Engine endurance test method, system and device, and readable storage medium

Abstract

This application provides an engine durability testing method, system, device, and readable storage medium. The engine durability testing method includes: acquiring the compressor impeller speed through sensors; adjusting the opening of an electronic valve based on the impeller speed and a preset speed under high-altitude conditions; acquiring the exhaust temperature of the turbocharger turbine; adjusting the opening of a cooler electronic valve based on the exhaust temperature and a first preset temperature value under high-altitude conditions; acquiring the compressor outlet air temperature of the turbocharger; and adjusting the opening of an electronic vent valve based on the outlet air temperature and a second preset temperature value under high-altitude conditions. Through the technical solution of this application, tests simulating high-altitude environments can be conducted in plains environments without the need to construct a high-altitude environment chamber, improving the engine's durability verification capability, fully verifying engine reliability, and reducing the engine failure rate under high-altitude conditions.

Description

Technical Field

[0001] This application relates to the field of mechanical performance testing technology, and more specifically, to an engine durability testing method, system, device, and readable storage medium. Background Technology

[0002] my country has a vast territory and the world's largest plateau region. For diesel engines used in plateau areas, as the altitude increases, the air becomes thinner and the atmospheric pressure decreases. This reduces the actual intake air volume of the diesel engine, leading to a decrease in the final compression pressure and temperature in the cylinder, worsening combustion, increasing the exhaust temperature, and increasing the turbocharger speed. This can easily cause problems such as turbocharger overspeed, overheating, and surge.

[0003] Therefore, it is essential to conduct engine durability tests in high-altitude environments to verify the reliability of the engine and turbocharger. Existing test benches are high-altitude environment chambers, but these are expensive to build and operate. Alternatively, adding a separate regulating valve and vacuum pump to the engine (turbocharger) intake can cause the turbocharger compressor outlet temperature to exceed limits, rendering it unsuitable for durability testing. Furthermore, few companies conduct simulated high-altitude durability tests, resulting in high engine failure rates. Summary of the Invention

[0004] This application aims to solve or improve the aforementioned technical problems.

[0005] Therefore, the primary objective of this application is to provide a method for testing engine durability.

[0006] The second objective of this application is to provide an engine durability testing system.

[0007] The third objective of this application is to provide an engine durability testing apparatus.

[0008] The fourth objective of this application is to provide an engine durability testing system.

[0009] The fifth objective of this application is to provide a readable storage medium.

[0010] To achieve the first objective of this application, the technical solution of the first aspect of this application provides an engine durability testing method, comprising: acquiring the impeller speed of the compressor through a sensor; adjusting the opening of an electronic valve according to the impeller speed and a preset speed under high-altitude conditions; acquiring the front exhaust temperature of the turbocharger turbine; adjusting the opening of the cooler electronic valve according to the front exhaust temperature and a first preset temperature value under high-altitude conditions; acquiring the compressor outlet air temperature of the turbocharger; and adjusting the opening of an electronic vent valve according to the outlet air temperature and a second preset temperature value under high-altitude conditions.

[0011] According to the engine durability testing method provided in this application, the compressor impeller speed is first acquired using sensors. The opening of the electronic valve is then adjusted based on the impeller speed and a preset speed for high-altitude environments until the impeller speed reaches the preset speed for high-altitude environments. Next, the exhaust temperature of the turbocharger turbine is acquired, and the opening of the cooler electronic valve is adjusted based on the exhaust temperature and a first preset temperature value until the exhaust temperature of the turbocharger turbine reaches the first preset temperature value for high-altitude environments. Finally, the compressor outlet air temperature is acquired, and the opening of the electronic vent valve is adjusted based on the outlet air temperature and a second preset temperature value until the outlet air temperature reaches the second preset temperature value for high-altitude environments. This technical solution eliminates the need to construct a high-altitude environment chamber to simulate high-altitude environments in a plain environment, improving the engine's durability verification capability, fully verifying engine reliability, reducing the engine failure rate in high-altitude environments, and saving significant construction and operating costs associated with high-altitude environment chambers. Furthermore, the compressor outlet temperature will not exceed the limit during the test, preventing impeller failure and ensuring the test does not conform to actual high-altitude parameters.

[0012] In addition, the technical solution provided in this application may also have the following additional technical features:

[0013] In the above technical solution, adjusting the opening of the electronic valve according to the impeller speed and the preset speed in the high-altitude environment specifically includes: determining whether the impeller speed is lower than the preset speed in the high-altitude environment; if so, adjusting the opening of the electronic valve through the electronic control unit and determining whether the impeller speed is lower than the preset speed in the high-altitude environment; if so, adjusting the opening of the electronic throttle valve through the electronic control unit and determining whether the impeller speed is lower than the preset speed in the high-altitude environment; if so, adjusting the fuel injection flow of the engine through the electronic control unit.

[0014] In this technical solution, the opening of the electronic valve is adjusted according to the impeller speed and the preset speed for high-altitude environments. Specifically, when the impeller speed is lower than the preset speed for high-altitude environments, the electronic control unit automatically adjusts the opening of the electronic valve to reduce the amount and proportion of exhaust gas that bypasses the turbocharger turbine and is directly discharged to the turbine outlet, thereby increasing the turbocharger speed until the preset speed for high-altitude environments is reached. If this cannot be achieved, the electronic control unit adjusts the electronic throttle valve to regulate the compressor inlet pressure, but not exceeding the permissible limit. If this still cannot be achieved, the electronic control unit adjusts the engine's fuel injection flow rate until the turbocharger speed for high-altitude environments is reached.

