Figure 3 This is a diagram showing the relationship between the gas supply pressure and the gas supply flow rate of a gas source unit provided in an exemplary embodiment of the present invention;

[0036] Figure 4 This is a schematic diagram of the positive temperature air supply capability of a high-altitude cabin provided by an exemplary embodiment of the present invention;

[0037] Figure 5 This is a schematic diagram of the negative temperature air supply capability of a high-altitude cabin provided by an exemplary embodiment of the present invention;

[0038] Figure 6 This is a schematic diagram of the air extraction capability of a high-altitude cabin provided in an exemplary embodiment of the present invention;

[0039] Figure 7 This is a schematic diagram illustrating the relationship between simulated temperature and flow rate in a high-altitude cabin, provided by an exemplary embodiment of the present invention.

[0040] Figure 8 This is a schematic diagram of the air extraction volume flow rate of a high-altitude cabin at various altitudes, provided by an exemplary embodiment of the present invention;

[0041] Figure 9 This is a graph showing the maximum extraction mass flow rate at various altitudes of a certain high-altitude cabin, provided by an exemplary embodiment of the present invention.

[0042] Figure 10 This is a schematic diagram of the structure of a dynamic operation matching device based on an aero-engine high-altitude test air source unit provided in an exemplary embodiment of the present invention;

[0043] Figure 11 This is a structural diagram of an electronic device provided in an exemplary embodiment of the present invention. Detailed Implementation

[0044] Hereinafter, exemplary embodiments according to the present invention will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of the present invention, and not all embodiments of the present invention. It should be understood that the present invention is not limited to the exemplary embodiments described herein.

[0045] It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of the invention.

[0046] Figure 1 A flowchart illustrating the dynamic operation matching method for aero-engine high-altitude test air source unit provided by this invention is shown. Figure 1 As shown, the dynamic operation matching method based on the high-altitude test air source unit of an aero-engine includes:

[0047] Step S101: Determine the first carrier gas supply capacity, the second carrier gas supply capacity, and the total carrier gas extraction capacity of the test carrier, wherein the first carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply pressures, the second carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply temperatures, and the total carrier gas extraction capacity is the gas flow rate that the test carrier can provide under different gas extraction pressures.

[0048] In this embodiment of the invention, the test vehicle is, for example, a high-altitude chamber, and the test object is, for example, an engine. Assuming the high-altitude chamber has six gas generator units connected in parallel, the maximum gas flow rate of the high-altitude chamber reaches 276 kg / s, the gas pressure is <350 kPa, and the temperature is 40℃~200℃. The gas supply method of the six gas generator units is as follows: Figure 2 As shown, the air supply capacity of this high-altitude cabin is as follows: Figure 3 As shown. Alternatively, assuming a high-altitude cabin has two gas supply units connected in parallel, the maximum gas supply flow rate of the high-altitude cabin reaches 210 kg / s, the gas supply pressure is <1000 kPa, and the temperature is 40℃~200℃.

[0049] Optionally, the second carrier gas supply capacity includes the carrier positive temperature gas supply capacity and the carrier negative temperature gas supply capacity, wherein the carrier positive temperature gas supply capacity is the gas flow rate that the test carrier can provide at different positive temperatures, and the carrier negative temperature gas supply capacity is the gas flow rate that the test carrier can provide at different negative temperatures.

[0050] In this embodiment of the invention, based on the analysis of a certain high-altitude chamber test object, three low-pressure heating furnaces can basically meet the simulation requirements of high-temperature test points on the entire envelope. Here, we only analyze the temperature range that a certain high-altitude chamber can simulate when the gas supply pressure is below 350 kPa and three low-pressure heating furnaces are used.

[0051] 1) Positive temperature

[0052] The simulated temperature can be considered in two segments:

[0053] a) Temperature between 40 and 150℃

[0054] For temperatures between 40 and 150°C, the unit directly supplies air (up to approximately 180°C), and the air supply temperature is regulated by adjusting the unit's aftercooler. Therefore, the flow rate within this temperature range is the maximum air supply flow rate of the unit, 276 kg / s.

