Experimental device and experimental method for simulating aircraft wake cloud generation and evolution

Abstract

The application discloses an experimental device and experimental method for simulating aircraft wake cloud generation and evolution, and relates to the field of experimental devices for simulating aircraft wake cloud generation and evolution. The experimental device for simulating aircraft wake cloud generation and evolution comprises a gas supply system, an altitude simulation system, a wake cloud generation and evolution system and a gas extraction system. The altitude simulation system comprises a test cabin provided with an aero-engine. The first gas supply system delivers low-temperature gas towards the aero-engine. The wake cloud generation and evolution system comprises an environment cabin, a nozzle and a dilution assembly. The dilution assembly receives and dilutes exhaust gas of the aero-engine and delivers the diluted exhaust gas to the nozzle. The nozzle sprays the exhaust gas into the environment cabin. The second gas supply system delivers low-temperature and high-humidity gas towards the environment cabin. The gas extraction system extracts gas in the test cabin, the aero-engine and the environment cabin. The experimental device for simulating aircraft wake cloud generation and evolution can realize the generation and evolution of simulated wake clouds, thereby facilitating the subsequent research on the influence of aviation emissions on global climate.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine experiments, and in particular to an experimental device and an experimental method for simulating the generation and evolution of aircraft contrail clouds. BACKGROUND

[0002] Contrail clouds are linear ice clouds generated by aircraft cruising in the upper troposphere, and are the only artificial ice clouds. The global cloud cover change caused by contrail clouds leads to an imbalance between the incoming radiation from the sun and the updraft radiation from the earth's surface and atmosphere, resulting in a trend of radiation forcing of the climate and a change in the temperature structure of the lower atmosphere.

[0003] Currently, the research on contrail clouds mainly includes CFD (Computational Fluid Dynamics), climate model simulation and satellite cloud identification. However, due to the lack of a perfect experimental device and method for the generation and evolution of contrail clouds, the understanding of the physical and chemical properties of contrail clouds, the formation of contrail clouds and the transformation of contrail clouds into cirrus clouds is still unclear, and the scientific uncertainty limits the prediction of the overall climate impact of aviation and hinders the development of mitigation measures.

[0004] Therefore, it is necessary to develop an experimental device for simulating the generation and evolution of contrail clouds to support the research on the global climate impact of aviation emissions. SUMMARY

[0005] The present application aims to at least solve one of the technical problems existing in the prior art. To this end, the present application proposes an experimental device for simulating the generation and evolution of aircraft contrail clouds, which can effectively simulate the generation and evolution of contrail clouds, and solve the technical problem that the lack of a perfect experimental device for the generation and evolution of contrail clouds in the prior art leads to unclear understanding of contrail clouds and inability to effectively develop mitigation measures.

[0006] The present application also aims to propose an experimental method for the above-mentioned experimental device for simulating the generation and evolution of aircraft contrail clouds.

[0007] The experimental device for simulating aircraft wake cloud generation and evolution according to the embodiment of the present application comprises: a first gas supply system and a high-altitude simulation system, the high-altitude simulation system comprises a test cabin, an aero-engine is arranged in the test cabin, and the first gas supply system is used for conveying low-temperature gas towards the aero-engine; a wake cloud generation and evolution system, the wake cloud generation and evolution system comprises an environment cabin, a nozzle and a dilution assembly, the dilution assembly is used for receiving and diluting exhaust gas of the aero-engine, conveying the diluted exhaust gas to the nozzle, and the nozzle can spray the exhaust gas into the environment cabin; a second gas supply system, the second gas supply system is used for conveying low-temperature and high-humidity gas towards the environment cabin; and a gas extraction system, the gas extraction system is in communication with the test cabin, the aero-engine and the environment cabin respectively, and is used for extracting gas in the test cabin, the aero-engine and the environment cabin.

[0008] The experimental device for simulating aircraft wake cloud generation and evolution according to the embodiment of the present application can form a low-humidity, low-pressure and high-humidity environment in the environment cabin by arranging the second gas supply system for conveying low-temperature and high-humidity gas towards the environment cabin and arranging the gas extraction system for extracting gas in the environment cabin, so as to simulate a high-altitude environment in the environment cabin. Meanwhile, the application also arranges the dilution assembly for receiving and diluting the exhaust gas of the aero-engine and arranges the nozzle for spraying gas into the environment cabin. In this way, when the exhaust gas of the aero-engine enters the dilution assembly, the dilution assembly can dilute the exhaust gas, and the nozzle can spray the diluted exhaust gas into the environment cabin, so as to simulate the generation and evolution process of the wake cloud continuously, facilitate the research on the wake cloud, and facilitate the subsequent development of measures for relieving the wake cloud and the research on the influence of aviation emission on global climate.

[0009] The experimental device for simulating aircraft wake cloud generation and evolution according to some embodiments of the present application, the dilution assembly comprises: a diluter in communication with the aero-engine for receiving and diluting the exhaust gas of the aero-engine; and a gas supply element in communication with the diluter for conveying dilution gas towards the diluter.

[0010] Optionally, the diluter comprises a dilution cavity, a first gas inlet and a gas outlet arranged at axial two ends of the dilution cavity, the first gas inlet and the gas outlet are in communication with the dilution cavity, the exhaust gas of the aero-engine enters the dilution cavity through the first gas inlet, and the gas outlet is used for discharging the gas in the dilution cavity.

[0011] Optionally, the diluter further comprises a second gas inlet arranged in the circumferential direction of the diluter, the second gas inlet is in communication with the dilution cavity, and the gas supply element conveys dilution gas towards the dilution cavity through the second gas inlet.

[0012] Optionally, the second air inlet comprises a plurality of second air inlets, the plurality of second air inlets are arranged along a radial direction of the diluter, and the second air inlets are inclinedly arranged from outside to inside along the radial direction of the diluter and towards the air outlet.

[0013] According to some embodiments of the present application, the experimental device for simulating the generation and evolution of aircraft wake cloud comprises a second air supply system, the second air supply system comprises a first refrigerating machine and a first air supply path and a second air supply path connected in parallel, the first air supply path is used for conveying low-humidity gas to the first refrigerating machine, and the second air supply path is used for conveying high-humidity gas to the first refrigerating machine; the first refrigerating machine mixes the received gas and reduces the temperature of the gas, and the first refrigerating machine is used for conveying low-temperature gas to the environment cabin.

[0014] According to some embodiments of the present application, the experimental device for simulating the generation and evolution of aircraft wake cloud comprises a first air supply system, the first air supply system comprises a mixer and a third air supply path, a fourth air supply path and a fifth air supply path connected to the mixer at the same time; wherein the third air supply path is used for conveying normal-temperature gas to the mixer, the fourth air supply path is used for conveying high-temperature gas to the mixer, and the fifth air supply path is used for conveying low-temperature gas to the mixer; the mixer mixes the gas and conveys the gas to the aero-engine.

[0015] According to some embodiments of the present application, the experimental device for simulating the generation and evolution of aircraft wake cloud comprises a high-altitude simulation system, the high-altitude simulation system further comprises a thrust tester and an air inlet valve, the thrust tester is arranged in the test cabin and is used for measuring the thrust of the aero-engine, and the air inlet valve is connected to the test cabin and is used for air inletting to the test cabin.

[0016] According to some embodiments of the present application, the experimental device for simulating the generation and evolution of aircraft wake cloud comprises an air extraction system, the air extraction system comprises a vacuum pump assembly, the vacuum pump assembly is connected to the test cabin, the aero-engine and the environment cabin respectively, and comprises a first vacuum pump and a second vacuum pump connected in parallel; a heat exchanger is arranged between the vacuum pump assembly and the environment cabin, so as to increase the temperature of the gas entering the vacuum pump assembly; and a cooler is arranged between the vacuum pump assembly and the aero-engine, so as to reduce the temperature of the gas entering the vacuum pump assembly.

[0017] The experimental method of the experimental device for simulating aircraft contrail generation and evolution according to the embodiment of the present application comprises the following steps: placing the aero-engine in the test cabin; starting the aero-engine under the ground air intake condition, and judging whether the aero-engine condition is normal, if yes, executing the next step, if not, performing fault elimination; starting the experimental device for simulating aircraft contrail generation and evolution, and using the contrail generation and evolution system to simulate the generation and evolution of the exhaust of the aero-engine.

[0018] The experimental method of the experimental device for simulating aircraft contrail generation and evolution according to the embodiment of the present application, by using the contrail generation and evolution system to simulate the generation and evolution of the exhaust of the aero-engine, can facilitate real-time observation of the change of the contrail, thereby facilitating subsequent research on the contrail, that is, facilitating subsequent development of measures for alleviating the contrail, and providing support for research on the influence of aviation emission on global climate.