[0015] In the above technical solution, adjusting the opening of the cooler electronic valve according to the front exhaust temperature and a first preset temperature value under high-altitude conditions specifically includes: determining whether the front exhaust temperature is lower than the first preset temperature value; if so, adjusting the opening of the cooler electronic valve through the electronic control unit, and determining whether the front exhaust temperature is lower than the first preset temperature value; if so, adjusting the engine fuel injection flow through the electronic control unit; determining whether the front exhaust temperature exceeds the first preset temperature value; if so, adjusting the opening of the cooler electronic valve through the electronic control unit.

[0016] In this technical solution, the opening of the cooler's electronic valve is adjusted based on the exhaust temperature and a first preset temperature value for high-altitude environments. Specifically, the electronic control unit analyzes whether the exhaust temperature of the turbocharger's turbine has reached the first preset temperature value for high-altitude environments. If it has not, the electronic control unit adjusts the opening of the cooler's electronic valve to reduce cooling of the compressor outlet (i.e., the pressurized air), thus raising the exhaust temperature. If it still cannot reach the first preset temperature value, the electronic control unit adjusts the engine's fuel injection flow until the first preset temperature value for high-altitude environments is reached. If the electronic control unit detects that the exhaust temperature of the turbocharger's turbine has exceeded the first preset temperature value for high-altitude environments, the electronic control unit adjusts the opening of the cooler's electronic valve to increase cooling of the compressor outlet (i.e., the pressurized air), until the first preset temperature value for high-altitude environments is reached.

[0017] In the above technical solution, adjusting the opening of the electronic vent valve according to the outlet air temperature and the second preset temperature value under high-altitude environment specifically includes: determining whether the outlet air temperature is lower than the second preset temperature value; if so, adjusting the opening of the electronic vent valve through the electronic control unit.

[0018] In this technical solution, the opening of the electronic vent valve is adjusted according to the outlet air temperature and the second preset temperature value under high-altitude conditions. Specifically, the electronic control unit analyzes whether the outlet air temperature of the compressor of the booster, i.e., the temperature of the boosted air, reaches the second preset temperature value under high-altitude conditions. If it does not reach the second preset temperature value under high-altitude conditions, the electronic control unit adjusts the opening of the electronic vent valve to allow a portion of the boosted air to leak directly into the atmosphere, thereby reducing the compressor efficiency and increasing the compressor outlet air temperature.

[0019] The above technical solution, which adjusts the opening of the electronic vent valve according to the outlet air temperature and the second preset temperature value under high-altitude conditions, also includes: determining whether the outlet air temperature exceeds the second preset temperature value; if so, adjusting the air conditioning temperature at the compressor inlet through the electronic control unit.

[0020] In this technical solution, if the electronic control unit analyzes that the compressor outlet air temperature of the turbocharger has exceeded the second preset temperature value under high-altitude conditions, the electronic control unit adjusts the air conditioning temperature at the compressor inlet to reduce the intake air temperature, thereby reducing the air temperature at the compressor outlet.

[0021] To achieve the second objective of this application, the technical solution of the second aspect of this application provides an engine durability testing system, comprising: a first acquisition module for acquiring the impeller speed of the compressor via a sensor; a first adjustment module for adjusting the opening of an electronic valve according to the impeller speed and a preset speed under high-altitude conditions; a second acquisition module for acquiring the front exhaust temperature of the turbocharger turbine; a second adjustment module for adjusting the opening of a cooler electronic valve according to the front exhaust temperature and a first preset temperature value under high-altitude conditions; a third acquisition module for acquiring the compressor outlet air temperature of the turbocharger; and a third adjustment module for adjusting the opening of an electronic vent valve according to the outlet air temperature and a second preset temperature value under high-altitude conditions.

[0022] The engine durability testing system provided in this application includes a first acquisition module, a first adjustment module, a second acquisition module, a second adjustment module, a third acquisition module, and a third adjustment module. The first acquisition module acquires the compressor impeller speed via a sensor. The first adjustment module adjusts the opening of an electronic valve based on the impeller speed and a preset speed under high-altitude conditions. The second acquisition module acquires the exhaust temperature of the turbocharger's turbine. The second adjustment module adjusts the opening of the cooler's electronic valve based on the exhaust temperature and a first preset temperature value under high-altitude conditions. The third acquisition module acquires the compressor outlet air temperature of the turbocharger. The third adjustment module adjusts the opening of an electronic vent valve based on the outlet air temperature and a second preset temperature value under high-altitude conditions.

[0023] To achieve the third objective of this application, the technical solution of the third aspect of this application provides an engine durability testing device, comprising: an engine body; an engine turbocharger connected to the engine body, the engine turbocharger including a compressor and a turbine, a sensor on the compressor for monitoring the impeller speed of the compressor; an electronic throttle valve located on the compressor's intake pipe for regulating the intake flow rate and pressure; an electronic vent valve located on the compressor's outlet pipe for discharging air from the pipe to the atmosphere; a cooler located on the compressor's outlet pipe for cooling the air discharged from the compressor, the cooler having an electronic valve for regulating the cooling medium; an electronic valve located on the engine turbocharger for regulating the exhaust gas bypass rate of the turbine; and an air conditioner connected to the compressor's intake port.