[0055] b) Temperature between 150 and 320℃

[0056] The design temperature limit for a certain high-altitude cabin piping network and forecourt is 350℃. Considering the temperature loss from the main air supply pipe to the convergence section in the forecourt, the simulated engine inlet limit temperature is approximately 320℃. Within this temperature range, it is necessary to mix the unit's supply air with the high-temperature air heated by the heater. The heater outlet temperature is considered to be 550℃ (limit). The formula for calculating the highest simulated temperature under a certain airflow is as follows:

[0057] T=[70×550+(Wa-70)×150] / Wa

[0058] Where: Wa (kg / s) is the air flow rate; T (°C) is the highest temperature that can be simulated;

[0059] In the formula, 550 is the maximum heating limit of the heating furnace, 70 is the maximum heating flow rate of the heating furnace, and 150 is the direct gas supply temperature of the unit.

[0060] Based on the above analysis, the positive temperature air supply capacity of a certain high-altitude cabin is as follows: Figure 4 As shown.

[0061] 2) Negative temperature

[0062] Due to factors such as temperature loss, the temperature of the drying gas is considered to be 12℃; the minimum temperature that the expansion turbine can reduce is considered to be -65℃.

[0063] The simulated temperature can be considered in two segments:

[0064] a) Flow rate < 70 kg / s:

[0065] A certain high-altitude cabin can simulate a minimum temperature of -65℃.

[0066] b) Flow rate between 70 and 250 kg / s:

[0067] Based on the current construction of the drying and cooling pipeline network at the Mianyang base, the maximum flow rate of the mixed negative-temperature air supply is 250 kg / s. The formula for calculating the lowest simulated temperature under a given air flow rate is as follows:

[0068] T=[70×(-65)+(Wa-70)×12] / Wa

[0069] Where Wa (kg / s) is the air flow rate; T (°C) is the lowest temperature that can be simulated.

[0070] Based on the above analysis, the negative temperature air supply capacity of a certain high-altitude cabin is as follows: Figure 5 As shown (temperature loss along the pipeline is not considered).

[0071] Optionally, the total pumping capacity of the carrier includes the pumping capacity of the first carrier and the pumping capacity of the second carrier, wherein the pumping capacity of the first carrier is the volumetric flow rate that the test carrier can provide under different pumping pressures, and the pumping capacity of the second carrier is the mass flow rate that the test carrier can provide under different pumping pressures.

[0072] In this embodiment of the invention, when two pumping units are connected in parallel, the pressure range of the first pumping unit is 12 kPa to 30 kPa, and when two pumping units are connected in series, the pressure range of the second pumping unit is 2.5 kPa to 12 kPa.

[0073] a) 12 ≤ Pm ≤ 30 kPa

[0074] The volumetric flow rate of the air extraction can reach 47250 m3 / min.

[0075] d) 2.5 ≤ Pm ≤ 12 kPa

[0076] The volumetric flow rate of the air extraction system can reach 36,000 m³ / min.

[0077] The formula for calculating the pumping mass flow rate under a certain Pm pressure is as follows:

[0078] Wa=(Q×Pm×1000) / (RT×60)

[0079] Where: Wa is the mass flow rate of the extracted gas, in kg / s; Q is the volumetric flow rate of the extracted gas, in m3 / min; R is the gas constant, in J / (kgK); T is the gas temperature after the exhaust cooler, 313.15K; Pm is the pressure of the main extraction pipe, in kPa.

[0080] Based on the above analysis, the pumping capacity is as follows: Figure 6 As shown.

[0081] Step S102: Determine whether the first carrier gas supply capacity of the test carrier matches the first product gas supply capacity of the test sample, wherein the first product gas supply capacity is the gas flow rate that the test sample can provide under different gas supply pressures;

[0082] In this embodiment of the invention, it is necessary to determine whether the engine's air supply capacity matches the air supply capacity of the air source unit in a certain high-altitude chamber. Specifically, it is determined whether the engine's air supply flow rate is within the maximum air supply flow rate range of the air source unit, and whether the engine's air supply pressure is within the maximum air supply pressure range of the air source unit. Currently, the maximum air supply flow rate of the certain high-altitude chamber is 276 kg / s, and the air supply pressure range is 2.5–350 kPa. If both the engine's air supply flow rate and air supply pressure are within the maximum air supply flow rate or pressure range of the air source unit, it proves that the engine's air supply capacity matches the air supply capacity of the air source unit in the certain high-altitude chamber. This means that the air supply capacity of the high-altitude chamber matches the air supply capacity of the engine, laying the foundation for subsequent testing of the engine within the high-altitude chamber.