[0019] Additional aspects and advantages of the present application will become apparent from the following description, or will be learned by practice of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0020] The above and / or additional aspects and advantages of the present application will become apparent and be readily understood by considering the following detailed description, including the accompanying drawings, in which:

[0021] Figure 1 The principle schematic diagram of the experimental device for simulating aircraft contrail generation and evolution according to some embodiments of the present application.

[0022] Figure 2 The principle schematic diagram of the high-altitude simulation system according to some embodiments of the present application.

[0023] Figure 3 The principle schematic diagram of the contrail generation and evolution system according to some embodiments of the present application.

[0024] Figure 4 The principle schematic diagram of the second gas supply system according to some embodiments of the present application.

[0025] Figure 5 The principle schematic diagram of the first gas supply system according to some embodiments of the present application.

[0026] Figure 6 The flowchart of the experimental method of the experimental device for simulating aircraft contrail generation and evolution according to some embodiments of the present application.

[0027] Figure 7 The flowchart of the experimental method of the experimental device for simulating aircraft contrail generation and evolution according to some embodiments of the present application.

[0028] Reference signs:

[0029] 1000, experimental device for simulating aircraft wake cloud generation and evolution;

[0030] 100, first gas supply system;

[0031] 110, mixer;

[0032] 121, third gas supply path; 122, fourth gas supply path; 123, fifth gas supply path;

[0033] 130, gas inlet tower; 140, second filter; 150, second screw air compressor;

[0034] 160, warmer; 170, second dryer; 180, second refrigerating machine;

[0035] 200, high-altitude simulation system;

[0036] 210, test cabin; 211, gas inlet cabin;

[0037] 220, thrust tester;

[0038] 230, gas inlet valve;

[0039] 300, wake cloud generation and evolution system;

[0040] 310, environment cabin;

[0041] 320, nozzle;

[0042] 330, dilution assembly;

[0043] 331, diluter;

[0044] 3311, dilution chamber; 3312, first gas inlet;

[0045] 3313, gas outlet; 3314, second gas inlet;

[0046] 332, gas supply element;

[0047] 400, second gas supply system;

[0048] 410, first refrigerating machine;

[0049] 421, first gas supply path; 422, second gas supply path;

[0050] 430, first filter; 440, first screw air compressor; 450, transition tank;

[0051] 460, exhaust valve; 470, first dryer;

[0052] 500, air extraction system;

[0053] 510, vacuum pump assembly; 511, first vacuum pump; 512, second vacuum pump;

[0054] 520, heat exchanger;

[0055] 530, cooler;

[0056] 600, on-off valve;

[0057] 700, electric regulating valve;

[0058] 810, temperature and pressure sensor; 820, temperature, humidity and pressure sensor; 830, temperature sensor;

[0059] 2000, aero-engine. DETAILED DESCRIPTION

[0060] Embodiments of the present application are described below in detail with reference to the accompanying drawings, in which the same or similar components or components having the same or similar functions are denoted by the same or similar reference numerals throughout. The embodiments described below by reference to the accompanying drawings are exemplary and are intended only to explain the present application, and should not be construed as limiting the present application.

[0061] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or components referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present application.

[0062] The experimental device 1000 for simulating the generation and evolution of aircraft wake clouds according to the embodiments of the present application is described below with reference to the accompanying drawings.

[0063] As shown in Figure 1 The experimental device 1000 for simulating the generation and evolution of aircraft wake clouds according to the embodiments of the present application includes a first gas supply system 100, a high-altitude simulation system 200, a wake cloud generation and evolution system 300, a second gas supply system 400, and a gas extraction system 500.

[0064] The high-altitude simulation system 200 includes a test cabin 210, and the aero-engine 2000 is arranged in the test cabin 210 (the specific schematic of the aero-engine 2000 can be found in Figure 2), the first gas supply system 100 is used for conveying low-temperature gas towards the aero-engine 2000, so that the aero-engine 2000 can be normally operated, and the running state of the aero-engine 2000 in high altitude is simulated, thereby facilitating the simulation of the generation and evolution of the wake cloud generated by the exhaust of the aero-engine 2000.

[0065] It should be noted that the first gas supply system 100 is used for conveying low-temperature gas towards the aero-engine 2000, mainly according to the simulated height condition of the aero-engine 2000, the gas with specific temperature and specific pressure is conveyed to the aero-engine 2000.

[0066] In some examples, the first gas supply system 100 is in communication with the aero-engine 2000 through a pipeline, so as to realize the conveying of the gas towards the aero-engine 2000 by the first gas supply system 100.

[0067] Meanwhile, in some examples, the test cabin 210 is provided with a mounting platform (not shown in the figure), and the aero-engine 2000 is mounted on the mounting platform, so as to realize the arrangement of the aero-engine 2000 in the test cabin 210.

[0068] In combination with FIGS. 1 and 2, Figure 1 and Figure 3 As shown in FIGS. 3 and 4, the wake cloud generation and evolution system 300 includes an environment cabin 310, a nozzle 320, and a dilution assembly 330, the dilution assembly 330 is used for receiving and diluting the exhaust of the aero-engine 2000, and conveying the diluted exhaust to the nozzle 320, and the nozzle 320 can spray the exhaust into the environment cabin 310. It can be understood here that the exhaust generated by the aero-engine 2000 can be transmitted into the dilution assembly 330, the dilution assembly 330 is used for receiving the exhaust of the aero-engine 2000 and diluting the received exhaust, after the dilution is completed, the dilution assembly 330 again conveys the diluted exhaust to the nozzle 320, and the nozzle 320 is used for receiving the diluted exhaust and spraying the exhaust into the environment cabin 310, so as to realize the simulation of the generation of the aircraft wake cloud and facilitate the subsequent simulation of the evolution of the wake cloud in the environment cabin 310.

[0069] In some examples, the aero-engine 2000, the dilution assembly 330, the nozzle 320, and the environment cabin 310 are in communication, so as to ensure that the exhaust of the aero-engine 2000 can enter the dilution assembly 330, and the exhaust in the dilution assembly 330 can enter the nozzle 320, and at the same time, it is ensured that the nozzle 320 can accurately spray the exhaust into the environment cabin 310.

[0070] The aforementioned connection can be achieved by connecting two components to each other through a pipeline, for example, connecting the aircraft engine 2000 and the dilution component 330 through a pipeline, and connecting the dilution component 330 and the nozzle 320 through a pipeline; or the connection can be achieved by setting the inlet and outlet of the two components facing each other, for example, setting the nozzle 320's nozzle outlet facing the inlet of the environmental chamber 310 to achieve connection between the nozzle 320 and the environmental chamber 310.

[0071] It should be noted that when high-temperature exhaust gas with a certain temperature and flow rate is introduced into the environmental chamber 310 through the dilution component 330 and the nozzle 320, the nozzle 320 can spray the exhaust plume of the real aircraft engine 2000 into the environmental chamber 310. This can more accurately simulate the real jetting state of the aircraft engine 2000 in high-altitude flight and simulate a more realistic contrail cloud growth and evolution pattern, thereby improving the simulation accuracy.

[0072] The second air supply system 400 is used to deliver low-temperature, high-humidity gas to the environmental chamber 310. This is to regulate the temperature and humidity inside the environmental chamber 310, making the environment inside the environmental chamber 310 close to the high-altitude environment, that is, to simulate the high-altitude environment inside the environmental chamber 310, thereby facilitating the subsequent simulation of the generation and evolution of aircraft contrails.

[0073] In some examples, the second gas supply system 400 is connected to the environmental chamber 310 via a pipeline to enable the delivery of gas from the second gas supply system 400 to the environmental chamber 310.

[0074] like Figure 1 As shown, the extraction system 500 is connected to the test chamber 210, the aircraft engine 2000 and the environmental chamber 310 respectively. The extraction system 500 is used to extract the gas in the test chamber 210, the aircraft engine 2000 and the environmental chamber 310. Specifically, when the exhaust system 500 extracts gas from the test chamber 210, some of the gas can be discharged to create a low-pressure environment within the test chamber 210, thereby simulating a high-altitude environment. This simulates the aircraft engine 2000 being in a high-altitude environment, improving the accuracy of the generation and evolution of simulated aircraft contrails. When the exhaust system 500 extracts gas from the aircraft engine 2000, some of the exhaust gas generated by the aircraft engine 2000 during operation can be discharged to ensure the aircraft engine 2000 can operate normally. When the exhaust system 500 extracts gas from the environmental chamber 310, some of the gas can be discharged to create a low-pressure environment within the environmental chamber 310, further making the environment within the environmental chamber 310 closer to a high-altitude environment, thus improving the accuracy of the generation and evolution of simulated aircraft contrails.

