Multi-type aero-engine high-altitude simulation sampling device and simulation system

Abstract

The invention discloses a multi-type aero-engine high-altitude simulation sampling device and simulation system, the multi-type aero-engine high-altitude simulation sampling device comprises an oil filter module, a multi-stage dilution module and a sampling module which are sequentially communicated with a sampling rake, and the sampling rake is used for collecting high-altitude simulation emissions of aero-engines; the oil filter module is communicated with the sampling rake and comprises a plurality of channels, each channel is provided with a filter screen and a plurality of filter layers, and the oil filter module is used for filtering emissions output by the sampling rake by adopting the corresponding channel based on the type of the aero-engine to obtain a detection object; the multi-stage dilution module comprises a plurality of diluters and is used for carrying out multi-stage dilution on a detection object discharged by the oil filter module; the sampling module comprises a particle sampling system and a gas sampling system, and is used for carrying out particle sampling and gas sampling on the detection substances subjected to multi-stage dilution so as to be used for detecting high-altitude simulation emissions of an aero-engine. The sampling device can be suitable for sampling and detecting emissions of various different types of aero-engines.

Description

Technical Field

[0001] The present application relates to the technical field of high-altitude simulation of aircraft engines, and more specifically, to a high-altitude simulation sampling device and simulation system for multiple types of aircraft engines. Background Art

[0002] With increasing global attention to environmental protection and climate change, the impact of aircraft emissions on the high-altitude environment and climate change has become a research hotspot. Aircraft engine emissions are complex and diverse, encompassing volatile particulate matter, non-volatile particulate matter, nitrogen oxides (NOx), incompletely burned hydrocarbons, and a variety of unconventional pollutants. Under the unique low-temperature, low-pressure environment of high altitude, the physical and chemical behavior of these emissions undergoes significant changes. Particulate matter, in particular, can act as heterogeneous condensation nuclei for water vapor, directly promoting the formation of contrails, which in turn influence the global radiative forcing balance and drive global warming. Therefore, accurately measuring and assessing the behavior of aircraft engine emissions in the high-altitude environment is of paramount importance for environmental protection and climate change response.

[0003] However, existing high-altitude emissions measurement systems have significant shortcomings in simulating realistic high-altitude environments, significantly compromising the accuracy and reliability of measurement results. Different engine types exhibit significant variations in emission characteristics due to key factors such as combustion temperature and fuel, posing a significant challenge to accurately assessing engine emissions. Existing technologies are prone to sampling distortion during the sampling process and lack the ability to adjust sampling for different engines under various complex conditions. Summary of the Invention

[0004] One object of the present application is to provide a high-altitude simulation sampling device for multiple types of aircraft engines to solve at least one of the problems existing in the prior art. Another object of the present application is to provide an aircraft engine high-altitude simulation system.

[0005] To achieve the above objectives, this application adopts the following technical solutions:

[0006] The present application discloses a multi-type aircraft engine high-altitude simulated sampling device, comprising an oil filter module, a multi-stage dilution module, and a sampling module, which are sequentially connected to a sampling rake, wherein the sampling rake is used to collect emissions simulated at high altitude from aircraft engines;

[0007] The oil filter module is in communication with the sampling rake and includes a plurality of channels, each of which is provided with a filter screen and a plurality of filter layers, and is used to filter the emissions output by the sampling rake using a corresponding channel based on the type of the aircraft engine to obtain a test object;

[0008] The multi-stage dilution module includes a plurality of diluters for performing multi-stage dilution on the test object discharged from the oil filter module;

[0009] The sampling module includes a particle sampling system and a gas sampling system, which are used to respectively perform particle and gas sampling on the test object after multi-stage dilution for use in the detection of high-altitude simulated emissions of aircraft engines.

[0010] Optionally, the oil filter module includes an input main pipeline, an output main pipeline and a plurality of channels;

[0011] Both ends of each channel are connected to the input main pipeline and the output main pipeline respectively;

[0012] Each of the channels is provided with a valve for opening or closing the corresponding channel.

[0013] Optionally, the pore sizes of the filter screen and the filter layer on each channel are different, and the size of the pore size corresponds to the engine type of the aircraft engine emissions that need to be filtered.

[0014] Optionally, the filter screen is annular with a side wall fixedly connected to the channel, and the multiple filter layers include two filter layers, which are respectively arranged at both ends of the filter screen, and the size of the filter layer matches the filter screen.