[0083] Step S103: Determine whether the gas supply capacity of the second carrier of the test carrier matches the gas supply capacity of the second product of the test sample, wherein the gas supply capacity of the second product is the gas flow rate that the test sample can provide at different gas supply temperatures;

[0084] Optionally, determining whether the second carrier gas supply capacity of the test carrier matches the second product gas supply capacity of the test sample includes: determining whether the positive temperature gas supply capacity of the test sample is within the range of the positive temperature gas supply capacity of the test carrier, wherein the positive temperature gas supply capacity is the gas flow rate that the test sample can provide at different positive temperatures; and determining whether the negative temperature gas supply capacity of the test sample is within the range of the negative temperature gas supply capacity of the test carrier, wherein the negative temperature gas supply capacity is the gas flow rate that the test sample can provide at different negative temperatures.

[0085] In this embodiment of the invention, it is necessary to determine whether the positive and negative temperature air supply capabilities of the engine match the positive and negative temperature air supply capabilities of the air source unit in a certain high-altitude cabin. That is, to determine whether the relationship between the engine's air supply temperature and air supply flow rate is... Figure 7 Within the indicated test range. Figure 7 In the medium-high temperature envelope, the gas is directly supplied by the unit or mixed with high-temperature gas heated by the high-temperature furnace. In the negative temperature envelope, dry gas is mixed with negative temperature gas cooled by the expansion turbine. In the mixing envelope, atmospheric gas intake, dry gas supply, or mixing of dry gas and gas directly supplied by the unit are used.

[0086] When analyzing negative temperature gas supply, special attention should be paid to adjusting the pressure before the valve (i.e., Pb pressure) to around 120 kPa. It should not be too high, otherwise it will affect the cooling capacity of the expansion turbine.

[0087] Individual analysis was conducted on engine simulation parameters at test points near the capability boundary of a certain high-altitude cabin, such as a flow rate of 270 kg / s, a pressure of 2.5 kPa or 350 kPa, and at other test points. Figure 7 When analyzing the temperature near the envelope, factors such as adjustment margin need to be considered to determine whether a certain high-altitude cabin can meet the simulation requirements.

[0088] Step S104: Determine whether the total pumping capacity of the test carrier matches the total pumping capacity of the test product, wherein the total pumping capacity of the product is the air supply flow rate that the test product can provide under different pumping pressures.

[0089] Optionally, determining whether the total pumping capacity of the test carrier matches the total pumping capacity of the test sample includes: determining whether the first product pumping capacity of the test sample is within the range of the first carrier pumping capacity of the test carrier, wherein the first product pumping capacity is the pumping volumetric flow rate that the test sample can provide under different pumping pressures; and determining whether the second product pumping capacity of the test sample is within the range of the second carrier pumping capacity of the test carrier, wherein the second product pumping capacity is the pumping mass flow rate that the test sample can provide under different pumping pressures.

[0090] In this embodiment of the invention, the total pumping capacity of a high-altitude compartment can be analyzed to determine whether it matches the total pumping capacity of an engine, based on both volumetric flow rate and mass flow rate. The specific steps for analysis based on volumetric flow rate are as follows:

[0091] 1) The simulated altitude of the test point was determined to be within the testable range of a certain high-altitude cabin. Due to altitude limitations, the simulated altitude range of a certain high-altitude cabin is 2km to 25km.

[0092] 2) Calculate the simulated pressure inside the chamber based on the height of the test point, and determine whether to use single-stage or two-stage evacuation. Use single-stage evacuation if the simulated pressure is above 12 kPa; use two-stage evacuation if the simulated pressure is below 12 kPa. The calculation formula is as follows.

[0093] H≤11km:

[0094] P=101325×(1-0.0225577×H)5.25588(Pa);

[0095] 11<H≤20km:

[0096] P=22632.04×exp[-0.1576885×(H-11)](Pa);

[0097] 20<H≤32km:

[0098] P=5474.879×[1+4.64574×10-3×(H-20)]34.16322(Pa).

[0099] 3) Determine the number of extraction units based on the engine exhaust volume flow rate.