[0075] That is, the application forms a low-temperature, low-pressure and high-humidity environment in the environmental cabin 310 by setting the second gas supply system 400 and the gas extraction system 500, that is, makes the environmental parameters in the environmental cabin 310 meet the wake cloud generation condition, facilitates the simulation of the evolution of the persistent wake cloud, and improves the accuracy of the evolution.

[0076] In some examples, the gas extraction system 500 is in communication with the test cabin 210 and the environmental cabin 310 through pipelines, so as to extract the gas in the test cabin 210, the aero-engine 2000 and the environmental cabin 310 by using the gas extraction system 500.

[0077] Optionally, the pipeline is internally smooth and the roughness is controlled to be less than 3.2, so as to ensure the sealed connection between the systems and avoid the air leakage, thereby reducing the pressure loss along the pipeline.

[0078] As can be seen from the above structure, the experimental device 1000 for simulating the generation and evolution of the aircraft wake cloud of the embodiment of the application forms a low-pressure environment in the test cabin 210 by setting the test cabin 210 of the high-altitude simulation system 200 and the gas extraction system 500 for extracting the gas in the test cabin 210, so as to simulate the high-altitude fuselage environment of the aero-engine 2000, thereby facilitating the improvement of the accuracy of the subsequent simulation of the generation and evolution of the aircraft wake cloud.

[0079] By setting the wake cloud generation and evolution system 300 and connecting the dilution assembly 330 of the wake cloud generation and evolution system 300 with the aero-engine 2000, the exhaust gas generated by the aero-engine 2000 during operation can enter the dilution assembly 330, so as to dilute the exhaust gas in the dilution assembly 330 and spray the diluted exhaust gas through the nozzle 320, thereby facilitating the simulation of the generation and evolution of the aircraft wake cloud.

[0080] By setting the environmental cabin 310 in the wake cloud generation and evolution system 300 and setting the second gas supply system 400 and the gas extraction system 500 matched with the environmental cabin 310, a low-temperature, low-pressure and high-humidity environment is formed in the environmental cabin 310, so that when the exhaust gas diluted by the nozzle 320 is sprayed into the environmental cabin 310, the generation and evolution of the aircraft wake cloud can be simulated in the environmental cabin 310, thereby realizing the simulation of the generation and evolution of the aircraft wake cloud by using the experimental device 1000 for simulating the generation and evolution of the aircraft wake cloud of the application.

[0081] That is, the application can perform the whole machine and component simulation test on the aero-engine 2000 in the ground and high-altitude states, and can also realize the simulation of the generation and evolution process of the persistent wake cloud by simulating the real high-altitude cruising environment condition.

[0082] It can be understood that, compared with the prior art, the application can simulate the injection state of the aero-engine 2000 and simulate the high-altitude environment, so as to realize the generation and evolution of the simulated contrail cloud, facilitate the subsequent research on the contrail cloud, that is, facilitate the subsequent accurate formulation of the mitigation measures for the contrail cloud, and provide support for the research on the influence of aviation emissions on global climate.

[0083] Optionally, as shown in Figure 1 The test cabin 210 includes an air inlet cabin 211, which is in communication with the first gas supply system 100 and the aero-engine 2000. In this way, the first gas supply system 100 can deliver low-temperature gas into the air inlet cabin 211, and then the air inlet cabin 211 can deliver the low-temperature gas into the aero-engine 2000, so as to achieve the purpose of delivering low-temperature gas to the aero-engine 2000 by using the first gas supply system 100.

[0084] Optionally, as shown in Figure 2 The test cabin 210 is provided with a temperature and pressure sensor 810, which is used to monitor the temperature and pressure in the test cabin 210, so as to realize the real-time acquisition of the temperature and pressure in the test cabin 210, and facilitate the subsequent control of the temperature and pressure in the test cabin 210.

[0085] In some examples, an electric regulating valve 700 can be arranged on the first gas supply system 100 and between the air extraction system 500 and the test cabin 210. The electric regulating valve 700 is used to adjust the opening degree of the pipeline, so as to realize the adjustment of the temperature and pressure in the test cabin 210, so that the temperature and pressure in the test cabin 210 are within the required range.

[0086] In some specific examples, the electric regulating valve 700 can cooperate with the temperature and pressure sensor 810. When the temperature and / or pressure in the test cabin 210 detected by the temperature and pressure sensor 810 exceeds the required range of the test cabin 210, the electric regulating valve 700 is adjusted to ensure that the temperature and pressure in the test cabin 210 can always be maintained within the required range, so as to accurately simulate the high-altitude environment and improve the accuracy of the subsequent simulation of the generation and evolution of the contrail cloud.

[0087] Of course, in other examples, in combination with Figure 1 and Figure 5 A switch valve 600 can also be arranged on the first gas supply system 100 and between the air extraction system 500 and the test cabin 210. The switch valve 600 is used to control the on-off of the pipeline, so as to realize the control of whether the first gas supply system 100 supplies air to the test cabin 210 and whether the air extraction system 500 extracts the gas in the test cabin 210.

[0088] Optionally, as shown in Figure 1As shown, the air extraction system 500 is also provided with an on-off valve 600 for controlling the exhaust of the aero-engine 2000 to control whether the air extraction system 500 extracts the exhaust of the aero-engine 2000.

[0089] In some specific examples, the exhaust port of the test cabin 210 and the exhaust port of the aero-engine 2000 can be connected to the same pipeline at the same time, so that only one on-off valve 600 is needed to control whether the air extraction system 500 extracts the gas in the test cabin 210 and whether the air extraction system 500 extracts the exhaust of the aero-engine 2000, reducing the number of on-off valves 600.

[0090] It should be further emphasized that through the above arrangement, the exhaust of the aero-engine 2000 can be discharged into the air extraction system 500 and the wake cloud generation and evolution system 300 respectively, which not only facilitates the smooth discharge of the exhaust generated by the aero-engine 2000, but also facilitates the simulation of the generation and evolution of the wake cloud.

[0091] Optionally, as shown in Figure 3 The temperature, humidity and pressure sensor 820 is arranged on the environment cabin 310 and is used to monitor the temperature, humidity and pressure in the environment cabin 310, so as to obtain the temperature, humidity and pressure in the environment cabin 310 in real time and facilitate subsequent control of the temperature, humidity and pressure in the environment cabin 310.

[0092] Optionally, as shown in Figure 1 The on-off valve 600 is used to control the opening and closing of the pipeline, and the electric regulating valve 700 is used to control the opening of the pipeline, so that whether the second gas supply system 400 supplies gas to the environment cabin 310, whether the air extraction system 500 extracts the gas in the environment cabin 310, and the amount of gas supplied by the second gas supply system 400 to the environment cabin 310 and the amount of gas extracted by the air extraction system 500 from the environment cabin 310 can be controlled, so as to adjust the temperature, humidity and pressure in the environment cabin 310, so that the temperature, humidity and pressure in the environment cabin 310 are within the required range, that is, the environment in the environment cabin 310 approaches the high-altitude environment.

[0093] In some specific examples, the electric regulating valve 700 between the second gas supply system 400 and the environment cabin 310 and the electric regulating valve 700 between the environment cabin 310 and the air extraction system 500 are matched with the temperature, humidity and pressure sensor 820, when the temperature, humidity and pressure sensor 820 detects that the temperature, humidity and pressure in the environment cabin 310 exceed the required range of the environment cabin 310, the electric regulating valve 700 is adjusted to ensure that the temperature, humidity and pressure in the environment cabin 310 can always be maintained within the required range, to simulate the high-altitude environment, and improve the accuracy of subsequent simulation of the generation and evolution of the contrail cloud.

[0094] In some examples, when the air extraction system 500 extracts the gas in the environment cabin 310, the electric regulating valve 700 and the temperature, humidity and pressure sensor 820 are matched to ensure that the low pressure and low temperature in the environment cabin 310 remain stable, and the fluctuation range does not exceed 5%, and the pressure range in the environment cabin 310 is maintained between 0.036 MPa and 0.019 MPa, the pressure of 0.036 MPa and the pressure of 0.019 MPa respectively correspond to the atmospheric environment pressure of 8000 meters altitude and 12000 meters altitude, so that the environment in the environment cabin 310 can accurately simulate the high-altitude environment.

[0095] In addition, the gas temperature in the environment cabin 310 needs to be stabilized between 228.1 K and 236.2 K, and the humidity should not be less than 95%, so that the environment in the environment cabin 310 can be more close to the actual situation of high altitude, to realize the simulation of high-altitude environment.