[0024] The engine durability testing apparatus provided in this application includes an engine block, an engine turbocharger, an electronic throttle valve, an electronic vent valve, a cooler, electronic valves, and an air conditioner. Specifically, a sensor for monitoring the compressor impeller speed is installed on the compressor of the turbocharger. An electronic throttle valve for adjusting the intake flow rate and pressure is installed in the compressor's inlet intake pipe. An electronic vent valve for discharging air from the pipe to the atmosphere is installed in the compressor's outlet exhaust pipe. A cooler for cooling the air discharged from the compressor is installed in the compressor's outlet exhaust pipe, and the cooler has an electronic valve for adjusting the cooling medium. By adjusting the opening of the electronic valve, different degrees of cooling of the air are achieved. An electronic valve for adjusting the turbine exhaust bypass rate is installed on the turbocharger. By adjusting the opening of the electronic valve, the amount and proportion of exhaust gas that bypasses the turbocharger turbine and is directly discharged to the turbine outlet are controlled. An air conditioner is installed at the compressor inlet of the turbocharger. The technical solution presented in this application allows for simulation of high-altitude environments in plains environments without the need to construct a high-altitude environment chamber. This improves the engine's durability verification capabilities, fully verifies its reliability, reduces the engine's failure rate in high-altitude environments, and saves significant construction and operating costs associated with high-altitude environment chambers. Furthermore, the compressor outlet temperature will not exceed the limit during testing, preventing impeller failure and ensuring the test does not accurately reflect actual high-altitude parameters.

[0025] In the above technical solution, the engine durability test device also includes an electronic control unit, which is connected to the sensor, electronic throttle valve, electronic vent valve, cooler electronic valve, electronic valve and air conditioner respectively, and is used to control the sensor, electronic throttle valve, electronic vent valve, cooler electronic valve, electronic valve and air conditioner.

[0026] In this technical solution, the engine durability testing device also includes an electronic control unit. The electronic control unit is connected to the sensors, electronic throttle valve, electronic vent valve, cooler electronic valve, electronic valve, and air conditioner, and is used to control the sensors, electronic throttle valve, electronic vent valve, cooler electronic valve, electronic valve, and air conditioner.

[0027] To achieve the fourth objective of this application, the technical solution of the fourth aspect of this application provides an engine durability testing system, including: a memory and a processor, wherein the memory stores a program or instructions that can be run on the processor, and when the processor executes the program or instructions, it implements the engine durability testing method of any one of the technical solutions of the first aspect, thus having the technical effects of any one of the technical solutions of the first aspect, which will not be elaborated here.

[0028] To achieve the fifth objective of this application, the technical solution of the fifth aspect of this application provides a readable storage medium storing a program or instructions thereon. When the program or instructions are executed by a processor, they implement the steps of the engine durability test method of any one of the technical solutions of the first aspect, and thus have the technical effects of any one of the technical solutions of the first aspect, which will not be repeated here.

[0029] Additional aspects and advantages of this application will become apparent in the following description or may be learned by practice of this application. Attached Figure Description

[0030] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:

[0031] Figure 1 This is a schematic flowchart of the steps of an engine durability testing method according to an embodiment of this application;

[0032] Figure 2 This is a flowchart illustrating the steps of an engine durability testing method according to an embodiment of this application;

[0033] Figure 3 This is a schematic flowchart of the steps of an engine durability testing method according to an embodiment of this application;

[0034] Figure 4 This is a flowchart illustrating the steps of an engine durability testing method according to an embodiment of this application;

[0035] Figure 5 This is a schematic block diagram of the structure of an engine durability testing system according to an embodiment of this application;

[0036] Figure 6 This is a schematic block diagram of the structure of an engine durability testing system according to another embodiment of this application;

[0037] Figure 7 This is a schematic diagram illustrating the working principle of an engine durability testing device according to an embodiment of this application.

[0038] in, Figures 5 to 7 The correspondence between the reference numerals and component names in the attached drawings is as follows:

[0039] 10: Engine durability testing system; 110: First acquisition module; 120: First adjustment module; 130: Second acquisition module; 140: Second adjustment module; 150: Third acquisition module; 160: Third adjustment module; 20: Engine durability testing device; 200: Engine body; 212: Compressor; 214: Turbine; 216: Sensor; 220: Electronic throttle valve; 230: Electronic vent valve; 240: Cooler; 250: Electronic valve; 260: Air conditioner; 270: Electronic control unit; 30: Engine durability testing system; 300: Memory; 400: Processor. Detailed Implementation

[0040] To better understand the above-mentioned objectives, features, and advantages of this application, the application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0041] Many specific details are set forth in the following description in order to provide a full understanding of this application. However, this application may also be implemented in other ways different from those described herein. Therefore, the scope of protection of this application is not limited to the specific embodiments disclosed below.

[0042] The following reference Figures 1 to 7 This application describes engine durability testing methods, systems, apparatus, and readable storage media according to some embodiments.

[0043] like Figure 1 As shown, an embodiment of the first aspect of this application provides a method for testing the durability of an engine, comprising the following steps:

[0044] Step S102: Obtain the impeller speed of the compressor through a sensor;

[0045] Step S104: Adjust the opening of the electronic valve according to the impeller speed and the preset speed in the high-altitude environment;

[0046] Step S106: Obtain the exhaust temperature of the turbocharger's turbine front section;

[0047] Step S108: Adjust the opening of the cooler's electronic valve according to the exhaust temperature and the first preset temperature value under high-altitude conditions;

[0048] Step S110: Obtain the outlet air temperature of the compressor in the booster;

[0049] Step S112: Adjust the opening of the electronic vent valve according to the outlet air temperature and the second preset temperature value under high-altitude conditions.