[0015] Optionally, it further includes a centrifugal separation device, which is arranged between the sampling rake and the oil filter module.

[0016] Optionally, the multi-stage dilution module includes a plurality of dilution units connected in sequence;

[0017] The dilution unit includes a mass flow controller, a diluter and a pressure relief channel;

[0018] The mass flow controller controls the flow rate of the transmitted test object under the action of the control system;

[0019] The diluter receives the test object input by the mass flow controller, mixes the test object with the input dilution gas to dilute the exhaust, and then outputs it to the next level dilution unit or sampling module;

[0020] The pressure relief channel is in communication with the diluter and is used to balance the air pressure in the diluter.

[0021] Optionally, the sampling rake, the oil filter module, the multi-stage dilution module and the sampling module are connected via a pipeline;

[0022] The pipeline has a double-layer thermal insulation structure.

[0023] Optionally, the double-layer insulation structure includes an inner layer and an outer layer;

[0024] The inner layer is connected to a temperature regulating device, and the temperature regulating device is used to regulate the temperature of the inner layer;

[0025] The outer surface of the outer layer is provided with a heat-insulating layer.

[0026] Optionally, the sampling module is connected to a vacuum pump, and the sampling module samples under the negative pressure condition formed by the vacuum pump.

[0027] The present application also discloses an aircraft engine high-altitude simulation system, including the multi-type aircraft engine high-altitude simulation sampling device as described above.

[0028] The beneficial effects of this application are as follows:

[0029] The high-altitude simulation sampling device for multiple types of aircraft engines of the present application includes an oil filter module, a multi-stage dilution module and a sampling module which are sequentially connected to a sampling rake. The oil filter module of the sampling device of the present application is provided with multiple channels, each of which is provided with a filter screen and multiple filter layers, and different materials are used to filter the emissions of the aircraft engine. The filter screens and filter layers of the multiple channels in the oil filter module are respectively provided for different types of aircraft engines, and different scales of filtration are performed according to the characteristics of the emissions of different aircraft engines, so that the filtration of the emissions can achieve the best effect. At the same time, the multi-stage dilution module of the sampling device is provided with multiple diluters, and the multiple diluters can realize the dilution of different proportions of the test object obtained after filtration by the filter module. The diluted test object is then sampled by both particles and gases for subsequent emission detection. The sampling device of the present application can be applied to the sampling and detection of emissions of multiple different types of aircraft engines, avoiding the problem of sampling distortion, improving sampling accuracy, and improving detection accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The specific implementation of this application is further described in detail below with reference to the accompanying drawings.

[0031] Figure 1 A schematic diagram showing a specific embodiment of the high-altitude simulation sampling device for multiple types of aircraft engines of the present application;

[0032] Figure 2 A schematic diagram showing the structure of the oil filter module of a high-altitude simulated sampling device for multiple types of aircraft engines;

[0033] Figure 3 A schematic diagram showing the structure of a multi-stage dilution module for a high-altitude simulated sampling device for multiple types of aircraft engines is shown. DETAILED DESCRIPTION

[0034] To more clearly illustrate the present application, the present application is further described below in conjunction with the embodiments and drawings. Similar components in the drawings are represented by the same reference numerals. Those skilled in the art should understand that the specific description below is illustrative rather than restrictive and should not be used to limit the scope of protection of this application.

[0035] In the description of this application, it should be noted that the terms "upper" and "lower" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0036] It should also be noted that, in the description of the present application, relational terms such as first and second, etc. are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply the existence of any such actual relationship or order between these entities or operations. Moreover, the terms "comprise", "include" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the statement "comprises a ..." does not exclude the presence of other identical elements in the process, method, article or device comprising the element.

[0037] At present, high-altitude environmental simulation experimental platforms have become an important means of evaluating aircraft engine emissions due to their wide simulation range, multiple test parameters, high efficiency and time-saving, and safe and controllable advantages. In aircraft engine high-altitude simulation experiments, engine emission sampling is an important part of evaluating engine performance and environmental characteristics. Common sampling methods include direct sampling, dilution sampling, and constant volume sampling. The direct sampling method has simple equipment and is easy to operate, but it can easily lead to high concentrations of certain pollutants and condensation in low-temperature environments, affecting sampling accuracy. The dilution sampling method reduces the exhaust temperature and pollutant concentration by dilution, more realistically simulating the diffusion process of exhaust in the atmosphere, but the dilution ratio and flow rate adjustment functions are limited, making it difficult to adapt to the needs of different types of engines. The constant volume sampling method is suitable for measuring total emissions, but physical and chemical changes are prone to occur during the sampling process, resulting in distorted measurement results.

