A method and apparatus for testing the performance of a fuel cell air compressor in a simulated high-altitude environment.

Abstract

This invention discloses a performance testing device for a fuel cell air compressor in a simulated high-altitude environment. The device includes an air filter, a first electronic valve, a first mass flow sensor, a first pressure sensor, an air compressor, a second pressure sensor, a cooling module, a second mass flow sensor, a third pressure sensor, a second electronic valve, a host computer, a first temperature sensor, a second temperature sensor, a third temperature sensor, and a muffler. The host computer adjusts the air compressor's pressure between 80 kPa and 101 kPa by setting the operating speed of the air compressor and adjusting the opening angles of the first and second electronic valves, thus simulating the environmental pressure below 2 km altitude on a plateau. The device measures the pressurization pressure parameters of the air compressor at different pressure and flow operating points, completing the performance test of the air compressor under conditions below standard atmospheric pressure. This invention utilizes both experimental and simulation methods to test air compressor performance, both of which can simulate high-altitude environments and test the performance of fuel cell air compressors.

Description

Technical Field

[0001] This invention belongs to the field of fuel cell technology and relates to a method and apparatus for testing the performance of a fuel cell air compressor in a simulated high-altitude environment. Background Technology

[0002] The fuel cell air compressor is a key component for air delivery in fuel cell products. It pressurizes air through the rotation of an impeller inside the compressor to meet the fuel cell's requirements for intake pressure and flow rate. The pressure ratio and flow rate of the air compressor during operation are important performance indicators, used to evaluate whether the compressor's performance meets the fuel cell's requirements. When the fuel cell system operates in a high-altitude environment, the lower intake pressure compared to atmospheric pressure at sea level causes changes in the pressure ratio and flow rate of the fuel cell air compressor. This change may lead to performance degradation of the fuel cell system at high altitudes. Therefore, engineers need to understand the performance of the fuel cell air compressor under high-altitude conditions during the product development phase and implement a series of protective measures. However, since it may not be possible to operate the fuel cell product in a real high-altitude environment during the initial development stage, it is necessary to simulate high-altitude environmental pressures in the laboratory to test the air compressor's performance and obtain pressure ratio and flow rate data under low intake pressure. Summary of the Invention

[0003] To solve the above problems, the technical solution adopted by the present invention is: a performance testing device for a fuel cell air compressor simulating a high-altitude environment, comprising:

[0004] An air filter used to filter compressed air;

[0005] A first electronic valve that controls the amount of air filtered by the air filter;

[0006] A first mass flow sensor for detecting the gas flow rate of the air filtered by the air filter;

[0007] A first pressure sensor detects the real-time intake pressure of the air filtered by the air filter before it enters the fuel cell air compressor.

[0008] An air compressor that compresses filtered air;

[0009] A second pressure sensor for detecting the intake pressure of the air compressed by the air compressor;

[0010] A cooling module for cooling the air compressed by the air compressor;

[0011] A second mass flow sensor for detecting the gas flow rate of the air cooled by the cooling module;

[0012] A third pressure sensor for detecting the pressure of the air cooled by the cooling module;

[0013] A second electronic valve that controls the amount of air cooled by the cooling module;

[0014] A host computer receives the filtered gas flow rate from the first mass flow sensor, the real-time intake pressure of the air compressor to be fed into the fuel cell from the first pressure sensor, the compressed pressure from the second pressure sensor, the cooled air flow rate from the second mass flow sensor, and the cooled air pressure from the third pressure sensor. The host computer adjusts the air compressor pressure between 80 kPa and 101 kPa by setting the operating speed of the air compressor and adjusting the opening angles of the first and second electronic valves to simulate the environmental pressure below 2 km altitude on a plateau. The host computer measures the boost pressure parameters of the air compressor at different pressure and flow operating points to complete the air compressor performance test under conditions below standard atmospheric pressure.

[0015] Furthermore, it also includes a first temperature sensor for acquiring the temperature of the gas filtered by the air filter.