[0096] In summary, the second gas supply system 400 and the air extraction system 500 are matched to control the temperature, humidity and pressure in the environment cabin 310, so that the temperature, humidity and pressure in the environment cabin 310 remain uniform and controllable, that is, the second gas supply system 400 and the air extraction system 500 can realize the manufacture of high-altitude low-pressure low-temperature high-humidity environment, and further improve the simulation accuracy of the contrail cloud in the environment cabin 310. At the same time, the electric regulating valve 700 and the temperature, humidity and pressure sensor 820 are matched to balance the suction state of the air extraction system 500, and finally the low pressure of the environment cabin 310 remains unchanged.

[0097] In some examples, the environment cabin 310 is formed as a visualization environment cabin, which can facilitate real-time observation of the generation and evolution process of the contrail cloud.

[0098] In some embodiments of the present application, in combination with Figure 1 , Figure 2 and Figure 3 as shown, the dilution assembly 330 includes a diluter 331, which communicates with the aero-engine 2000, and the diluter 331 is used to receive and dilute the exhaust gas of the aero-engine 2000. Thus, it is convenient for subsequent simulation of the generation and evolution process of the contrail cloud.

[0099] Here, it can also be understood that the dilution of the aero-engine 2000 exhaust is mainly realized by the diluter 331.

[0100] Optionally, as shown in the figure, the dilution assembly 330 further comprises a gas supply element 332, which is in communication with the diluter 331, and is used to transport dilution gas towards the diluter 331, so as to achieve the purpose of diluting the aero-engine 2000 exhaust with dilution gas, thereby facilitating the subsequent simulation of the generation and evolution of the plume cloud. Figure 3 That is, the diluter 331 of the present application is in communication with the aero-engine 2000 and the gas supply element 332 at the same time, so that the exhaust generated by the aero-engine 2000 and the dilution gas in the gas supply element 332 can all enter the diluter 331. When the exhaust and the dilution gas enter the diluter 331 at the same time, the exhaust and the dilution gas are mixed in the diluter 331, so as to achieve the purpose of diluting the exhaust of the aero-engine 2000 with dilution gas, and help simulate the rotating plume of different exhaust amounts, thereby facilitating the simulation of the generation and evolution of the plume cloud.

[0101] Here, the dilution of the diluter 331 can evaluate the size of the exhaust amount.

[0102] In some examples, the gas supply element 332 is a gas tank, which is used to store dilution gas, so as to dilute the exhaust of the aero-engine 2000 with dilution gas. Here, the dilution gas can be nitrogen.

[0103] Optionally, as shown in the figure, the diluter 331 comprises a dilution cavity 3311, a first gas inlet 3312 and a gas outlet 3313, the first gas inlet 3312 and the gas outlet 3313 are arranged at the axial ends of the dilution cavity 3311, the first gas inlet 3312 and the gas outlet 3313 are in communication with the dilution cavity 3311, the exhaust of the aero-engine 2000 enters the dilution cavity 3311 through the first gas inlet 3312, and the gas outlet 3313 is used to discharge the gas in the dilution cavity 3311. Here, it can be understood that the first gas inlet 3312 is used to ensure that the diluter 331 can smoothly receive the exhaust of the aero-engine 2000, so as to facilitate the dilution of the exhaust of the aero-engine 2000 with the diluter 331, and the gas outlet 3313 is used to discharge the gas in the dilution cavity 3311, thereby facilitating the subsequent simulation of the generation and evolution of the plume cloud.

[0104] Figure 3 In some examples, the gas outlet 3313 is in communication with the nozzle 320, so as to transport the gas diluted by the diluter 331 into the nozzle 320.

[0105] In some examples, the gas outlet 3313 is in communication with the nozzle 320, so as to transport the gas diluted by the diluter 331 into the nozzle 320.

[0106] ​Optionally, the exhaust volume of the environment cabin 310 should be close to the total exhaust volume of the diluter 331, and the fluctuation range thereof should not exceed 5%, so that the low pressure and low temperature in the environment cabin 310 are stable.

[0107] Optionally, as shown in Figure 3 the diluter 331 also includes a second air inlet 3314, the second air inlet 3314 is arranged circumferentially on the diluter 331, the second air inlet 3314 is in communication with the dilution cavity 3311, and the gas supply element 332 delivers dilution gas to the dilution cavity 3311 through the second air inlet 3314. The purpose of delivering dilution gas to the dilution cavity 3311 by the gas supply element 332 is to facilitate the dilution of the exhaust gas of the aero-engine 2000 entering the dilution cavity 3311.

[0108] That is, the diluter 331 of the present application is respectively provided with a first air inlet 3312 and a second air inlet 3314, the first air inlet 3312 is used to ensure that the exhaust gas generated by the aero-engine 2000 can smoothly enter the dilution cavity 3311, and the second air inlet 3314 is used to ensure that the dilution gas in the gas supply element 332 can smoothly enter the dilution cavity 3311, so as to facilitate the dilution of the exhaust gas of the aero-engine 2000 entering the dilution cavity 3311, thereby facilitating the subsequent simulation of the generation and evolution of the wake cloud.

[0109] Optionally, as shown in Figure 3 the second air inlet 3314 includes a plurality of second air inlets 3314, the plurality of second air inlets 3314 are arranged at intervals along the radial direction of the diluter 331, and the second air inlets 3314 extend obliquely from the outside to the inside along the radial direction of the diluter 331 towards the direction close to the air outlet 3313. The plurality of second air inlets 3314 can increase the amount of dilution gas entering the dilution cavity 3311, thereby achieving the dilution of the exhaust gas of the aero-engine 2000 by the dilution gas. In addition, by arranging the second air inlets 3314 to extend obliquely from the outside to the inside along the radial direction of the diluter 331 towards the direction close to the air outlet 3313, when the dilution gas is introduced into the dilution cavity 3311 through the second air inlets 3314, the rotational flow of the dilution gas can be achieved, thereby ensuring that the diluted exhaust gas can be rotated when being discharged from the air outlet 3313.

[0110] It can also be understood that the high-temperature exhaust gas with a certain temperature and flow rate can be introduced into the environment cabin 310 through the nozzle 320 in a rotating plume mode after passing through the diluter 331, which can more accurately simulate the real injection state of the aero-engine 2000 in high-altitude flight and simulate more realistic wake cloud growth and evolution patterns, thereby facilitating the simulation of the thermal-fluid-structure coupling process of carbon smoke and the simulation of the wake cloud icing and evolution process.

[0111] In some embodiments of the present application, as shown in Figure 4As shown, the second air supply system 400 comprises a first refrigerating machine 410, a first air supply path 421 and a second air supply path 422, the first air supply path 421 and the second air supply path 422 are arranged in parallel, the first air supply path 421 is used for transporting low-humidity air to the first refrigerating machine 410, the second air supply path 422 is used for transporting high-humidity air to the first refrigerating machine 410, the first refrigerating machine 410 mixes and lowers the temperature of the received air, and the first refrigerating machine 410 is used for transporting low-temperature air to the environment cabin 310. That is, the air transported by the first air supply path 421 and the second air supply path 422 has different humidity, so when the air is transported into the environment cabin 310 by the cooperation of the first air supply path 421 and the second air supply path 422, the humidity of the air can be effectively adjusted to achieve the purpose of transporting high-humidity air to the environment cabin 310 by the second air supply system 400, and the air mixed by the first air supply path 421 and the second air supply path 422 is cooled by the first refrigerating machine 410 to achieve the purpose of cooling the air, so that low-temperature high-humidity air can be transported to the environment cabin 310, thereby realizing the transportation of low-temperature high-humidity air to the environment cabin 310 by the second air supply system 400, and facilitating the simulation of high-altitude environment in the environment cabin 310.

[0112] In some examples, as Figure 4 shown, the first air supply path 421 is provided with a first drying machine 470 and has a low dew point, and the second air supply path 422 is provided with a first drying machine 470 and has a higher dew point, and the first drying machine 470 dries the air flowing therethrough to adjust the humidity of the air, thereby controlling the first air supply path 421 to transport low-humidity air to the first refrigerating machine 410 and controlling the second air supply path 422 to transport high-humidity air to the first refrigerating machine 410.

[0113] It should be noted that the first drying machine 470 needs to meet the drying requirements of the corresponding flow of air of the aero-engine 2000 under various conditions at various altitudes, and the maximum drying capacity of the first drying machine 470 needs to be able to make the minimum relative humidity of the inlet air continuously less than 30%.

[0114] Optionally, as Figure 4 shown, the first air supply path 421 and the second air supply path 422 are each provided with a temperature, humidity and pressure sensor 820, the temperature, humidity and pressure sensor 820 on the first air supply path 421 is used to detect the temperature, humidity and pressure of the air in the first air supply path 421, and the temperature, humidity and pressure sensor 820 on the second air supply path 422 is used to detect the temperature, humidity and pressure of the air in the second air supply path 422, thereby facilitating subsequent control of the temperature, humidity and pressure of the air flowing through the first air supply path 421 and the second air supply path 422.