[0038] Existing high-altitude emission measurement systems have obvious deficiencies in simulating real-world high-altitude environments, which directly leads to a significant reduction in the accuracy and reliability of measurement results. Different types of engines have significantly different emission characteristics due to differences in key factors such as combustion temperature and fuel, which poses a huge challenge to truly evaluating engine emission characteristics. Existing technologies are prone to sampling distortion during the sampling process and lack the ability to adjust sampling for different engines in various complex situations. In addition, the existing sampling process still has many defects, such as the lack of pipe heating function and flow rate and dilution ratio adjustable functions. These problems seriously restrict the comprehensive evaluation of engine performance and emissions, and it is difficult to meet the growing demand for comprehensive testing.

[0039] In summary, while existing high-altitude environmental simulation platforms play an important role in aircraft engine emissions assessment, they still have many shortcomings in terms of sampling technology, making it difficult to adapt to the high-altitude simulation sampling requirements of different engine types. Therefore, it is particularly urgent to develop a sampling and analysis system that can overcome the shortcomings of existing technology and adapt to the high-altitude emissions research needs of different engine types and new fuels.

[0040] Aiming at the shortcomings of existing technologies, such as Figure 1 As shown, this embodiment proposes a multi-type aircraft engine high-altitude simulation sampling device, including an oil filter module 1, a multi-stage dilution module 2 and a sampling module 3 connected to a sampling rake in sequence, and the sampling rake is used to collect emissions simulated at high altitude from aircraft engines.

[0041] The oil filter module 1 is connected to the sampling rake and includes multiple channels 13. Each channel 13 is provided with a filter mesh and multiple filter layers, which is used to filter the emissions output by the sampling rake using the corresponding channel 13 based on the type of the aircraft engine to obtain the test object.

[0042] The multi-stage dilution module 2 includes a plurality of diluters for performing multi-stage dilution on the test object discharged from the oil filter module 1 .

[0043] The sampling module 3 includes a particle sampling system 301 and a gas sampling system 302, which are used to respectively perform particle and gas sampling on the test object after multi-stage dilution for the detection of simulated emissions of aircraft engines at high altitude.

[0044] The high-altitude simulation sampling device for multiple types of aircraft engines of the present application includes an oil filter module 1, a multi-stage dilution module 2 and a sampling module 3 which are sequentially connected to a sampling rake. The oil filter module 1 of the sampling device of the present application is provided with multiple channels 13, each of which is provided with a filter screen and multiple filter layers, and different materials are used to filter the emissions of the aircraft engine. The filter screens and filter layers of the multiple channels 13 in the oil filter module 1 are respectively provided for different types of aircraft engines, and different scales of filtration are performed according to the characteristics of the emissions of different aircraft engines, so that the filtration of the emissions can achieve the best effect. At the same time, the multi-stage dilution module 2 of the sampling device is provided with multiple diluters, and the multiple diluters can realize the dilution of different proportions of the test object obtained after filtration by the filter module. The diluted test object is then sampled by both particles and gases for subsequent emission detection. The sampling device of the present application can be applied to the sampling and detection of emissions of multiple different types of aircraft engines, avoiding the problem of sampling distortion, improving sampling accuracy, and improving detection accuracy.

[0045] In an optional embodiment, if Figure 2 As shown, the oil filter module 1 includes an input main pipeline 11, an output main pipeline 12 and multiple channels 13; the two ends of each channel 13 are respectively connected to the input main pipeline 11 and the output main pipeline 12; each channel 13 is provided with a valve 14 for opening or closing the corresponding channel 13.

[0046] Specifically, the oil filter module 1 of the present application is structured in the form of a combination of a main pipeline and branch channels 13. The main pipeline 11 uniformly receives the emissions of the aircraft engine output by the sampling rake, and has parallel triple channels 13 for removing particles, oil droplets, and oil mist generated by unburned different fuels after the tail nozzle. The main pipeline is connected to multiple channels 13. By selecting the channel 13, the emissions in the main pipeline are filtered through the selected channel 13 to obtain the detected object, which is output to the output main pipeline 12. The detected object is then output to the multi-stage dilution module 2 through the output main pipeline 12. This structural arrangement facilitates the connection and integration of the oil filter module 1 with other modules, and also facilitates the use of the oil filter module 1 in different filtering scenarios, thereby improving the applicability of the oil filter module 1.