[0016] A second temperature sensor that collects the temperature of the gas compressed by the air compressor;

[0017] A third temperature sensor that collects the temperature of the gas after it has been cooled and contracted by the cooling module;

[0018] The host computer receives the temperature of the filtered gas from the first temperature sensor, the temperature of the compressed gas from the second temperature sensor, and the temperature of the gas cooled by the cooling module, thereby monitoring the gas temperature changes during the simulation process and controlling the temperature.

[0019] Furthermore: the cooling module includes a water tank, a water pump, a heat exchanger, and a fan;

[0020] The pressurized gas is cooled by a heat exchanger;

[0021] The gas flowing out of the air compressor enters the heat exchanger and the circulating water in the water tank for heat exchange and cooling. The circulating water circuit has a water pump to provide power and a fan to control the temperature.

[0022] Furthermore, it also includes a silencer to reduce the noise of the gas discharged after the second electronic valve is controlled.

[0023] According to any one of the test methods for a performance testing device for a fuel cell air compressor in a simulated high-altitude environment, the performance testing device for a fuel cell air compressor in a simulated high-altitude environment finds the corresponding sub-model in the AMEsim simulation software, completes the connection and parameter input of each sub-model in the software according to the arrangement of the experimental device, and obtains the performance data of the air compressor through simulation calculation.

[0024] Furthermore, this includes simulation modeling of a fuel cell air compressor performance testing device for a simulated high-altitude environment, and determining parameters reflecting air compressor performance such as pressure ratio (Pr) and flow rate (m). c The calculation formula is as follows:

[0025] Pr=(dm c w c (1)

[0026]

[0027]

[0028] Wherein: dm c To correct the flow rate g / s, w c To correct the engine speed (rpm), P up For the actual inlet pressure ba, P st For standard pressure bars, T up For the actual inlet temperature K, T st The standard temperature is K; the performance curve of the air compressor under standard conditions can be provided by the supplier, and the MAP data of flow rate and pressure can be directly input into the air compressor sub-model, so that the air compressor sub-model can correct the air compressor boost ratio and flow rate values ​​under low air pressure conditions;

[0029] The opening angle of the first electronic valve affects the airflow rate through the pipeline while adjusting the intake pressure. The formula for calculating the flow rate in the air compressor sub-model is as follows:

[0030]

[0031] Where: A is the aperture area in m 2 C q It is the flow coefficient, C m It is the mass flow rate coefficient (kg·K / J). 1 / 2 P up It is the pressure before the valve, T up It is the temperature before the valve, C. q It is a variable related to the valve opening value, the mass flow coefficient C. m The calculation method is as follows:

[0032]

[0033] Where: γ is the specific heat ratio, defined as the ratio of the gas's isobaric specific heat capacity to its isochoric specific heat capacity; R is the universal gas constant, with a value of 8.314 [J / K / mol].

[0034] Before running the air compressor performance simulation model, you need to input the three-dimensional MAP data of the air compressor speed, flow rate and pressure ratio under standard conditions, and give the opening value of the flow regulating valve and the air compressor speed. Set the air source pressure and temperature at the front end of the model. When the air source pressure is set to below 101kPa, the simulation calculation can be performed to obtain the air compressor performance under the simulated plateau intake pressure conditions. The lower the air source pressure, the higher the corresponding plateau altitude.

[0035] The present invention provides a method and apparatus for testing the performance of a fuel cell air compressor in a simulated high-altitude environment, which has the following advantages:

[0036] A testing device was constructed under normal pressure. This device can regulate and control the intake pressure of an air compressor, simulating the intake pressure of an air compressor in a high-altitude environment and completing performance tests. Each component of this testing device can also find corresponding sub-models in the AMEsim simulation software. The sub-models are connected and parameters are input in the software according to the experimental setup, and simulation calculations can also obtain the air compressor's performance data. This invention uses both experimental and simulation results for comparative verification, which verifies the validity of the experimental results.

[0037] This invention simulates the high-altitude environment through both experiments and simulations, and can achieve the purpose of testing the performance of fuel cell air compressors. The results of both experiments and simulations can effectively provide a feasibility assessment for the operation of fuel cells in real high-altitude environments.