[0100] 4) Based on the engine airflow, considering 5%–10% of the two-stream flow, 15% of the pressure loss from the exhaust cooler, and approximately 10% adjustment margin, determine the exhaust volumetric flow rate.

[0101] Q=1.1×60×(Wa+Wa×10%) / [P×(1-15%) / (RT)];

[0102] Where: Q—exhaust volume flow rate, m3 / min; Wa—engine air flow rate, kg / s; P—simulated chamber pressure, Pa; R—gas constant, J / (kgK); T—gas temperature after exhaust cooler, 313.15K.

[0103] The extraction volume flow rate of a single AV100 unit is calculated at 9000 m³ / min, and the extraction volume flow rate of a single AV71 unit is calculated at 3750 m³ / min. After determining the number of units, the total extraction volume flow rate must be greater than the engine exhaust volume flow rate.

[0104] The extraction volume flow rate and extraction method of a certain high-altitude cabin at various altitudes are shown in the figure. Figure 8 .

[0105] The specific steps for analyzing the mass flow rate of the extracted air are as follows:

[0106] Based on the capacity of a certain high-altitude cabin extraction unit and considering a 15% pressure loss from the exhaust cooler, the extraction mass flow rate at various altitudes is calculated as follows. An extraction mass flow rate graph for each altitude of the high-altitude cabin is also plotted. Figure 9 (The allowable mass flow rate for air extraction is the same for heights below 8km, which is 263kg / s). When H≤15km (12kPa), Wa=[P×(1-15%) / (RT)]×(47250 / 60); when 15km<H≤25km, Wa=[P×(1-15%) / (RT)]×(36000 / 60).

[0107] Where: Wa—gas extraction mass flow rate, kg / s; P—simulated chamber pressure, Pa; R—gas constant, J / (kgK); T—gas temperature after exhaust cooler, 313.15K.

[0108] When analyzing the extraction parameters at the engine test points, the total flow rate of the two streams should be added to the engine exhaust flow rate, and a 10% adjustment margin should be considered. This should be less than the extraction mass flow rate at that height (in reality, the flow rates of the two streams and the pressure loss of the exhaust cooler will vary slightly at each test point).

[0109] When the first carrier air supply capacity of the high-altitude cabin matches the first product air supply capacity of the engine, the second carrier air supply capacity of the high-altitude cabin matches the second product air supply capacity of the engine, and the total carrier air extraction capacity of the high-altitude cabin matches the total product air extraction capacity of the engine, it proves that the engine can be placed in the high-altitude cabin for testing, thus realizing the dynamic operation matching between the aero-engine and the high-altitude test air source unit.

[0110] This invention addresses the practical testing needs of high-altitude test benches for aero-engines by researching dynamic operation matching methods for these benches. It aims to improve the testing and management levels of the gas supply system and equipment, explore automated control of the process flow and dynamic management of the equipment's technical status, enhance the utilization rate of testing equipment, and improve testing efficiency and quality. This will provide technical support for the future engineering application of dynamic management of high-altitude test benches for aero-engines.

[0111] Therefore, the dynamic operation matching method for the air source unit of the high-altitude test bench for aero-engines proposed in this invention can be widely applied to the dynamic operation matching of air source units for aero-engines and gas turbines, improving the testing and equipment management level of the air supply system, exploring automated control of the process flow and dynamic control of the equipment technical status of the air source unit for the high-altitude test bench for aero-engines, improving the utilization rate of test equipment, improving the test efficiency and quality of the test equipment, and providing technical support for the engineering application of dynamic control of the air source unit for the high-altitude test bench for aero-engines in the future.

[0112] Exemplary device

[0113] Figure 10 This is a schematic diagram of the structure of a dynamic operation matching device based on an aero-engine high-altitude test air source unit, provided in an exemplary embodiment of the present invention. (See diagram below.) Figure 10 As shown, the device 1000 includes:

[0114] The determination module 1010 is used to determine the first carrier gas supply capacity, the second carrier gas supply capacity and the total carrier gas extraction capacity of the test carrier, wherein the first carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply pressures, the second carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply temperatures, and the total carrier gas extraction capacity is the gas flow rate that the test carrier can provide under different gas extraction pressures.

[0115] The first matching module 1020 is used to determine whether the first carrier gas supply capacity of the test carrier matches the first product gas supply capacity of the test sample, wherein the first product gas supply capacity is the gas flow rate that the test sample can provide under different gas supply pressures.