[0115] Optionally, as Figure 4As shown, the first air supply path 421 and the second air supply path 422 are further provided with electric regulating valves 700, which are used to adjust the opening degree of the first air supply path 421 and the second air supply path 422, so as to adjust the temperature, humidity and pressure of the gas flowing through the first air supply path 421 and the second air supply path 422, so that the temperature, humidity and pressure in the environmental cabin 310 are within the required range.

[0116] In some specific examples, the electric regulating valve 700 on the first air supply path 421 cooperates with the temperature, humidity and pressure sensor 820 on the first air supply path 421, and the electric regulating valve 700 on the second air supply path 422 cooperates with the temperature, humidity and pressure sensor 820 on the second air supply path 422, so that when the temperature, humidity or pressure of the gas flowing through the temperature, humidity and pressure sensor 820 is detected to be out of the preset range, the electric regulating valve 700 can be used for adjustment, so as to ensure that the temperature, humidity and pressure of the gas flowing through the first air supply path 421 and the second air supply path 422 are within the preset range, thereby ensuring that the temperature, humidity and pressure of the gas entering the environmental cabin 310 are within the required range, so as to simulate the high-altitude environment in the environmental cabin 310 and improve the accuracy of subsequent simulation of the contrail cloud.

[0117] It should be further noted that the mixed gas of the first air supply path 421 and the second air supply path 422 needs to meet the humidity requirements of the corresponding flow of air of the aero-engine 2000 under various conditions at various altitudes, and the maximum humidity capability requirement needs to be able to make the highest relative humidity of the intake air not less than 99%, and the humidity requirement of the split gas needs to reach the relative humidity (30%~98%) at different flight altitudes.

[0118] Optionally, as shown, Figure 4 The second air supply system 400 further includes a first filter 430, a first screw air compressor 440 and a transition tank 450, which are arranged in sequence along the flow direction of the gas, and the first filter 430 is in communication with the external air and the first screw air compressor 440, so that the first filter 430 can lead the external fresh air out of the first screw air compressor 440 and filter out the impurities in the external fresh air during the introduction process, thereby improving the cleanliness of the introduced air, and the first screw air compressor 440 is in communication with the transition tank 450, so as to realize the transmission of the received gas into the transition tank 450.

[0119] Among them, the first screw air compressor 440 is used to compress air, so as to improve the amount of gas entering the transition tank 450 subsequently, and the transition tank 450 is used to store gas and plays a role of pressure stabilization, so as to improve the stability of the subsequent gas flow.

[0120] Optionally, the gas storage capacity of the transition tank 450 is greater than or equal to 1-2 times the total capacity of the environmental cabin 310, to ensure that a sufficient amount of gas can be subsequently delivered to the environmental cabin 310.

[0121] In some examples, the first filter 430 and the first screw air compressor 440, and the first screw air compressor 440 and the transition tank 450 are in communication through pipelines, to ensure that the gas can flow normally.

[0122] Optionally, as shown in Figure 4 , the transition tank 450 is in communication with the first gas supply path 421 and the second gas supply path 422, so that the gas stored in the transition tank 450 can be smoothly delivered to the first gas supply path 421 and the second gas supply path 422, to facilitate subsequent adjustment of the humidity of the gas by the first gas supply path 421 and the second gas supply path 422, and adjustment of the temperature of the gas by the first refrigeration machine 410, to achieve delivery of low-temperature and high-humidity gas to the environmental cabin 310.

[0123] Optionally, as shown in Figure 4 , a switch valve 600 is arranged between the transition tank 450 and the first gas supply path 421 and the second gas supply path 422, and the switch valve 600 is used to control the opening and closing of the pipeline between the transition tank 450 and the first gas supply path 421 and the second gas supply path 422, to facilitate control of the flow of gas.

[0124] Optionally, in combination with Figure 1 and Figure 4 , a temperature and pressure sensor 810 is arranged between the transition tank 450 and the first gas supply path 421 and the second gas supply path 422, and a temperature, humidity, and pressure sensor 820 is arranged downstream of the first refrigeration machine 410, where the temperature and pressure sensor 810 is used to detect the temperature and pressure of the gas about to enter the first gas supply path 421 and the second gas supply path 422, and the temperature, humidity, and pressure sensor 820 is used to detect the temperature, humidity, and pressure of the gas cooled by the first refrigeration machine 410, to facilitate adjustment of the temperature, humidity, and pressure of the gas entering the second gas supply system 400.

[0125] Here, the downstream can be understood as, in the process of gas flow, the gas first flows through the first refrigeration machine 410, and then flows to the temperature, humidity, and pressure sensor 820.

[0126] In some examples, as shown in Figure 4As shown, an exhaust valve 460 is also provided between the transition tank 450 and the first gas supply line 421 and the second gas supply line 422. The exhaust valve 460 is used to discharge part of the gas that is about to enter the first gas supply line 421 and the second gas supply line 422, so as to avoid damage to the first gas supply line 421 and the second gas supply line 422 and the pipeline between the transition tank 450 and the first gas supply line 421 and the second gas supply line 422 due to excessive gas flow and pressure, thereby extending the service life of the second gas supply system 400.

[0127] In some specific examples, the exhaust valve 460 can cooperate with the temperature and pressure sensor 810 between the transition tank 450 and the first gas supply line 421 and the second gas supply line 422. When the temperature and pressure sensor 810 detects that the gas pressure flowing through it is too high, the exhaust valve 460 is activated and some gas is discharged to reduce the gas pressure.

[0128] Specifically, when the second air supply system 400 of this application is working, fresh external air first enters the first screw air compressor 440 through the first filter 430. The first screw air compressor 440 compresses the gas entering it and delivers the compressed gas to the transition tank 450. The transition tank 450 is used to buffer the gas flow to stabilize the gas pressure. Then, the gas is simultaneously transmitted to the first air supply path 421 and the second air supply path 422. The first air supply path 421 and the second air supply path 422 are used to adjust the humidity of the gas flowing through them respectively, and deliver the adjusted gas to the first refrigerator 410. In the first refrigerator 410, the two gases from the first air supply path 421 and the second air supply path 422 are mixed, and the first refrigerator 410 is used to cool the mixed gas. After cooling, the first refrigerator 410 transmits the low-temperature, high-humidity gas into the intermediate environment chamber 310, so as to achieve the purpose of using the second air supply system 400 to deliver low-temperature, high-humidity gas to the environment chamber 310.

[0129] In some embodiments of the present invention, such as Figure 5 As shown, the first gas supply system 100 includes a mixer 110, a third gas supply path 121, a fourth gas supply path 122, and a fifth gas supply path 123. The third, fourth, and fifth gas supply paths 121, 122, and 123 are all connected to the mixer 110. Thus, the gas in the third, fourth, and fifth gas supply paths 121, 122, and 123 can all enter the mixer 110. The mixer 110 is used to mix at least two gas supply paths to change the temperature of the gas entering the mixer 110, facilitating the subsequent delivery of cryogenic gas to the aircraft engine 2000.

[0130] In the description of this invention, features defined with "first", "second", "third", "fourth" and "fifth" may explicitly or implicitly include one or more of these features, used to distinguish and describe features, without any order or importance.

[0131] Optionally, the third gas supply path 121 is configured to supply normal-temperature gas to the mixer 110, the fourth gas supply path 122 is configured to supply high-temperature gas to the mixer 110, and the fifth gas supply path 123 is configured to supply low-temperature gas to the mixer 110. The mixer 110 mixes the gases and supplies the gases to the aero-engine 2000. That is, the gases supplied by the third gas supply path 121, the fourth gas supply path 122, and the fifth gas supply path 123 are at different temperatures. By providing the fifth gas supply path 123 for supplying low-temperature gas, the low-temperature gas can be supplied to the aero-engine 2000 by the fifth gas supply path 123, that is, the purpose of supplying low-temperature gas to the aero-engine 2000 by the first gas supply system 100 is achieved.

[0132] In addition, by providing the third gas supply path 121 for supplying normal-temperature gas and the fourth gas supply path 122 for supplying high-temperature gas, the temperature of the gases in the mixer 110 can be adjusted so that the temperature of the gases entering the aero-engine 2000 meets the required temperature requirement of the aero-engine 2000, thereby facilitating the high-altitude simulation of the environment in which the aero-engine 2000 is located. Meanwhile, the third gas supply path 121, the fourth gas supply path 122, and the fifth gas supply path 123 cooperate to improve the efficiency of temperature adjustment.

[0133] Optionally, in combination with the temperature and pressure sensor 810 shown in Figure 1 and Figure 5 Optionally, the mixer 110 is provided downstream of the temperature and pressure sensor 810, which is configured to detect the temperature and pressure of the gases flowing therethrough, thereby facilitating subsequent adjustment of the gas supply temperature of the first gas supply system 100.