[0038] This invention creates an air compressor experimental device that can adjust the intake pressure within the range of 80kPa-101kPa through electronic valves, thereby realizing the performance testing of a fuel cell air compressor under simulated high-altitude environmental pressure.

[0039] This invention establishes a simulation model of an air compressor testing device based on AMEsim software. The model parameters of valves and air compressor in the testing device are used as inputs. The performance of the air compressor in the range of 80kPa-101kPa is obtained through software simulation, realizing the performance simulation of fuel cell air compressor under the pressure of high-altitude environment.

[0040] This invention utilizes a simulated high-altitude environment by constructing an air compressor testing device to conduct experiments on fuel cell air compressors. This device is easy to control and can adjust the inlet pressure within the range of 80 kPa to 101 kPa. The invention employs simulation technology to test the performance of the air compressor under high-altitude conditions. The simulation results also provide the pressure ratio and flow rate parameters of the fuel cell air compressor within the 80 kPa-101 kPa inlet pressure range. The results obtained from both experimental and simulation methods show good consistency and effectively reflect the expected performance of the fuel cell air compressor under high-altitude conditions.

[0041] This invention relates to a method for testing the performance of a fuel cell air compressor in a simulated high-altitude environment. The method comprises two parts: experiment and simulation. The experimental setup uses an electronic valve positioned at the inlet of the fuel cell air compressor to regulate the inlet pressure, thereby simulating the inlet pressure under high-altitude conditions. This testing setup features a simple architecture and precise pressure control. The electronic valve operates at millisecond speeds, enabling rapid adjustment and stabilization of the inlet pressure value even when the compressor speed changes.

[0042] This invention includes the construction of a simulation model of the experimental device based on AMEsim software. The simulation results can be used to independently calculate and obtain the performance of the fuel cell air compressor under simulated high-altitude environment. On the other hand, it can also evaluate the validity of the test results obtained by the above experimental methods, and can promptly detect anomalies in the experimental results to ensure data accuracy.

[0043] The present invention has the following advantages:

[0044] 1. This invention tests the performance of air compressors using both experimental and simulation methods, both of which can simulate high-altitude environments and test the performance of fuel cell air compressors.

[0045] 2. This invention relates to the construction of an air compressor experimental device and the simulation of intake pressure corresponding to a high-altitude environment by controlling electronic valves at the front end of the air compressor.

[0046] 3. The experimental setup includes components that generate pressure drop, such as air filters, heat exchangers, and silencers, and can test pressure changes in the air pipeline of fuel cell products.

[0047] 4. This method is based on AMEsim software to build the entire test pipeline of the air compressor. By modifying the pressure value of the air source in the model, the intake pressure corresponding to the high-altitude environment can be simulated.

[0048] 5. The air compressor sub-model in the simulation model only requires performance data under standard conditions as input, and the input content is easy to obtain.

[0049] 6. The simulation model built based on the components of the experimental setup showed good consistency between the simulation results and the experimental results. The simulation results can also serve as a tool to verify the validity of the experimental results; combining the results of both can improve the accuracy of the tests. Attached Figure Description

[0050] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0051] Figure 1 This is a schematic diagram of the experimental apparatus for testing air compressors in a simulated high-altitude environment according to the present invention.

[0052] Figure 2 This is a schematic diagram of a simulation model for testing air compressors in a high-altitude environment, as per the present invention.

[0053] Figure 3 A comparison chart of simulation and experimental results of flow rate values ​​at different operating points of the air compressor under an intake pressure of 90 kPa;

[0054] Figure 4 Comparison of simulation and experimental results of pressure values ​​after pressurization at different operating points under an air compressor intake pressure of 90 kPa;

[0055] Figure 5 A comparison chart of simulation and experimental results of flow rate values ​​at different operating points of the air compressor under an intake pressure of 80 kPa;

[0056] Figure 6 The figure shows a comparison of simulation and experimental results of the pressure values ​​after pressurization at different operating points under an air compressor intake pressure of 80 kPa.