[0116] The second matching module 1030 is used to determine whether the second carrier gas supply capacity of the test carrier matches the second product gas supply capacity of the test sample, wherein the second product gas supply capacity is the gas flow rate that the test sample can provide at different gas supply temperatures.

[0117] The third matching module 1040 is used to determine whether the total pumping capacity of the test carrier matches the total pumping capacity of the test product, wherein the total pumping capacity of the product is the air supply flow rate that the test product can provide under different pumping pressures.

[0118] Optionally, the second carrier gas supply capacity includes the carrier positive temperature gas supply capacity and the carrier negative temperature gas supply capacity, wherein the carrier positive temperature gas supply capacity is the gas flow rate that the test carrier can provide at different positive temperatures, and the carrier negative temperature gas supply capacity is the gas flow rate that the test carrier can provide at different negative temperatures.

[0119] Optionally, the total pumping capacity of the carrier includes the pumping capacity of the first carrier and the pumping capacity of the second carrier, wherein the pumping capacity of the first carrier is the volumetric flow rate that the test carrier can provide under different pumping pressures, and the pumping capacity of the second carrier is the mass flow rate that the test carrier can provide under different pumping pressures.

[0120] Optionally, the second matching module 1030 is specifically used to: determine whether the positive temperature gas supply capacity of the test sample is within the range of the positive temperature gas supply capacity of the test carrier, wherein the positive temperature gas supply capacity is the gas flow rate that the test sample can provide at different positive temperatures; and determine whether the negative temperature gas supply capacity of the test sample is within the range of the negative temperature gas supply capacity of the test carrier, wherein the negative temperature gas supply capacity is the gas flow rate that the test sample can provide at different negative temperatures.

[0121] Optionally, the third matching module 1040 is specifically used to: determine whether the first product pumping capacity of the test sample is within the range of the first carrier pumping capacity of the test carrier, wherein the first product pumping capacity is the pumping volume flow rate that the test sample can provide under different pumping pressures; and determine whether the second product pumping capacity of the test sample is within the range of the second carrier pumping capacity of the test carrier, wherein the second product pumping capacity is the pumping mass flow rate that the test sample can provide under different pumping pressures.

[0122] The dynamic operation matching device based on the air source unit of the high-altitude test bench of the aero-engine in this embodiment of the invention corresponds to the dynamic operation matching method based on the air source unit of the high-altitude test bench of the aero-engine in another embodiment of the invention, and will not be described again here.

[0123] Exemplary electronic devices

[0124] Figure 10 This is the structure of an electronic device provided in an exemplary embodiment of the present invention. For example... Figure 11 As shown, the electronic device 110 includes one or more processors 111 and memory 112.

[0125] The processor 111 may be a central processing unit (CPU) or other form of processing unit with data processing capabilities and / or instruction execution capabilities, and may control other components in the electronic device to perform desired functions.

[0126] The memory 112 may include one or more computer program products, which may include various forms of computer-readable storage media, such as volatile memory and / or non-volatile memory. The volatile memory may include, for example, random access memory (RAM) and / or cache memory. The non-volatile memory may include, for example, read-only memory (ROM), hard disk, flash memory, etc. One or more computer program instructions may be stored on the computer-readable storage medium, and the processor 111 may execute the program instructions to implement the methods of the software programs of the various embodiments of the present invention described above, and / or other desired functions. In one example, the electronic device may further include an input device 113 and an output device 114, which are interconnected via a bus system and / or other forms of connection mechanisms (not shown).

[0127] In addition, the input device 113 may also include, for example, a keyboard, a mouse, etc.

[0128] The output device 114 can output various information to the outside. The output device 114 may include, for example, a display, a speaker, a printer, and a communication network and its connected remote output devices, etc.

[0129] Of course, for the sake of simplicity, Figure 11 Only some of the components of the electronic device relevant to the present invention are shown, omitting components such as buses, input / output interfaces, etc. In addition, the electronic device may include any other suitable components depending on the specific application.

[0130] Exemplary computer program products and computer-readable storage media

[0131] In addition to the methods and apparatus described above, embodiments of the present invention may also be computer program products, which include computer program instructions that, when executed by a processor, cause the processor to perform the steps of the methods according to various embodiments of the present invention described in the "Exemplary Methods" section above.