[0050] According to the engine durability testing method provided in this embodiment, firstly, the compressor impeller speed is acquired through sensors, and the opening of the electronic valve is adjusted according to the impeller speed and a preset speed under high-altitude conditions until the impeller speed reaches the preset speed under high-altitude conditions. Then, the exhaust temperature of the turbocharger turbine is acquired, and the opening of the cooler electronic valve is adjusted according to the exhaust temperature and a first preset temperature value until the exhaust temperature of the turbocharger turbine reaches the first preset temperature value under high-altitude conditions. Finally, the compressor outlet air temperature is acquired, and the opening of the electronic vent valve is adjusted according to the outlet air temperature and a second preset temperature value until the outlet air temperature reaches the second preset temperature value under high-altitude conditions. Through the technical solution of this application, tests simulating high-altitude environments can be conducted in plains environments without the need to construct a high-altitude environment chamber, improving the engine's durability verification capability, fully verifying engine reliability, reducing the engine failure rate under high-altitude conditions, and saving significant construction and operating costs of high-altitude environment chambers. Furthermore, the compressor outlet temperature will not exceed the limit during the test, preventing impeller failure and ensuring the test does not conform to actual high-altitude parameters. The turbocharger speed, exhaust temperature, and compressor outlet temperature are all subject to limited control and can be automatically adjusted.

[0051] like Figure 2 As shown, the engine durability testing method according to an embodiment of this application adjusts the opening of the electronic valve according to the impeller speed and a preset speed under high-altitude conditions, specifically including the following steps:

[0052] Step S202: Determine whether the impeller speed is lower than the preset speed for high-altitude environments;

[0053] Step S204: If yes, adjust the opening of the electronic valve through the electronic control unit and determine whether the impeller speed is lower than the preset speed in the high-altitude environment;

[0054] Step S206: If yes, adjust the opening of the electronic throttle valve through the electronic control unit and determine whether the impeller speed is lower than the preset speed in the high-altitude environment;

[0055] Step S208: If so, adjust the engine fuel injection flow rate via the electronic control unit.

[0056] In this embodiment, the opening of the electronic valve is adjusted according to the impeller speed and a preset speed for high-altitude environments. Specifically, when the impeller speed is lower than the preset speed for high-altitude environments, the electronic control unit automatically adjusts the opening of the electronic valve to reduce the amount and proportion of exhaust gas that bypasses the turbocharger turbine and is directly discharged to the turbine outlet, thereby increasing the turbocharger speed until the preset speed for high-altitude environments is reached. If this cannot be achieved, the electronic control unit adjusts the electronic throttle valve to regulate the compressor inlet pressure, but not exceeding the permissible limit. If this still cannot be achieved, the electronic control unit adjusts the engine's fuel injection flow rate until the turbocharger speed for high-altitude environments is reached.

[0057] like Figure 3 As shown, the engine durability testing method according to an embodiment of this application adjusts the opening of the cooler electronic valve based on the exhaust temperature and a first preset temperature value under high-altitude conditions, specifically including the following steps:

[0058] Step S302: Determine whether the exhaust temperature of the front section is lower than the first preset temperature value;

[0059] Step S304: If yes, adjust the opening of the cooler's electronic valve through the electronic control unit and determine whether the exhaust temperature of the front section is lower than the first preset temperature value.

[0060] Step S306: If so, adjust the engine fuel injection flow rate via the electronic control unit;

[0061] Step S308: Determine whether the exhaust temperature of the front section exceeds the first preset temperature value;

[0062] Step S310: If so, adjust the opening of the cooler's electronic valve through the electronic control unit.

[0063] In this embodiment, the opening of the cooler's electronic valve is adjusted based on the exhaust temperature and a first preset temperature value. Specifically, the electronic control unit analyzes whether the exhaust temperature of the turbocharger's turbine has reached the first preset temperature value for high-altitude environments. If it has not, the electronic control unit adjusts the opening of the cooler's electronic valve to reduce cooling of the compressor outlet (i.e., the pressurized air), thereby increasing the exhaust temperature. If the temperature still cannot be reached, the electronic control unit adjusts the engine's fuel injection flow rate until the first preset temperature value for high-altitude environments is achieved. If the electronic control unit detects that the exhaust temperature of the turbocharger's turbine has exceeded the first preset temperature value for high-altitude environments, the electronic control unit adjusts the opening of the cooler's electronic valve to increase cooling of the compressor outlet (i.e., the pressurized air), until the first preset temperature value for high-altitude environments is reached.

[0064] like Figure 4As shown, the engine durability testing method according to an embodiment of this application adjusts the opening of the electronic vent valve based on the outlet air temperature and a second preset temperature value under high-altitude conditions, specifically including the following steps:

[0065] Step S402: Determine whether the outlet air temperature is lower than the second preset temperature value;

[0066] Step S404: If so, adjust the opening of the electronic vent valve through the electronic control unit;

[0067] Step S406: Determine whether the outlet air temperature exceeds the second preset temperature value;

[0068] Step S408: If so, adjust the air conditioning temperature at the compressor inlet via the electronic control unit.

[0069] In this embodiment, the opening of the electronic vent valve is adjusted based on the outlet air temperature and a second preset temperature value. Specifically, the electronic control unit analyzes whether the outlet air temperature of the supercharger compressor, i.e., the temperature of the pressurized air, reaches the second preset temperature value for high-altitude environments. If it does not reach the second preset temperature value, the electronic control unit adjusts the opening of the electronic vent valve, allowing some of the pressurized air to leak directly into the atmosphere, reducing compressor efficiency and thus increasing the compressor outlet air temperature. If the electronic control unit analyzes that the outlet air temperature of the supercharger compressor has exceeded the second preset temperature value for high-altitude environments, the electronic control unit adjusts the air conditioning temperature at the compressor inlet to lower the inlet air temperature, thereby lowering the compressor outlet air temperature.