[0057] Figure reference numerals: 1. Air filter; 2. First electronic valve; 3. First mass flow sensor; 4. First pressure sensor; 5. First temperature sensor; 6. Air compressor; 7. Host computer; 8. Second pressure sensor; 9. Second temperature sensor; 10. Heat exchanger; 11. Water pump; 12. Water tank; 13. Fan; 14. Second mass flow meter; 15. Third pressure sensor; 16. Third temperature sensor; 17. Second electronic valve; 18. Silencer; 101. Air source sub-model; 102. Air filter sub-model; 103. First mass flow meter sub-model; 104. First pipeline sub-model. 105. Second Piping Sub-model; 106. Third Piping Sub-model; 107. Air Compressor Sub-model; 108. Fourth Piping Sub-model; 109. Heat Exchanger Sub-model; 1010. Fifth Piping Sub-model; 1013. Sixth Piping Sub-model; 1014. Seventh Piping Sub-model; 1015. Eighth Piping Sub-model; 1016. Second Mass Flow Meter Sub-model; 1017. Ninth Piping Sub-model; 1019. Eighth Piping Sub-model; 1011. Pressure Sensor Sub-model; 1012. Temperature Sensor Sub-model; 1018. Electronic Valve Sub-model; 1020. Atmospheric Environment Sub-model. Detailed Implementation

[0058] It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and embodiments.

[0059] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0060] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of exemplary embodiments according to the invention. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0061] 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. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0062] In the description of this invention, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is generally based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this invention and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this invention. The directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0063] For ease of description, spatial relative terms such as "above," "over," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation besides the orientation of the device as described in the figures. For example, if the device in the figures is inverted, a device described as "above" or "above" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways, rotated 90 degrees, or in other orientations, and the spatial relative descriptions used herein will be interpreted accordingly.

[0064] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0065] Figure 1This is a schematic diagram of the experimental apparatus for testing air compressors in a simulated high-altitude environment according to the present invention.

[0066] This invention constructs a performance testing device for a fuel cell air compressor in a simulated high-altitude environment, comprising an air filter 1, a first electronic valve 2, a first mass flow sensor 3, a first pressure sensor 4, an air compressor 6, a second pressure sensor 8, a cooling module, a second mass flow sensor 14, a third pressure sensor 15, a second electronic valve 17, a host computer 7, a first temperature sensor 5, a second temperature sensor 9, a third temperature sensor 16, and a muffler 18.

[0067] The air filter 1 is used to filter the compressed air;

[0068] The first electronic valve 2 controls the amount of air filtered by the air filter 1;

[0069] The first mass flow sensor 3 detects the gas flow rate of the air filtered by the air filter 1;

[0070] The first pressure sensor 4 detects the real-time intake pressure of the air filtered by the air filter 1 before it enters the fuel cell air compressor 6.

[0071] The air compressor 6 compresses the filtered air;

[0072] The second pressure sensor 8 detects the intake pressure of the air compressed by the air compressor 6;

[0073] The cooling module cools the air compressed by the air compressor 6;

[0074] The second mass flow sensor 14 detects the gas flow rate of the air cooled by the cooling module;

[0075] The third pressure sensor 15 detects the pressure of the air cooled by the cooling module;

[0076] The second electronic valve 17 controls the amount of air cooled by the cooling module;

[0077] The host computer 7 receives the filtered gas flow rate transmitted by the first mass flow sensor 3, the real-time intake pressure of the air compressor 6 to be fed into the fuel cell transmitted by the first pressure sensor 4, the compressed pressure transmitted by the second pressure sensor 8, the cooled air flow rate transmitted by the second mass flow sensor 14, and the cooled air pressure transmitted by the third pressure sensor 15. The host computer 7 adjusts the pressure of the air compressor 6 between 80kPa and 101kPa by setting the operating speed of the air compressor 6 and adjusting the opening angle of the first electronic valve 2 and the second electronic valve 17, thereby simulating the environmental pressure below 2km altitude on a plateau. The host computer 7 measures the boost pressure parameters of the air compressor 6 at different pressure and flow operating points, thus completing the performance test of the air compressor 6 under conditions below standard atmospheric pressure.