[0047] The selection of the channel 13 is achieved by the valve 14 provided on the channel 13 , and the opening and closing of the channel 13 are achieved by opening and closing the valve 14 , that is, when the channel 13 is selected, the corresponding valve 14 on the channel 13 is opened to open the channel 13 so that the emissions can flow and be filtered through the channel 13 .

[0048] It should be noted that the valve 14 of the present application can be a manually controlled valve 14 or an electrically controlled valve 14. Those skilled in the art can determine the applicable valve 14 based on actual conditions, and this application does not limit this. Of course, in this optional embodiment, the opening and closing of the channel 13 are controlled by the valve 14. In other embodiments, other methods can also be used to achieve the opening or closing of the channel 13.

[0049] In an optional embodiment, the filter screen is annular with side walls fixedly connected to the channel 13, and the multiple filter layers include two filter layers, which are respectively arranged at both ends of the filter screen, and the size of the filter layer matches the filter screen.

[0050] Specifically, in this embodiment, the filtering structure of the oil filter module 1 is provided with a filter screen on the channel 13, and two filter layers are provided at both ends of the filter screen, and impurities in the emissions are filtered through the filter layers, and the filtered impurities are discharged through the filter screen.

[0051] Among them, the filter structure formed by the filter mesh and the filter layer can be fixed in the channel 13, so that the size of the filter structure matches the cross-sectional size of the channel 13, so that the emissions are basically filtered out of impurities through the filter structure, and at the same time, a partial gap is left between the filter mesh and the inner wall of the channel 13, and the emissions are filtered through double layers in different directions of the filter layer and the filter mesh, so as to achieve a better emission impurity filtering effect.

[0052] In an optional embodiment, the mesh size of the filter and the filtration layer on each of the channels 13 are different, and the size of the pore size corresponds to the engine type of the aircraft engine emissions that need to be filtered.

[0053] Specifically, each passage of the oil filter module 1 includes two filter layers, and the two filter layers are respectively arranged at both ends of the annular filter mesh 15, wherein the two filter layers include a first filter layer 16 with a pore size close to the exhaust inlet side and a second filter layer 17 close to the exhaust outflow side. The pore size of the first filter layer 16 is larger than the pore size of the second filter layer 17. Large-sized particulate impurities are first filtered through the first filter layer 16, and then filtered through the second filter layer 17 to further remove impurities in the exhaust.

[0054] To adapt to the filtration of different types of aircraft engine emissions, this application incorporates the characteristics of these emissions by providing three channels 13 and adjusting the filter mesh and filter layer apertures in each channel 13 to effectively filter most aircraft engine emissions and enhance filtration effectiveness. For example, the filter mesh apertures in each channel 13 and the filter layer apertures are adjusted based on the fuel type and engine characteristics. The oil filter module 1 comprises a first channel, a second channel, and a third channel. The first channel utilizes a 316L stainless steel annular filter mesh 15 with a pore size of 4-5 mm, a first filter layer 16 with a pore size of 4-5 mm, and a second filter layer 17 with a polyimide filter membrane with a pore size of 200 nm. The second channel utilizes a filter mesh with a pore size of 3-4 mm, a first filter layer 16 with a pore size of 3-4 mm, and a second filter layer 17 with a pore size of 300 nm. The third channel utilizes a filter mesh with a pore size of 2-3 mm, a first filter layer 16 with a pore size of 2-3 mm, and a second filter layer 17 with a pore size of 500 nm.

[0055] In an optional embodiment, the device further includes a centrifugal separation device, which is arranged between the sampling rake and the oil filter module 1.