[0070] In the above embodiments, the preset rotational speed is less than or equal to 560 meters per second. The first preset temperature value is less than or equal to 720°C. The second preset temperature value is less than or equal to 210°C. Specifically, the preset rotational speed in high-altitude environments is less than or equal to 560 meters per second. The first preset temperature value in high-altitude environments is less than or equal to 720°C, but some models or engine manufacturers use less than or equal to 745°C or 760°C. The second preset temperature value in high-altitude environments is less than or equal to 230°C, but some models or engine manufacturers use less than or equal to 210°C.

[0071] like Figure 5As shown, an embodiment of the second aspect of this application provides an engine durability testing system 10, comprising: a first acquisition module 110 for acquiring the impeller speed of the compressor via a sensor; a first adjustment module 120 for adjusting the opening of an electronic valve according to the impeller speed and a preset speed under high-altitude conditions; a second acquisition module 130 for acquiring the front exhaust temperature of the turbocharger turbine; a second adjustment module 140 for adjusting the opening of a cooler electronic valve according to the front exhaust temperature and a first preset temperature value under high-altitude conditions; a third acquisition module 150 for acquiring the compressor outlet air temperature of the turbocharger; and a third adjustment module 160 for adjusting the opening of an electronic vent valve according to the outlet air temperature and a second preset temperature value under high-altitude conditions.

[0072] The engine durability testing system 10 provided in this embodiment includes a first acquisition module 110, a first adjustment module 120, a second acquisition module 130, a second adjustment module 140, a third acquisition module 150, and a third adjustment module 160. The first acquisition module 110 acquires the compressor impeller speed via a sensor. The first adjustment module 120 adjusts the opening of an electronic valve based on the impeller speed and a preset speed under high-altitude conditions. The second acquisition module 130 acquires the exhaust temperature of the turbocharger's turbine. The second adjustment module 140 adjusts the opening of the cooler's electronic valve based on the exhaust temperature and a first preset temperature value under high-altitude conditions. The third acquisition module 150 acquires the compressor outlet air temperature of the turbocharger. The third adjustment module 160 adjusts the opening of an electronic vent valve based on the outlet air temperature and a second preset temperature value under high-altitude conditions.

[0073] like Figure 7 As shown, an embodiment of the third aspect of this application provides an engine durability testing apparatus 20, comprising: an engine body 200; an engine turbocharger connected to the engine body 200, the engine turbocharger including a compressor 212 and a turbine 214, a sensor 216 provided on the compressor 212 for monitoring the impeller speed of the compressor 212; an electronic throttle valve 220 provided on the intake pipe of the compressor 212 for adjusting the intake flow rate and pressure; and an electronic discharge... Air valve 230 is located on the outlet pipe of compressor 212 and is used to discharge air from the pipe to the atmosphere; cooler 240 is located on the outlet pipe of compressor 212 and is used to cool the air discharged from compressor 212. Cooler 240 is equipped with a cooler electronic valve, which is used to regulate the cooling medium; electronic valve 250 is located on the engine turbocharger and is used to regulate the exhaust gas bypass of turbine 214; air conditioner 260 is connected to the air inlet of compressor 212.

[0074] The engine durability testing apparatus 20 provided in this embodiment includes an engine body 200, an engine turbocharger, an electronic throttle valve 220, an electronic vent valve 230, a cooler 240, an electronic valve 250, and an air conditioner 260. Specifically, a sensor 216 for monitoring the impeller speed of the compressor 212 is provided on the compressor 212 of the engine turbocharger. An electronic throttle valve 220 for adjusting the intake flow rate and pressure is provided in the inlet intake pipe of the compressor 212. An electronic vent valve 230 for discharging air from the pipe to the atmosphere is provided in the outlet exhaust pipe of the compressor 212. A cooler 240 for cooling the air discharged from the compressor 212 is provided in the outlet exhaust pipe of the compressor 212. The cooler 240 is equipped with a cooler electronic valve for adjusting the cooling medium. By adjusting the opening of the cooler electronic valve, different degrees of cooling of the air can be achieved. An electronic valve 250 is installed on the turbocharger to adjust the bypass flow of exhaust gas from turbine 214. By adjusting the opening of the electronic valve 250, the amount and proportion of exhaust gas that bypasses the turbocharger turbine and is directly discharged to the outlet of turbine 214 are controlled. An air conditioner 260 is installed at the inlet of compressor 212 in the turbocharger. Through the technical solution of this application, tests simulating high-altitude environments can be conducted in a plain environment without the need to construct a high-altitude environment chamber. This improves the engine's durability verification capability, fully verifies engine reliability, reduces the engine's failure rate in high-altitude environments, and saves significant construction and operating costs of high-altitude environment chambers. Furthermore, the outlet temperature of compressor 212 will not exceed the limit during testing, preventing impeller failure and ensuring the test does not conform to actual high-altitude parameters.

[0075] In the above embodiments, the engine durability testing device further includes an electronic control unit 270. The electronic control unit 270 is connected to the sensor 216, the electronic throttle valve 220, the electronic vent valve 230, the cooler electronic valve, the electronic valve 250, and the air conditioner 260, respectively, and is used to control the sensor 216, the electronic throttle valve 220, the electronic vent valve 230, the cooler electronic valve, the electronic valve 250, and the air conditioner 260.

[0076] like Figure 6 As shown, an embodiment of the fourth aspect of this application provides an engine durability testing system 30, including a memory 300 and a processor 400. The memory 300 stores a program or instructions that can be run on the processor 400. When the processor 400 executes the program or instructions, it implements the steps of the engine durability testing method of any one of the embodiments of the first aspect, and thus has the technical effects of any embodiment of the first aspect, which will not be repeated here.