[0078] The host computer 7 can communicate with the air compressor 6 via a USB-CAN card; it can send operation commands such as start, speed setting, and stop to the air compressor 6, and it can also collect the speed and power values ​​fed back by the air compressor 6.

[0079] This simulated high-altitude environment fuel cell air compressor performance testing device can operate at atmospheric pressure. While adjusting the intake pressure, it also simultaneously adjusts the gas flow rate through the air compressor 6. The device can measure key parameters such as boost pressure and power consumption of the air compressor 6 at different pressure and flow operating points, and complete the performance test of the air compressor 6 under conditions below standard atmospheric pressure.

[0080] Outside air first flows into the air filter 1 under the suction generated by the air compressor 6 during operation, filtering out impurities that may damage the air compressor 6 and producing a small pressure drop. Then it flows through the first electronic valve 2, and the inlet pressure of the air compressor 6 is adjusted by adjusting the opening of the first electronic valve 2.

[0081] The air compressor 6 can heat and pressurize the gas. The pressurized gas needs to be cooled because of its high temperature in order to meet the requirements of the fuel cell. The experimental device also includes this function.

[0082] The cooling module includes a water tank 12, a water pump 11, a heat exchanger 10, and a fan 13. The water tank 12 stores a certain amount of water, which flows in the pipeline under the action of the water pump 11. When the water flows through the heat exchanger 10, it exchanges heat with the pressurized high-temperature gas on one side of the heat exchanger 10 to cool the gas. After the water temperature rises after the heat exchange is completed, it is cooled by the fan 13 and then flows back to the water tank.

[0083] The cooling module cools the pressurized gas through heat exchanger 10. On the one hand, it can reduce the temperature of the gas and thus reduce the heat load of the entire test bench. On the other hand, it can also be consistent with the air circuit layout of the fuel cell product, and better simulate the gas pressure change at the back end of the fuel cell air compressor 6 pipeline in a high-altitude environment.

[0084] The opening degree of the second electronic valve of the host computer 7 and the rotational speed of the air compressor 6 together affect the flow rate of the air compressor 6.

[0085] The first pressure sensor 4 at the inlet of the air compressor 6 can provide feedback on the real-time intake pressure value of the actual fuel cell air compressor 6. When the intake pressure value differs significantly from the target pressure corresponding to the simulated high-altitude environment, the deviation can be eliminated by readjusting the opening value of the electronic valve.

[0086] Gas flows out of air compressor 6 and enters heat exchanger 10 and circulating water in water tank 12 for heat exchange and cooling. In the circulating water circuit, water pump 11 provides power and fan 13 controls the temperature. The gas temperature after heat exchange is read by third temperature sensor 16. Gas flowing through heat exchanger 10 will also cause a pressure drop. The pressure value after the drop can be read by second pressure sensor 8.

[0087] The gas that has completed heat exchange and cooling flows into the second electronic valve 17. The opening degree of this valve can regulate the gas flow rate, which can be read by the second mass flow meter 14 located at the front end of the second electronic valve 17. Because high-speed gas flow is accompanied by significant noise, a silencer 18 is installed at the end of the experimental device to reduce the noise during emission.

[0088] The host computer 7 receives the temperature of the filtered gas transmitted by the first temperature sensor 5, the temperature of the compressed gas transmitted by the second temperature sensor 9, and the temperature of the gas cooled by the cooling module, thereby controlling the temperature during the simulated high-altitude environment test.

[0089] This experimental setup can test the flow and pressure characteristics of an air compressor under conditions below standard atmospheric pressure; it can also test whether the air compressor performance matches the product's pressure and flow target values ​​under low inlet pressure conditions.