[0132] The computer program product can be written in any combination of one or more programming languages ​​to perform the operations of the embodiments of the present invention. The programming languages ​​include object-oriented programming languages ​​such as Java and C++, as well as conventional procedural programming languages ​​such as C or similar languages. The program code can be executed entirely on the user's computing device, partially on the user's computing device, as a standalone software package, partially on the user's computing device and partially on a remote computing device, or entirely on a remote computing device or server.

[0133] Furthermore, embodiments of the present invention may also be computer-readable storage media storing computer program instructions thereon, which, when executed by a processor, cause the processor to perform the steps of the methods according to various embodiments of the present invention described in the "Exemplary Methods" section above.

[0134] The computer-readable storage medium may be any combination of one or more readable media. A readable medium may be a readable signal medium or a readable storage medium. A readable storage medium may be, for example, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or any combination thereof. More specific examples (a non-exhaustive list) of readable storage media include: an electrical connection having one or more wires, a portable disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof.

[0135] The basic principles of the present invention have been described above with reference to specific embodiments. However, it should be noted that the advantages, benefits, and effects mentioned in the present invention are merely examples and not limitations, and should not be considered as essential features of each embodiment of the present invention. Furthermore, the specific details disclosed above are for illustrative and facilitative purposes only, and are not limitations. These details do not limit the present invention to the necessity of employing the aforementioned specific details.

[0136] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For system embodiments, since they largely correspond to method embodiments, the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments.

[0137] The block diagrams of devices, systems, devices, and systems involved in this invention are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, systems, devices, and systems can be connected, arranged, and configured in any manner. Words such as “comprising,” “including,” “having,” etc., are open-ended terms meaning “including but not limited to,” and are used interchangeably with them. The terms “or” and “and” as used herein refer to the terms “and / or,” and are used interchangeably with them unless the context clearly indicates otherwise. The term “such as” as used herein refers to the phrase “such as but not limited to,” and is used interchangeably with it.

[0138] The methods and systems of the present invention may be implemented in many ways. For example, they may be implemented by software, hardware, firmware, or any combination of software, hardware, and firmware. The above-described order of steps for the methods is for illustrative purposes only, and the steps of the methods of the present invention are not limited to the order specifically described above unless otherwise specifically stated. Furthermore, in some embodiments, the present invention may also be implemented as a program recorded on a recording medium, the program comprising machine-readable instructions for implementing the methods according to the present invention. Thus, the present invention also covers recording media storing programs for performing the methods according to the present invention.

[0139] It should also be noted that in the systems, apparatus, and methods of the present invention, the components or steps can be disassembled and / or recombined. These disassemblies and / or recombinations should be considered equivalents of the present invention. The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the invention. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of the invention. Therefore, the invention is not intended to be limited to the aspects shown herein, but rather to be carried out within the widest scope consistent with the principles and novel features disclosed herein.

[0140] The above description has been given for purposes of illustration and description. Furthermore, this description is not intended to limit the embodiments of the invention to the forms disclosed herein. Although numerous exemplary aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations therein.

Claims

1. A dynamic operation matching method based on an aero-engine high-altitude test air source unit, characterized in that, include: The high-altitude test air source unit of the aircraft engine provides air supply, air extraction and temperature control conditions for the test vehicle, and the test vehicle provides the test environment for the test object. Determine the first carrier gas supply capacity, the second carrier gas supply capacity, and the total carrier gas extraction capacity of the test carrier, wherein the first carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply pressures, the second carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply temperatures, and the total carrier gas extraction capacity is the gas flow rate that the test carrier can provide under different gas extraction pressures. Determine whether the first carrier gas supply capacity of the test carrier matches the first product gas supply capacity of the test sample, wherein the first product gas supply capacity is the gas flow rate that the test sample can provide under different gas supply pressures; Determine whether the gas supply capacity of the second carrier of the test carrier matches the gas supply capacity of the second product of the test sample, wherein the gas supply capacity of the second product is the gas flow rate that the test sample can provide at different gas supply temperatures; Determine whether the total pumping capacity of the test carrier matches the total pumping capacity of the test product, wherein the total pumping capacity of the product is the air supply flow rate that the test product can provide under different pumping pressures.