[0077] The fifth aspect of this application provides a readable storage medium storing a program or instructions thereon. When the program or instructions are executed by a processor, they implement the steps of the engine durability test method of any one of the embodiments of the first aspect, and thus have the technical effects of any of the embodiments of the first aspect, which will not be repeated here.

[0078] like Figures 1 to 7 As shown, according to a specific embodiment of the engine durability testing method provided in this application, a sensor 216 for monitoring the compressor impeller speed is installed on the compressor 212 of the turbocharger; an electronic throttle valve 220 for adjusting the intake flow and pressure is installed in the inlet intake pipe of the compressor 212; an electronic vent valve 230 for venting air from the pipe to the atmosphere is installed in the outlet exhaust pipe of the compressor 212; a cooler 240 for cooling the air discharged from the compressor 212 is installed in the outlet exhaust pipe of the compressor 212; an electronic valve 250 for adjusting the bypass volume of the turbine 214 is installed on the turbocharger; and an air conditioner 260 is installed at the inlet of the compressor 212 of the turbocharger. The sensor 216, electronic throttle valve 220, cooler 240, and air conditioner 260 communicate and connect with the electronic control unit 270 and are automatically adjusted (or they can be manually adjusted without connection or communication).

[0079] In the first step, the electronic control unit automatically adjusts the opening of the electronic valve until the required speed is reached for high-altitude environments. n高原 Step 2: The electronic control unit adjusts the opening of the cooler's electronic valves until the exhaust temperature of the turbocharger's turbine reaches the temperature value T3 required for high-altitude environments, and analyzes whether the turbocharger's compressor impeller speed has reached the value required for high-altitude environments. n高原 Otherwise, proceed to step 1; Step 3: The electronic control unit analyzes whether the outlet air temperature of the supercharger compressor, i.e., the temperature of the supercharged air, reaches the temperature value T2 in the high-altitude environment. If it does not reach the temperature value, the electronic control unit adjusts the opening of the electronic vent valve and simultaneously analyzes whether the impeller speed of the supercharger compressor is within the range of the high-altitude environment. n高原 Otherwise, proceed to step 1 to analyze whether the exhaust temperature of the turbine reaches the temperature value T3 under high-altitude conditions; otherwise, proceed to step 2.

[0080] Specifically, the engine durability testing apparatus includes an engine tested on an engine test bench, engine performance parameter testing and acquisition equipment, and parameter control and adjustment equipment. A sensor 216 for monitoring the compressor impeller speed is installed on the compressor 212 of the engine turbocharger; the sensor 216 communicates with and is connected to the electronic control unit 270. An electronic throttle valve 220 for adjusting intake flow and pressure is installed in the inlet intake pipe of the compressor 212; the electronic throttle valve 220 communicates with and is connected to the electronic control unit 270, which can automatically adjust the opening of the electronic throttle valve 220. An electronic vent valve 230 for venting air from the pipe to the atmosphere is installed in the outlet exhaust pipe of the compressor 212; the electronic vent valve 230 communicates with and is connected to the electronic control unit 270, which can automatically adjust the opening of the electronic vent valve 230. A cooler 240 is installed in the outlet pipe of compressor 212 to cool the air discharged from compressor 212. The cooler 240 is equipped with an electronic valve for adjusting the cooling medium. The electronic valve communicates and is connected to an electronic control unit 270, which can automatically adjust the opening of the electronic valve to achieve different degrees of cooling of the air. An electronic valve 250 is installed on the turbocharger to adjust the bypass flow of exhaust gas from turbine 214. The electronic valve 250 communicates and is connected to the electronic control unit 270, which can automatically adjust the opening of the electronic valve 250 to control the amount and proportion of exhaust gas that is discharged directly to the outlet of turbine 214 without passing through the turbocharger turbine. An air conditioner 260 is installed at the inlet of compressor 212 of the turbocharger and communicates and is connected to the electronic control unit 270. The electronic control unit 270 can automatically adjust the temperature of the air conditioner 260.

[0081] The experimental methods and procedures are as follows:

[0082] Based on the engine's performance test data in a plain environment, the main data are shown in Table 1. Engine performance simulation software was used to establish an engine performance model in a plain environment, run the model and perform model calibration to meet the requirements of calculation accuracy.

[0083]

[0084]

[0085] Table 1. Main performance test data of the engine in a plain environment.

[0086] In the engine performance simulation software, the parameters for high-altitude calibration of the engine (such as fuel consumption and advance angle at the highest altitude) are input. The engine boundary conditions (such as ambient pressure, compressor inlet pressure, turbine back pressure, ambient temperature, and compressor inlet temperature) in the high-altitude environment conditioning model are then applied. The model is then run to calculate the engine's performance parameters under these high-altitude environmental boundary conditions. The main parameters are shown in Table 1. These parameters serve as target reference data for the engine's endurance testing in a simulated high-altitude environment under plain conditions.

[0087] The device design and method procedure settings are as follows:

[0088] Step 1: Sensors monitor the compressor impeller speed of the turbocharger and send feedback to the electronic control unit. When the speed is lower than the value required for high-altitude environments... n高原 At this time, the electronic control unit automatically adjusts the opening of the electronic valve to reduce the amount and proportion of exhaust gas that is discharged directly to the turbine outlet without passing through the turbocharger turbine, thereby increasing the turbocharger speed until the speed required for high-altitude environments is reached. n高原 If this cannot be achieved, the electronic control unit adjusts the electronic throttle valve to regulate the compressor inlet pressure (negative pressure), but it must not exceed the permissible limit. If this still cannot be achieved, the electronic control unit adjusts the engine's fuel injection flow until the turbocharger speed suitable for high-altitude environments is reached.