[0090] This invention also includes the construction of a simulation model of the overall pipeline for air compressor experiments. The simulation model is generated based on AMEsim software. The main components of the experimental device, such as electronic valves, heat exchanger 10, and air compressor 6, can all be parameterized in AMEsim software. The parameters Pr (pressure ratio) and flow rate m that reflect the performance of air compressor 6 in the model are... c The calculation formula is as follows:

[0091] Pr=(dm cw c (1)

[0092]

[0093]

[0094] Wherein: dm c To correct the flow rate g / s, w c To correct the engine speed (rpm), P up P represents the actual inlet pressure in bars. st For standard pressure bars, T up For the actual inlet temperature K, T st The standard temperature is K; the performance curve of the air compressor under standard conditions can be provided by the supplier, and the MAP data of flow rate and pressure can be directly input into the air compressor sub-model. The air compressor sub-model can then correct the air compressor boost ratio and flow rate results under low air pressure conditions; the air compressor sub-model included in the AMEsim software can calculate the air compressor performance at any operating point based on the air compressor MAP data input by the user and correct the performance results at different intake pressures.

[0095] The opening angle of an electronic valve can affect the flow rate of air through a pipeline. The formula for calculating the flow rate in the air compressor sub-model is as follows:

[0096]

[0097] Where: A is the aperture area in m 2 C q It is the flow coefficient, C m It is the mass flow coefficient (kg·K / J). 1 / 2 P up It is the pressure before the valve, T up It is the temperature before the valve, C. q It is a variable related to the valve opening value, and the two are not purely linearly related. The curve of the flow coefficient changing with the valve opening can usually be obtained by conducting experiments on the valve. The mass flow coefficient C... m The calculation method is as follows:

[0098]

[0099] Where: γ is the specific heat ratio, defined as the ratio of the gas's isobaric specific heat capacity to its isochoric specific heat capacity; R is the universal gas constant, with a value of 8.314 [J / K / mol].

[0100] Before running the performance simulation model of air compressor 6, three-dimensional MAP data of air compressor 6's speed, flow rate, and boost ratio under normal temperature and pressure conditions must be input, along with the opening value of the flow control valve and the air compressor speed. The model front end allows setting the air source pressure and temperature. When the air source pressure is set below 101 kPa, simulation calculations can be performed to obtain the performance results of air compressor 6 under different operating points under simulated high-altitude intake pressure conditions. The lower the air source pressure, the higher the corresponding altitude. The simulation calculation results and experimental data of this model within the intake pressure range of 80 kPa-101 kPa show good consistency, effectively testing the performance of air compressor 6 in simulated high-altitude environments.

[0101] according to Figure 1 The constructed device can simulate the low intake pressure of a high-altitude environment by adjusting the opening of the electronic valve at the air compressor inlet. It can also collect key parameters such as air compressor flow rate, temperature, and pressure within the intake pressure range of 80kPa-101kPa, and obtain pressure and flow curve data characterizing the performance of the air compressor.

[0102] The method for simulating high-altitude environment testing of fuel cell air compressor performance in this invention also includes a simulation step. This simulation method is based on AMEsim software to build a model, and a schematic diagram of the model is shown below. Figure 2 As shown.

[0103] The model building process should fully consider the ability to simulate Figure 1 Only by understanding the pressure changes of each component in the experimental setup can the validity of the comparison between simulation results and experimental results be guaranteed.

[0104] Figure 2 This is a schematic diagram of a simulation model for testing air compressors in a high-altitude environment, as per the present invention.

[0105] Figure 2 It includes the following sub-models: air source sub-model 101, air filter sub-model 102, first mass flow meter sub-model 103, second mass flow meter sub-model 1016, first pipeline sub-model 104, second pipeline sub-model 105, third pipeline sub-model 106, fourth pipeline sub-model 108, fifth pipeline sub-model 1010, sixth pipeline sub-model 1013, seventh pipeline sub-model 1014, eighth pipeline sub-model 1015, ninth pipeline sub-model 1017, eighth pipeline sub-model 1019, air compressor sub-model 107, heat exchanger sub-model 109, pressure sensor sub-model 1011, temperature sensor sub-model 1012, electronic valve sub-model 1018, and atmospheric environment sub-model 1020.