2. The method according to claim 1, characterized in that, The second carrier gas supply capacity includes the carrier positive temperature gas supply capacity and the carrier negative temperature gas supply capacity, wherein the carrier positive temperature gas supply capacity is the gas flow rate that the test carrier can provide at different positive temperatures, and the carrier negative temperature gas supply capacity is the gas flow rate that the test carrier can provide at different negative temperatures.

3. The method according to claim 1, characterized in that, The total pumping capacity of the carrier includes the pumping capacity of the first carrier and the pumping capacity of the second carrier, wherein the pumping capacity of the first carrier is the volumetric flow rate that the test carrier can provide under different pumping pressures, and the pumping capacity of the second carrier is the mass flow rate that the test carrier can provide under different pumping pressures.

4. The method according to claim 2, characterized in that, The step of determining whether the gas supply capacity of the second carrier of the test carrier matches the gas supply capacity of the second product of the test sample includes: Determine whether the positive temperature gas supply capacity of the test sample is within the range of the positive temperature gas supply capacity of the test carrier, wherein the positive temperature gas supply capacity is the gas flow rate that the test sample can provide at different positive temperatures; Determine whether the negative temperature gas supply capacity of the test sample is within the range of the negative temperature gas supply capacity of the test carrier, wherein the negative temperature gas supply capacity is the gas flow rate that the test sample can provide at different negative temperatures.

5. The method according to claim 3, characterized in that, The determination of whether the total pumping capacity of the test carrier matches the total pumping capacity of the test sample includes: Determine whether the first product pumping capacity of the test sample is within the range of the first carrier pumping capacity of the test carrier, wherein the first product pumping capacity is the pumping volume flow rate that the test sample can provide under different pumping pressures. Determine whether the second product pumping capacity of the test sample is within the range of the second carrier pumping capacity of the test carrier, wherein the second product pumping capacity is the pumping mass flow rate that the test sample can provide under different pumping pressures.

6. A dynamic operation matching device based on an aero-engine high-altitude test air source unit, characterized in that, include: The high-altitude test air source unit of the aircraft engine provides air supply, air extraction and temperature control conditions for the test vehicle, and the test vehicle provides the test environment for the test object. The determination module is used to determine the first carrier gas supply capacity, the second carrier gas supply capacity, and the total carrier gas extraction capacity of the test carrier, wherein the first carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply pressures, the second carrier gas supply capacity is the gas flow rate that the test carrier can provide under different gas supply temperatures, and the total carrier gas extraction capacity is the gas flow rate that the test carrier can provide under different gas extraction pressures. The first matching module is used to determine whether the first carrier gas supply capacity of the test carrier matches the first product gas supply capacity of the test sample, wherein the first product gas supply capacity is the gas flow rate that the test sample can provide under different gas supply pressures. The second matching module is used to determine whether the second carrier gas supply capacity of the test carrier matches the second product gas supply capacity of the test sample, wherein the second product gas supply capacity is the gas flow rate that the test sample can provide at different gas supply temperatures. The third matching module is used to determine whether the total pumping capacity of the test carrier matches the total pumping capacity of the test product, wherein the total pumping capacity of the product is the air supply flow rate that the test product can provide under different pumping pressures.

7. The apparatus according to claim 6, characterized in that, The second carrier gas supply capacity includes the carrier positive temperature gas supply capacity and the carrier negative temperature gas supply capacity, wherein the carrier positive temperature gas supply capacity is the gas flow rate that the test carrier can provide at different positive temperatures, and the carrier negative temperature gas supply capacity is the gas flow rate that the test carrier can provide at different negative temperatures.

8. The apparatus according to claim 6, characterized in that, The total pumping capacity of the carrier includes the pumping capacity of the first carrier and the pumping capacity of the second carrier, wherein the pumping capacity of the first carrier is the volumetric flow rate that the test carrier can provide under different pumping pressures, and the pumping capacity of the second carrier is the mass flow rate that the test carrier can provide under different pumping pressures.

9. A computer-readable storage medium, characterized in that, The storage medium stores a computer program for performing the method described in any one of claims 1-5.

10. An electronic device, characterized in that, The electronic device includes: processor; Memory used to store the processor's executable instructions; The processor is configured to read the executable instructions from the memory and execute the instructions to implement the method described in any one of claims 1-5.

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