[0089] Step 2: The electronic control unit (ECU) analyzes whether the exhaust temperature at the front end of the turbocharger's turbine reaches the high-altitude temperature value T3. If not, the ECU adjusts the opening of the cooler's electronic valve to reduce cooling of the compressor outlet (compressed air), thus raising the front exhaust temperature. If this still fails to reach the desired temperature, the ECU adjusts the engine's fuel injection flow until the high-altitude temperature value T3 is reached. If the ECU detects that the exhaust temperature at the front end of the turbocharger's turbine exceeds the high-altitude temperature value T3, it adjusts the opening of the cooler's electronic valve to increase cooling of the compressor outlet (compressed air), until the high-altitude temperature value T3 is reached. Simultaneously, the ECU analyzes whether the turbocharger's compressor impeller speed is within the range required for high-altitude environments. n高原 If the value is lower or higher than that in a high-altitude environment n高原 If so, proceed to step 1.

[0090] Step 3: The electronic control unit analyzes whether the compressor outlet air temperature (i.e., the temperature of the pressurized air) reaches the high-altitude environment temperature value T2. If not, the electronic control unit adjusts the opening of the electronic vent valve, allowing some pressurized air to leak directly into the atmosphere, reducing compressor efficiency and thus increasing the compressor outlet air temperature. If the electronic control unit analyzes that the compressor outlet air temperature exceeds the high-altitude environment temperature value T2, it adjusts the compressor inlet air conditioning temperature (built into the test bench) to lower the inlet air temperature, thereby lowering the compressor outlet air temperature. Simultaneously, the electronic control unit analyzes whether the compressor impeller speed is within the range for high-altitude environments. n高原 If the value is lower or higher than that in a high-altitude environment n高原 If so, proceed to step 1. At the same time, the electronic control unit analyzes whether the exhaust temperature of the turbine reaches the temperature value T3 under high-altitude conditions. If it is lower or higher than that under high-altitude conditions, proceed to step 2.

[0091] Step 4: Design a test bench on the engine test bench, add an electronic throttle valve to the inlet intake pipe of the turbocharger compressor, and add an electronic vent valve and a turbocharged air cooler to the outlet exhaust pipe of the turbocharger compressor.

[0092] The above-described methods and procedures were implemented on the inventive device to conduct a durability test in a simulated plateau environment on a plain.

[0093] In summary, the beneficial effects of the embodiments of this application are as follows:

[0094] 1. The test can simulate the high-altitude environment in a plain environment without the need to build a high-altitude environment chamber, which improves the engine's durability verification capability, fully verifies the engine's reliability, and can reduce the engine's failure rate in high-altitude environments.

[0095] 2. Saves on the high costs of constructing and using high-altitude environment chambers.

[0096] 3. The compressor outlet temperature will not exceed the limit during the test, which can prevent the impeller from failing first, making the test impossible and the test not conforming to the actual parameters at high altitude.

[0097] 4. The turbocharger speed, exhaust temperature, and compressor outlet temperature are all subject to limited control and can be automatically adjusted.

[0098] In this application, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance; the term "multiple" refers to two or more unless otherwise expressly defined. The terms "install," "connect," "link," and "fix" should be interpreted broadly. For example, "connect" can mean a fixed connection, a detachable connection, or an integral connection; "link" can mean a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0099] In the description of this application, it should be understood that the terms "upper", "lower", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or module referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0100] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0101] The above are merely preferred embodiments of this application and are not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A method for testing the durability of an engine, characterized in that, include: The impeller speed of the compressor is obtained through sensors; The opening degree of the electronic valve is adjusted according to the impeller speed and the preset speed in the high-altitude environment; Obtain the exhaust temperature of the turbocharger's turbine; The opening of the cooler electronic valve is adjusted according to the exhaust temperature of the front section and the first preset temperature value under high-altitude environment. The cooler is located on the exhaust pipe of the compressor and is used to cool the air discharged from the compressor. The cooler is equipped with the cooler electronic valve, which is used to adjust the cooling medium. Obtain the outlet air temperature of the compressor in the booster; The opening degree of the electronic vent valve is adjusted according to the outlet air temperature and the second preset temperature value under high-altitude conditions; The electronic valve is located in the engine turbocharger and is used to regulate the exhaust gas bypass volume of the turbine. An electronic throttle valve is installed on the air intake line of the compressor and is used to regulate the air intake flow rate and pressure; The electronic vent valve is located on the outlet pipeline of the compressor and is used to discharge pipeline air to the atmosphere. The adjustment of the electronic valve opening based on the impeller speed and a preset speed in a high-altitude environment specifically includes: Determine whether the impeller speed is lower than the preset speed for high-altitude environments; If so, the opening of the electronic valve is adjusted by the electronic control unit, and it is determined whether the impeller speed is lower than the preset speed in a high-altitude environment; If so, the opening of the electronic throttle valve is adjusted by the electronic control unit, and it is determined whether the impeller speed is lower than the preset speed in a high-altitude environment; If so, the engine's fuel injection flow is adjusted via the electronic control unit.