[0106] The simulation model structure simply connects the various components of the device to suitable modules in the software, enabling a 1:1 reproduction of the entire device. The performance results of the air compressor are obtained through calculations in the software's backend. This application primarily invents a device and then verifies the validity of the experimental results through a combination of simulation and experimentation.

[0107] The AMEsim software contains many modules, each of which allows for parameter settings. The software model I built can be understood as a complete replication of the experimental setup within the software. If both the results calculated in the software's backend and the results from the experimental setup are valid, they will yield approximately consistent results.

[0108] The relationships between air filter gas flow rate and pressure drop, and between heat exchanger gas flow rate and pressure drop, in the simulation model are input as known parameters into the corresponding sub-models. The first pipeline sub-model 104, the second pipeline sub-model 105, the third pipeline sub-model 106, the fourth pipeline sub-model 108, the fifth pipeline sub-model 1010, the sixth pipeline sub-model 1013, the seventh pipeline sub-model 1014, the eighth pipeline sub-model 1015, the ninth pipeline sub-model 1017, and the eighth pipeline sub-model 1019 need to be confirmed and input with reference to the pipelines in the experimental setup. The three-dimensional data of the air compressor 7 under standard conditions (speed, flow rate, and pressure ratio) and the relationship between the flow coefficient and opening degree of the second electronic valve 18 are also input as known parameters into the corresponding sub-models.

[0109] The pressure in the high-altitude environment is simulated by rewriting the pressure value in air source 1. The operating point of the air compressor during simulation is determined by setting the air compressor speed and the opening degree of the electronic valve.

[0110] according to Figure 2 The constructed simulation model can calculate the compressor boost ratio and flow rate at various operating points under intake pressures of 80kPa-101kPa, and can be compared with... Figure 1 The consistency of the results measured on the experimental platform was verified. This invention includes the construction of a simulation model of the experimental device based on AMEsim software. The simulation results can independently calculate and obtain the performance of the fuel cell air compressor under simulated high-altitude conditions. Furthermore, it can evaluate the validity of the test results obtained by the aforementioned experimental methods, enabling timely detection of anomalies and ensuring data accuracy. The following figure shows a comparison between the experimentally measured flow rate and outlet pressure of a specific air compressor at multiple measurement points and the simulation results:

[0111] Figure 3 A comparison chart of simulation and experimental results of flow rate values ​​at different operating points of the air compressor under an intake pressure of 90 kPa;

[0112] Figure 4 Comparison of simulation and experimental results of pressure values ​​after pressurization at different operating points under an air compressor intake pressure of 90 kPa;

[0113] Figure 5 A comparison chart of simulation and experimental results of flow rate values ​​at different operating points of the air compressor under an intake pressure of 80 kPa;

[0114] Figure 6 The figure shows a comparison of simulation and experimental results of the pressure values ​​after pressurization at different operating points under an air compressor intake pressure of 80 kPa.

[0115] Figures 3-6 The results show that when the air compressor intake pressure is 90 kPa and 80 kPa (simulating atmospheric pressure at altitudes of 1 km and 2 km, respectively), the results obtained using the experimental and simulation methods described in this invention are in good agreement. The simulation model calculations in this invention can serve as an effective means of evaluating air compressor performance and can verify the experimental results.