[0134] In some examples, when the temperature and pressure sensor 810 downstream of the mixer 110 detects that the temperature of the gases flowing therethrough is low, the temperature of the gases in the mixer 110 can be increased by starting the third gas supply path 121 for supplying normal-temperature gas or starting the fourth gas supply path 122 for supplying high-temperature gas. Correspondingly, when the temperature and pressure sensor 810 downstream of the mixer 110 detects that the temperature of the gases flowing therethrough is high, the temperature of the gases in the mixer 110 can be reduced by starting the third gas supply path 121 for supplying normal-temperature gas or starting the fifth gas supply path 123 for supplying low-temperature gas, thereby reducing the difficulty of adjusting the temperature of the gases and improving the efficiency of adjustment.

[0135] Optionally, the total temperature requirement after the mixer 110 is to reach the environmental temperature (236.2K-300K) at different flight altitudes.

[0136] Optionally, as shown in Figure 5As shown, the third gas supply path 121 is provided with an air inlet tower 130, a second filter 140, a switch valve 600 and an electric regulating valve 700 arranged in sequence along the flow direction of the gas, wherein the air inlet tower 130 is used to introduce the external normal-temperature gas into the third gas supply path 121, and when the external normal-temperature gas flows along the extension direction of the third gas supply path 121, the normal-temperature gas first flows to the second filter 140, and the second filter 140 is used to filter the impurities in the gas to ensure the cleanliness of the gas.

[0137] Optionally, the second filter 140 meets the flow and filtration requirements of the aero-engine 2000 under various conditions at various altitudes.

[0138] Optionally, the switch valve 600 on the third gas supply path 121 is used to control the on-off of the third gas supply path 121 to control whether the normal-temperature air is introduced into the mixer 110, and the electric regulating valve 700 on the third gas supply path 121 is used to adjust the opening of the third gas supply path 121 to achieve the adjustment of the amount of normal-temperature air introduced into the mixer 110.

[0139] In a specific example, when it is needed to transport the normal-temperature gas towards the mixer 110, the air inlet tower 130 is first started to introduce the external normal-temperature gas into the third gas supply path 121, and then the gas flows through the second filter 140, the switch valve 600 and the electric regulating valve 700 in sequence to enter the mixer 110.

[0140] Optionally, as shown, Figure 5 As shown, the fourth gas supply path 122 is provided with an air inlet tower 130, a second filter 140, a second screw air compressor 150, a warming machine 160, an electric regulating valve 700, a temperature and pressure sensor 810 and a switch valve 600 arranged in sequence along the flow direction of the gas, wherein the air inlet tower 130 is used to introduce the external normal-temperature gas into the fourth gas supply path 122, and when the external normal-temperature gas flows along the extension direction of the fourth gas supply path 122, the normal-temperature gas first flows to the second filter 140, and the second filter 140 is used to filter the impurities in the gas to ensure the cleanliness of the gas, and then flows through the second screw air compressor 150, the warming machine 160, the electric regulating valve 700, the temperature and pressure sensor 810 and the switch valve 600 in sequence.

[0141] The second screw air compressor 150 on the fourth air supply path 122 is used to compress the gas flowing therethrough to ensure the amount of gas; the warmer 160 is used to warm the air to increase the temperature of the gas to ensure that the fourth air supply path 122 can deliver high-temperature gas; the electric regulating valve 700 is used to adjust the opening of the fourth air supply path 122 to achieve the adjustment of the amount of air introduced into the mixer 110; the temperature and pressure sensor 810 is used to detect the gas flowing therethrough, which is convenient for subsequent adjustment of the opening of the electric regulating valve 700 and feedback control of the warmer 160 according to the detection result, to ensure that the intake air has the required temperature and pressure after passing through the mixer 110; and the on-off valve 600 is used to control the on-off of the fourth air supply path 122 to control whether high-temperature air is introduced into the mixer 110.

[0142] Optionally, the warmer 160 needs to meet the temperature requirements of the corresponding flow of air of the aero-engine 2000 under various conditions at various altitudes, and the maximum heating capacity requirement is to make the highest temperature of the intake air not less than 300K.

[0143] In a specific example, when it is necessary to deliver high-temperature gas to the mixer 110, first start the intake tower 130 on the fourth air supply path 122, which introduces external normal-temperature gas into the fourth air supply path 122, and then the gas flows through the second filter 140, the second screw air compressor 150, the warmer 160, the electric regulating valve 700, the temperature and pressure sensor 810, and the on-off valve 600 in sequence to deliver high-temperature gas to the mixer 110, thereby increasing the temperature of the mixed air in the mixer 110.

[0144] Optionally, as shown in Figure 5 , a on-off valve 600 is also arranged between the second filter 140 and the second screw air compressor 150 on the fourth air supply path 122 to further control the on-off of the fourth air supply path 122.

[0145] Optionally, as shown in Figure 5 , the fifth air supply path 123 is provided with an intake tower 130, a second dryer 170, a second filter 140, a second screw air compressor 150, a second refrigeration machine 180, an electric regulating valve 700, a temperature and pressure sensor 810, and an on-off valve 600 arranged in sequence and communicated along the flow direction of the gas, wherein the intake tower 130 is used to introduce external normal-temperature gas into the fifth air supply path 123, and when the external normal-temperature gas flows in the extension direction of the fifth air supply path 123, the normal-temperature gas first flows to the second dryer 170, which is used to remove the moisture in the gas to achieve the purpose of drying the gas, and then the gas flows through the second filter 140, the second screw air compressor 150, the second refrigeration machine 180, the electric regulating valve 700, the temperature and pressure sensor 810, and the on-off valve 600 in sequence.

[0146] The second filter 140 on the fifth air supply path 123 is also used to filter impurities in the gas to ensure the cleanliness of the gas; the second screw air compressor 150 is used to compress the gas flowing therethrough to ensure the amount of the gas; the second refrigerating machine 180 is used to reduce the temperature of the air to ensure that the fifth air supply path 123 can deliver low-temperature gas; the electric regulating valve 700 is used to adjust the opening of the fifth air supply path 123 to achieve the adjustment of the amount of air introduced into the mixer 110; the temperature and pressure sensor 810 is used to detect the gas flowing therethrough, so as to facilitate subsequent adjustment of the opening of the electric regulating valve 700 and feedback control of the second refrigerating machine 180 according to the detection result, so as to ensure that the intake air has the required temperature and pressure after passing through the mixer 110; and the on-off valve 600 is used to control the on-off of the fifth air supply path 123 to control whether the low-temperature air is introduced into the mixer 110.

[0147] In some examples, the second drying machine 170 can remove 99% of the moisture in the gas, preventing the moisture in the air on the fifth air supply path 123 from condensing into water droplets in the second screw air compressor 150 and condensing into ice crystals in the second refrigerating machine 180, thereby ensuring that the second screw air compressor 150 and the second refrigerating machine 180 can operate normally.

[0148] Optionally, the second refrigerating machine 180 meets the condensation requirements of the corresponding flow of air of the aero-engine 2000 under various conditions at various altitudes, and the maximum condensation capacity requirement can make the minimum temperature of the intake air continuously below 230K.

[0149] In specific examples, when it is necessary to deliver low-temperature gas to the mixer 110, the intake tower 130 on the fifth air supply path 123 is first started, the intake tower 130 introduces external normal-temperature gas into the fifth air supply path 123, and then the gas sequentially flows through the second drying machine 170, the second filter 140, the second screw air compressor 150, the second refrigerating machine 180, the electric regulating valve 700, the temperature and pressure sensor 810, and the on-off valve 600 to realize the delivery of low-temperature gas to the mixer 110, thereby reducing the temperature of the mixed air in the mixer 110.

[0150] Optionally, as shown in Figure 5 , the second filter 140 and the second screw air compressor 150 on the fifth air supply path 123 are also provided with an on-off valve 600 to further control the on-off of the second refrigerating machine 180.

[0151] In some embodiments of the present application, as shown in Figure 2 , the high-altitude simulation system 200 further comprises a thrust tester 220 and an intake valve 230, the thrust tester 220 is arranged in the test cabin 210 and is used to measure the thrust of the aero-engine 2000. It is convenient for subsequent detection of whether the thrust parameters of the aero-engine 2000 are normal during the experiment.

[0152] In some examples, the measurement range of the thrust tester 220 should be within the dynamometer range, and the measurement error of the thrust tester 220 should be less than 0.5%.

[0153] Optionally, as shown in Figure 2 The intake valve 230 is in communication with the test cabin 210 for air intake towards the test cabin 210. This ensures that there is always a certain amount of gas in the test cabin 210, avoiding a vacuum state in the test cabin 210 after the air extraction system 500 extracts the gas in the test cabin 210.