2. The engine durability testing method according to claim 1, characterized in that, The adjustment of the opening degree of the cooler electronic valve based on the exhaust temperature and a first preset temperature value under high-altitude conditions specifically includes: Determine whether the exhaust temperature of the front section is lower than the first preset temperature value; If so, the opening of the cooler's electronic valve is adjusted by the electronic control unit, and it is determined whether the front exhaust temperature is lower than the first preset temperature value. If so, the engine's fuel injection flow is adjusted via the electronic control unit; Determine whether the exhaust temperature of the front section exceeds the first preset temperature value; If so, the opening of the cooler's electronic valve is adjusted via the electronic control unit.

3. The engine durability testing method according to claim 1, characterized in that, The adjustment of the opening degree of the electronic vent valve based on the outlet air temperature and the second preset temperature value under high-altitude conditions specifically includes: Determine whether the outlet air temperature is lower than the second preset temperature value; If so, the opening degree of the electronic vent valve is adjusted through the electronic control unit.

4. The engine durability testing method according to claim 3, characterized in that, The method of adjusting the opening degree of the electronic vent valve according to the outlet air temperature and the second preset temperature value under high-altitude environment also includes: Determine whether the outlet air temperature exceeds the second preset temperature value; If so, the air conditioning temperature at the compressor inlet is adjusted via the electronic control unit.

5. An engine durability testing system, characterized in that, include: The first acquisition module (110) is used to acquire the impeller speed of the compressor through a sensor; The first adjustment module (120) is used to adjust the opening of the electronic valve according to the impeller speed and the preset speed in the high-altitude environment; The second acquisition module (130) is used to acquire the front exhaust temperature of the turbocharger's turbine. The second adjustment module (140) is used to adjust the opening of the cooler electronic valve according to the front exhaust temperature and the first preset temperature value under high altitude conditions. The third acquisition module (150) is used to acquire the outlet air temperature of the compressor of the booster; The third adjustment module (160) is used to adjust the opening degree of the electronic vent valve according to the outlet air temperature and the second preset temperature value under the high-altitude environment. The electronic valve is located in the engine turbocharger and is used to regulate the exhaust gas bypass volume of the turbine. An electronic throttle valve is installed on the air intake line of the compressor and is used to regulate the air intake flow rate and pressure; The electronic vent valve is located on the outlet pipeline of the compressor and is used to discharge pipeline air to the atmosphere. The adjustment of the electronic valve opening based on the impeller speed and a preset speed in a high-altitude environment specifically includes: Determine whether the impeller speed is lower than the preset speed for high-altitude environments; If so, the opening of the electronic valve is adjusted by the electronic control unit, and it is determined whether the impeller speed is lower than the preset speed in a high-altitude environment; If so, the opening of the electronic throttle valve is adjusted by the electronic control unit, and it is determined whether the impeller speed is lower than the preset speed in a high-altitude environment; If so, the engine's fuel injection flow is adjusted via the electronic control unit; The cooler is located on the outlet pipe of the compressor and is used to cool the air discharged from the compressor. The cooler is equipped with an electronic valve for regulating the cooling medium.

6. An engine durability testing apparatus, characterized in that, include: Engine body (200); An engine supercharger is connected to the engine body. The engine supercharger includes a compressor (212) and a turbine (214). A sensor (216) is provided on the compressor. The sensor (216) is used to monitor the impeller speed of the compressor (212). An electronic throttle valve (220) is provided on the intake pipe of the compressor (212) for regulating the intake flow rate and pressure; An electronic vent valve (230) is provided on the outlet pipeline of the compressor (212) for discharging pipeline air to the atmosphere; A cooler (240) is provided on the outlet pipe of the compressor (212) for cooling the air discharged from the compressor (212). The cooler (240) is provided with a cooler electronic valve for adjusting the cooling medium. An electronic valve (250) is provided on the engine supercharger (210) for regulating the exhaust gas bypass of the turbine (214); An air conditioner (260) is connected to the air inlet of the compressor (212); the engine durability testing device further includes: An electronic control unit (270) is connected to the sensor (216), the electronic throttle valve (220), the electronic vent valve (230), the cooler electronic valve (242), the electronic valve (250), and the air conditioner (260) respectively, and is used to control the sensor (216), the electronic throttle valve (220), the electronic vent valve (230), the cooler electronic valve (242), the electronic valve (250), and the air conditioner (260). The electronic control unit obtains the impeller speed of the compressor through sensors; The opening degree of the electronic valve is adjusted according to the impeller speed and the preset speed in the high-altitude environment; Obtain the exhaust temperature of the turbocharger's turbine; The opening of the cooler's electronic valve is adjusted according to the exhaust temperature of the front section and the first preset temperature value under high-altitude conditions; Obtain the outlet air temperature of the compressor in the booster; The opening degree of the electronic vent valve is adjusted according to the outlet air temperature and the second preset temperature value under high-altitude conditions; The adjustment of the electronic valve opening based on the impeller speed and a preset speed in a high-altitude environment specifically includes: Determine whether the impeller speed is lower than the preset speed for high-altitude environments; If so, the opening of the electronic valve is adjusted by the electronic control unit, and it is determined whether the impeller speed is lower than the preset speed in a high-altitude environment; If so, the opening of the electronic throttle valve is adjusted by the electronic control unit, and it is determined whether the impeller speed is lower than the preset speed in a high-altitude environment; If so, the engine's fuel injection flow is adjusted via the electronic control unit.

7. An engine durability testing system, characterized in that, include: A memory (300) and a processor (400), wherein the memory (300) stores a program or instructions executable on the processor (400), and the processor (400) executes the program or instructions to implement the steps of the engine durability test method as described in any one of claims 1 to 4.

8. A readable storage medium having a program or instructions stored thereon, characterized in that, When the program or the instructions are executed by the processor, they implement the steps of the engine durability test method as described in any one of claims 1 to 4.

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