[0116] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A test method for a fuel cell air compressor performance testing device simulating a high-altitude environment, characterized in that: The testing apparatus includes: An air filter used to filter compressed air; A first electronic valve that controls the amount of air filtered by the air filter; A first mass flow sensor for detecting the gas flow rate of the air filtered by the air filter; A first pressure sensor detects the real-time intake pressure of the air filtered by the air filter before it enters the fuel cell air compressor. An air compressor that compresses filtered air; A second pressure sensor for detecting the intake pressure of the air compressed by the air compressor; A cooling module for cooling the air compressed by the air compressor; A second mass flow sensor for detecting the gas flow rate of the air cooled by the cooling module; A third pressure sensor for detecting the pressure of the air cooled by the cooling module; A second electronic valve that controls the amount of air cooled by the cooling module; A host computer receives the filtered gas flow rate from the first mass flow sensor, the real-time intake pressure of the air compressor to be fed into the fuel cell from the first pressure sensor, the compressed pressure from the second pressure sensor, the cooled air flow rate from the second mass flow sensor, and the cooled air pressure from the third pressure sensor. The host computer adjusts the air compressor pressure between 80 kPa and 101 kPa by setting the operating speed of the air compressor and adjusting the opening angles of the first and second electronic valves to simulate the environmental pressure below 2 km altitude on a plateau. The host computer measures the boost pressure parameters of the air compressor at different pressure and flow operating points to complete the air compressor performance test under conditions below standard atmospheric pressure. Each component of the simulated high-altitude environment fuel cell air compressor performance testing device was mapped to a corresponding sub-model in the AMEsim simulation software. The sub-models were then connected and their parameters were input according to the experimental setup. Simulation calculations yielded the air compressor's performance data. The testing method for the testing device includes the following steps: This includes simulation modeling of a fuel cell air compressor performance testing device in a simulated high-altitude environment, and parameters reflecting the air compressor's performance. Pr Pressure ratio and flow rate m c The calculation formula is as follows: （1） （2） （3） in: dm c To correct the flow rate g / s, w c To correct the engine speed (rpm), P up The actual inlet pressure is ba. P st Standard pressure bar, T up For the actual inlet temperature K, T st The standard temperature is K; the performance curve of the air compressor under standard conditions can be provided by the supplier, and the MAP data of flow rate and pressure can be directly input into the air compressor sub-model, so that the air compressor sub-model can correct the air compressor boost ratio and flow rate values ​​under low air pressure conditions; The opening angle of the first electronic valve affects the airflow rate through the pipeline while adjusting the intake pressure. The formula for calculating the flow rate in the air compressor sub-model is as follows: （4） in: A It is the aperture area m 2 , C q It is the flow coefficient, C m It is the mass flow coefficient ( kg•K / J ) 1 / 2 , P up It is the pressure before the valve. T up It is the temperature before the valve. C q It is a variable related to the valve opening value, the mass flow coefficient. C m The calculation method is as follows: (5) Wherein: γ is the specific heat ratio, defined as the ratio of the isobaric specific heat capacity to the isochoric specific heat capacity of the gas. R It is the universal gas constant, value It is 8.314 [J / K / mol]; Before running the air compressor performance simulation model, you need to input the three-dimensional MAP data of the air compressor's speed, flow rate, and boost ratio at normal temperature and pressure, and provide the opening value of the flow regulating valve and the air compressor speed. Set the air source pressure and temperature at the front end of the model. When the air source pressure is set below 101 kPa, the simulation calculation can obtain the performance results of the air compressor under different operating conditions under the simulated plateau intake pressure. The lower the air source pressure, the higher the corresponding plateau altitude.

2. The test method for a fuel cell air compressor performance testing device simulating a high-altitude environment according to claim 1, characterized in that: It also includes a first temperature sensor that collects the temperature of the gas filtered by the air filter. A second temperature sensor that collects the temperature of the gas compressed by the air compressor; A third temperature sensor that collects the temperature of the gas cooled by the cooling module; The host computer receives the temperature of the filtered gas from the first temperature sensor, the temperature of the compressed gas from the second temperature sensor, and the temperature of the gas cooled by the cooling module, thereby controlling the temperature during the simulated high-altitude environment test.

3. The test method for a fuel cell air compressor performance testing device simulating a high-altitude environment according to claim 1, characterized in that: The cooling module includes a water tank, a water pump, a heat exchanger, and a fan; The pressurized gas is cooled by a heat exchanger; The gas flowing out of the air compressor enters the heat exchanger and the circulating water in the water tank for heat exchange and cooling. The circulating water circuit has a water pump to provide power and a fan to control the temperature.

4. The test method for a fuel cell air compressor performance testing device simulating a high-altitude environment according to claim 1, characterized in that: It also includes a silencer to reduce the noise of the gas discharged after the second electronic valve is controlled.

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