[0154] In some examples, the intake valve 230 is in communication with the external air for introducing the external air into the test cabin 210.

[0155] In some embodiments of the present application, as shown in Figure 1 The air extraction system 500 includes a vacuum pump assembly 510 in communication with the test cabin 210, the aero-engine 2000 and the environment cabin 310, respectively, and the vacuum pump assembly 510 includes a first vacuum pump 511 and a second vacuum pump 512 connected in parallel. It can be understood that the air extraction system 500 extracts the gas in the test cabin 210, the aero-engine 2000 and the environment cabin 310 mainly through the vacuum pump assembly 510, thereby ensuring that the gas in the first gas supply system 100, the test cabin 210, the environment cabin 310 and the second gas supply system 400 can be smoothly discharged, and a low-pressure environment can be formed in the test cabin 210 and the environment cabin 310.

[0156] In addition, the present application provides that the vacuum pump assembly 510 is connected in parallel by the first vacuum pump 511 and the second vacuum pump 512, so that the first vacuum pump 511 and the second vacuum pump 512 can be used to adjust and compensate the pressure of the air extraction system 500, and the air extraction capacity of the air extraction system 500 can be improved, so that the gas in the test cabin 210 and the environment cabin 310 can be smoothly extracted, thereby facilitating the formation of a high-altitude low-pressure environment in the test cabin 210 and the environment cabin 310.

[0157] In some specific examples, the vacuum suction capacity of the vacuum pump assembly 510 should meet the pressure requirements of the test cabin 210 and the environment cabin 310.

[0158] Optionally, the air extraction system 500 is also provided with an on-off valve 600 and an electric regulating valve 700 (not shown in the example of the electric regulating valve 700), wherein the on-off valve 600 and the electric regulating valve 700 cooperate to balance the suction state of the vacuum pump assembly 510, so that the low pressure of the test cabin 210 and the environment cabin 310 is maintained unchanged, that is, a stable low pressure can be formed in the test cabin 210 and the environment cabin 310.

[0159] In summary, the application establishes a high-efficiency operation mechanism of the second air supply system 400 and the air extraction system 500, improves the temperature, humidity and pressure control accuracy of the environment cabin 310 in the wake vortex cloud generation and evolution system 300, reduces the interference of the high-temperature rotating jet plume to the atmospheric environment in the environment cabin 310, so that the temperature, humidity and pressure in the environment cabin 310 are closer to the real high-altitude wake vortex cloud environment.

[0160] Optionally, as shown in Figure 1 The air extraction system 500 further comprises a heat exchanger 520 arranged between the vacuum pump assembly 510 and the environment cabin 310, and the heat exchanger 520 is used to increase the temperature of the gas entering the vacuum pump assembly 510. In order to avoid the low-temperature gas entering the vacuum pump assembly 510 causing damage to the vacuum pump assembly 510, and prolong the service life of the vacuum pump assembly 510.

[0161] Specifically, the exhaust temperature of the environment cabin 310 is too low. At this time, if the exhaust of the environment cabin 310 is directly introduced into the vacuum pump assembly 510, it will cause damage to the vacuum pump assembly 510. Therefore, the application first introduces the exhaust of the environment cabin 310 to the heat exchanger 520 to increase the temperature of the exhaust, and then enters the vacuum pump assembly 510 after being heated, so as to protect the vacuum pump assembly 510.

[0162] In some examples, the heat exchanger 520 should be able to increase the exhaust temperature entering the vacuum pump assembly 510 to above 25°C under any working condition flow.

[0163] Optionally, as shown in Figure 1 The air extraction system 500 further comprises a cooler 530 arranged between the vacuum pump assembly 510 and the aero-engine 2000, and the cooler 530 is used to reduce the temperature of the gas entering the vacuum pump assembly 510. In order to avoid the high-temperature gas entering the vacuum pump assembly 510 causing damage to the vacuum pump assembly 510, and further prolong the service life of the vacuum pump assembly 510.

[0164] Specifically, the exhaust temperature of the aero-engine 2000 is too high. At this time, if the exhaust of the aero-engine 2000 is directly introduced into the vacuum pump assembly 510, it will cause damage to the vacuum pump assembly 510. Therefore, the application first introduces the exhaust of the aero-engine 2000 to the cooler 530 to reduce the temperature of the exhaust, and then enters the vacuum pump assembly 510 after being cooled, so as to protect the vacuum pump assembly 510.

[0165] In some examples, the cooler 530 should be able to reduce the exhaust temperature entering the vacuum pump assembly 510 to below 150°C under any working condition flow.

[0166] Optionally, as shown in Figure 1As shown, the temperature sensor 830 is arranged upstream of the vacuum pump assembly 510, and is configured to detect the temperature of the gas to be drawn into the vacuum pump assembly 510, so as to facilitate subsequent control of whether to draw the gas by the vacuum pump assembly 510.

[0167] Optionally, as shown, the vacuum pump assembly 510 and the temperature sensor 830 are provided with a switch valve 600, which is configured to control the opening and closing of the pipeline between the vacuum pump assembly 510 and the temperature sensor 830, so as to achieve control of whether to draw the gas by the vacuum pump assembly 510. Figure 1

[0168] In some examples, the temperature sensor 830 cooperates with the switch valve 600, and when the temperature sensor 830 detects that the temperature of the gas flowing therethrough is too high or too low, the switch valve 600 closes the pipeline, so as to avoid abnormal temperature entering the vacuum pump assembly 510, thereby protecting the vacuum pump assembly 510 and prolonging the service life of the vacuum pump assembly 510.

[0169] The experimental method of the experimental device 1000 for simulating the generation and evolution of aircraft wake clouds according to the embodiments of the present application is described below with reference to the accompanying drawings.

[0170] As shown, the experimental method of the experimental device 1000 for simulating the generation and evolution of aircraft wake clouds according to the embodiments of the present application comprises the following steps: Figure 6 S1, arranging the aero-engine 2000 in the test cabin 210.

[0171] S2, starting the aero-engine 2000 under ground intake conditions, and determining whether the aero-engine 2000 is normal, if normal, executing the next step; if not normal, troubleshooting.

[0172] S3, starting the experimental device 1000 for simulating the generation and evolution of aircraft wake clouds, and using the wake cloud generation and evolution system 300 to simulate the generation and evolution of the exhaust of the aero-engine 2000.

[0173] From the above method, it can be seen that the experimental method of the experimental device 1000 for simulating the generation and evolution of aircraft wake clouds according to the embodiments of the present application, after determining that the aero-engine 2000 is normal and starting the experimental device 1000 for simulating the generation and evolution of aircraft wake clouds, uses the wake cloud generation and evolution system 300 to simulate the generation and evolution of the exhaust of the aero-engine 2000, so as to facilitate real-time observation of the changes of the wake cloud, thereby facilitating subsequent research on the wake cloud, that is, facilitating subsequent development of measures to alleviate the wake cloud, and providing support for research on the influence of aviation emissions on global climate.

[0174]

[0175] ​​Optionally, after the aero-engine 2000 is arranged in the test cabin 210, the thrust tester 220 can be connected first, so that the thrust parameter of the aero-engine 2000 can be judged according to the test result of the thrust tester 220, and preparation for starting the experimental device 1000 for simulating the generation and evolution of the aircraft wake cloud can be made.

[0176] Optionally, when the aero-engine 2000 is started under the ground air intake condition and whether the aero-engine 2000 is normal is judged, the aero-engine 2000 can be operated to the rotating speed and load condition to be measured, and the performance indexes and parameters of the aero-engine 2000 under the ground state are observed, including the power (thrust), fuel consumption rate, cooling liquid temperature, lubricating oil pressure and temperature, exhaust temperature and the like, so that the aero-engine 2000 is ensured to be normal.

[0177] Optionally, when the aero-engine 2000 is judged to be abnormal and the fault is excluded, the aero-engine 2000 can be started again under the ground air intake condition, and whether the aero-engine 2000 is normal is judged, until the exhaust of the aero-engine 2000 can be experimented.

[0178] It should be noted that the experimental device 1000 for simulating the generation and evolution of the aircraft wake cloud is mainly started to start the first air supply system 100, the second air supply system 400 and the air extraction system 500, so that the low-temperature and low-pressure environment in the test cabin 210 and the low-temperature, low-pressure and high-humidity environment in the environmental cabin 310 are formed, and the exhaust of the aero-engine 2000 is smoothly introduced into the wake cloud generation and evolution system 300, so that the generation and evolution of the wake cloud are simulated.

[0179] In a specific example, when the generation and evolution of the wake cloud are simulated by using the experimental device 1000 for simulating the generation and evolution of the aircraft wake cloud, the aero-engine 2000 is arranged in the test cabin 210 first, and the thrust tester 220 is connected and the connection between the systems is checked, so that the connection between the systems is ensured to be good and the functions of the systems are ensured to be good.

[0180] After the checking is completed, the aero-engine 2000 is started under the ground air intake condition, the aero-engine 2000 is operated to the load condition to be measured, the performance indexes and parameters of the aero-engine 2000 under the ground state are observed, the aero-engine 2000 is ensured to be normal, and the first air supply system 100, the second air supply system 400, the wake cloud generation and evolution system 300 and the air extraction system 500 are started in succession.

[0181] Subsequently, as Figure 7As shown, the simulated altitude of the aero-engine 2000 is determined, and the first air supply system 100, the second air supply system 400, the wake vortex generation and evolution system 300 and the air extraction system 500 are adjusted according to the simulated altitude to achieve adjustment of the intake state of the aero-engine 2000, the state of the test cabin 210 and the state of the environmental cabin 310, so that the test cabin 210 and the environmental cabin 310 are both in the working state of wake vortex generation and evolution.

[0182] When the test cabin 210 and the environmental cabin 310 are both in the working state of wake vortex generation and evolution, as shown in Figure 7 the wake vortex generation and evolution system 300 is started to simulate the generation and evolution of the exhaust gas of the aero-engine 2000.

[0183] In a specific example, the switch valve 600 upstream of the diluter 331 and the electrically controlled valve 700 can be opened to facilitate simulation of the generation and evolution of the exhaust gas of the aero-engine 2000 by the wake vortex generation and evolution system 300.

[0184] It should be noted that during the simulation of the generation and evolution of the exhaust gas of the aero-engine 2000 by the wake vortex generation and evolution system 300, a high-speed camera can be used to observe the wake vortex in the environmental cabin 310, and the observation content includes but is not limited to emission aerosol particles, particle immersion, water condensation and ice crystal growth, top (bottom) ice crystal continues to grow (sublimation) stage.

[0185] In addition, during the observation, the data of different stages can also be saved by the data acquisition device to facilitate subsequent analysis of the generation and evolution of the wake vortex.

[0186] When the above experiment is completed, as shown in Figure 7 whether the aero-engine 2000 has completed the wake vortex generation and evolution simulation experiment of all altitudes of the current working condition, and when it is judged that the wake vortex generation and evolution simulation experiment of all altitudes of the current working condition has not been completed, the simulated altitude is adjusted again until the wake vortex generation and evolution simulation experiment of all altitudes of the aero-engine 2000 under the current working condition is completed.

[0187] In addition, when it is judged that the wake vortex generation and evolution simulation experiment of all altitudes of the current working condition is completed, it is also continuously judged whether the aero-engine 2000 has completed the wake vortex generation and evolution simulation experiment of all altitudes of all working conditions, and when it is judged that the wake vortex generation and evolution simulation experiment of all altitudes of all working conditions has not been completed, the speed and load working condition of the aero-engine 2000 is changed, and the aero-engine 2000 is started again to complete the wake vortex generation and evolution simulation experiment of all altitudes of the aero-engine 2000 under all working conditions.

[0188] Finally, after the simulation ends, the high-altitude simulation system 200 and the wake cloud generation and evolution system 300 are closed in turn, and the first air supply system 100, the second air supply system 400 and the air extraction system 500 are adjusted, so that the air intake and exhaust of the aero-engine 2000 gradually return to the ground running state, and the aero-engine 2000 is stopped, and the detection is completed.

[0189] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integrally connected; it can be mechanical connection, or electrical connection. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0190] Other components of the experimental device 1000 and experimental method for simulating the generation and evolution of aircraft wake cloud according to the embodiments of the present application, such as the structure and working principle of the intake tower 130, the filter, the screw air compressor, the warmer 160, the dryer, the refrigerator and the thrust tester 220, etc. are known to those skilled in the art, and will not be described in detail here.

[0191] In the description of the present application, the description of the terms "embodiment", "example" and the like means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0192] Although the embodiments of the present application have been shown and described, those skilled in the art can understand that various changes, modifications, replacements and variations can be made to these embodiments without departing from the principles and purposes of the present application, and the scope of the present application is defined by the claims and their equivalents.

Claims

1. An experimental apparatus for simulating the generation and evolution of aircraft contrails, characterized in that, include: A first gas supply system and a high-altitude simulation system, wherein the high-altitude simulation system includes a test chamber and an aircraft engine is installed inside the test chamber, and the first gas supply system is used to supply cryogenic gas toward the aircraft engine; A contrail cloud generation and evolution system, comprising an environmental chamber, a nozzle, and a dilution assembly, wherein the dilution assembly is used to receive and dilute the exhaust gas of the aircraft engine and deliver the diluted exhaust gas to the nozzle, and the nozzle can spray the exhaust gas into the environmental chamber; A second gas supply system is used to deliver low-temperature, high-humidity gas toward the environmental chamber. An extraction system is connected to the test chamber, the aircraft engine, and the environmental chamber, respectively, and is used to extract gases from the test chamber, the aircraft engine, and the environmental chamber.

2. The experimental apparatus for simulating the generation and evolution of aircraft contrails according to claim 1, characterized in that, The dilution component includes: A diluter, which is connected to the aircraft engine, is used to receive and dilute the exhaust gas of the aircraft engine; A gas supply element, which is connected to the diluent, is used to supply diluent gas toward the diluent.

3. The experimental apparatus for simulating the generation and evolution of aircraft contrails according to claim 2, characterized in that, The diluter includes a dilution chamber, a first air inlet and an air outlet located at both ends of the dilution chamber along its axial direction. Both the first air inlet and the air outlet are connected to the dilution chamber. The exhaust gas from the aircraft engine enters the dilution chamber through the first air inlet, and the air outlet is used to discharge the gas from the dilution chamber.

4. The experimental apparatus for simulating the generation and evolution of aircraft contrails according to claim 3, characterized in that, The diluter also includes a second air inlet located circumferentially in the diluter, the second air inlet being in communication with the dilution chamber, and the gas supply element supplying diluent gas toward the dilution chamber through the second air inlet.

5. The experimental apparatus for simulating the generation and evolution of aircraft contrails according to claim 4, characterized in that, The second air inlet includes a plurality of them, which are arranged at radial intervals along the diluent, and the second air inlets extend obliquely from the outside to the inside along the radial direction of the diluent toward the air outlet.

6. The experimental apparatus for simulating the generation and evolution of aircraft contrails according to claim 1, characterized in that, The second gas supply system includes a first refrigeration unit and a first gas supply line and a second gas supply line connected in parallel. The first gas supply line is used to supply low-humidity gas to the first refrigeration unit, and the second gas supply line is used to supply high-humidity gas to the first refrigeration unit. The first refrigerator mixes the received gas and lowers its temperature, and is used to deliver the cryogenic gas to the environmental chamber.

7. The experimental apparatus for simulating the generation and evolution of aircraft contrails according to claim 1, characterized in that, The first gas supply system includes a mixer and a third, a fourth, and a fifth gas supply line that are simultaneously connected to the mixer; The third gas supply path is used to supply room temperature gas to the mixer, the fourth gas supply path is used to supply high temperature gas to the mixer, and the fifth gas supply path is used to supply low temperature gas to the mixer. The mixer mixes the gases and delivers them to the aircraft engine.

8. The experimental apparatus for simulating the generation and evolution of aircraft contrails according to claim 1, characterized in that, The high-altitude simulation system also includes a thrust tester and an air intake valve. The thrust tester is located inside the test chamber and is used to measure the thrust of the aero-engine. The air intake valve is connected to the test chamber and is used to allow air to enter the test chamber.

9. The experimental apparatus for simulating the generation and evolution of aircraft contrails according to claim 1, characterized in that, The air extraction system includes: A vacuum pump assembly, which is connected to the test chamber, the aero-engine and the environmental chamber respectively, and includes a first vacuum pump and a second vacuum pump arranged in parallel; A heat exchanger is provided between the vacuum pump assembly and the environmental chamber to increase the temperature of the gas entering the vacuum pump assembly; A cooler is provided between the vacuum pump assembly and the aircraft engine to reduce the temperature of the gas entering the vacuum pump assembly.

10. An experimental method for an experimental apparatus for simulating the generation and evolution of aircraft contrails as described in any one of claims 1-9, characterized in that, Includes the following steps: The aircraft engine is installed in the test cabin; Start the aircraft engine under ground air intake conditions and determine whether the aircraft engine is in normal condition. If it is normal, proceed to the next step; if it is not normal, troubleshoot the problem. The experimental apparatus for simulating the generation and evolution of aircraft contrails is activated, and the generation and evolution of exhaust gas from the aero-engine are simulated using the contrail generation and evolution system.

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