[0056] Specifically, in practical applications, the first-pass filter has a pore size of 4-5mm and a polyimide filter membrane pore size of 200nm. It is suitable for filtering emissions from turbojet and turbofan engines burning diesel or RP-3 fuel. Under these operating conditions, the combustion product particles are large and there are many oil droplets, requiring a larger filter pore size and efficient centrifugal separation capacity. The second-pass filter has a pore size of 3-4mm and a filter layer pore size of 300nm. It is suitable for filtering emissions from turboshaft engines burning biodiesel or SAF fuel. Under these operating conditions, the combustion product particles are moderate and there is a lot of oil mist, requiring a moderate filter pore size and a strong centrifugal separation effect. The third-pass filter has a pore size of 2-3mm and a filter layer pore size of 500nm. It is suitable for filtering emissions from piston engines burning biodiesel or SAF fuel. Under these operating conditions, the combustion product particles are small and the oil mist is fine, requiring a smaller filter pore size and a larger filter membrane pore size to reduce filtration resistance while ensuring efficient oil mist filtration. Through this flexible passage design, the oil filter device can adapt to the combustion characteristics of different fuels and engines, effectively remove particles, oil droplets and oil mist in the exhaust gas, and ensure the accuracy of sampling and the cleanliness of the exhaust gas.

[0057] In an optional embodiment, if Figure 3 As shown, the multi-stage dilution module 2 includes a plurality of dilution units connected in sequence.

[0058] The dilution unit includes a mass flow controller, a diluter and a pressure relief channel 13; the mass flow controller controls the flow rate of the transmitted test substance under the action of the control system 40; the diluter receives the test substance input by the mass flow controller, mixes the test substance with the input dilution gas to dilute the exhaust, and then outputs it to the next-level dilution unit or sampling module 3; the pressure relief channel 13 is connected to the diluter to balance the air pressure in the diluter.

[0059] Specifically, in this optional embodiment, the multi-stage dilution module 2 implements multi-stage dilution of the test object by providing multiple diluters. The dilution ratios of the different diluters can be adjusted and set to achieve the desired test object dilution effect. The multi-stage dilution module 2 implements multi-stage dilution through the control of multiple mass flow controllers, achieving adjustable dilution ratios and simultaneously controlling the sampling flow rate, facilitating connection to different measuring instruments.

[0060] For example, Figure 3 A specific embodiment of the multi-stage dilution module 2 is shown. In this embodiment, the multi-stage dilution module 2 includes three dilution units connected in sequence, namely a first dilution unit, a second dilution unit and a third dilution unit.

[0061] The first dilution unit includes a first mass flow controller 31, a first diluter 32, and a first pressure relief channel 33; the second dilution unit includes a second mass flow controller 34, a first diluter 32, and a second pressure relief channel 36; and the third dilution unit includes a third mass flow controller 37, a third diluter 38, and a third pressure relief channel 39. The first diluter 32, the first diluter 32, and the third diluter 38 are each connected to a dilution gas reservoir 41 to receive dilution gas from the reservoir 41. The first mass flow controller 31, the second mass flow controller 34, and the third mass flow controller 37 are each connected to a control system 40, which controls the gas flow in the first mass flow controller 31, the second mass flow controller 34, and the third mass flow controller 37. The first mass flow controller 31 is connected to the oil filter module 1 to receive the test substance output by the oil filter module 1. The third diluter 38 is connected to the sampling module 3 to transmit the test substance diluted by multiple dilution units to the sampling module 3 for sampling.

[0062] When sampling different types of scaled-down small engines (turbofan, turbojet, turboshaft, piston), the specific adjustment of the mass flow controller is as follows according to its performance characteristics: For turbofan engines, the sampling flow rate can be adjusted in the range of 10-50m 3 / min, the dilution ratio is recommended to be 1:1 to 10:1, the sampling point is located 1-2 meters behind the tail nozzle, and the sampling module 3 needs to withstand an airflow of 200-600°C; the sampling flow range of the turbojet engine is 5-30m3 / min, the dilution ratio is 1:1 to 5:1, the sampling point is 0.5-1 meters behind the tail nozzle, and the equipment needs to adapt to high-temperature airflow of 300-800℃; the sampling flow rate of the turboshaft engine is 5-20m 3 / min, the dilution ratio is 1:1 to 8:1, the sampling point is 0.5-1 meter behind the exhaust port, and the equipment needs to withstand airflow of 250-700℃; the sampling flow range of the piston engine is 3-15m 3 / min, a dilution ratio of 1:1 to 3:1, a sampling point 0.3-0.8 meters behind the exhaust port, and sampling module 3 adapted to airflows of 150-400°C. These specific numerical adjustments allow the sampling system to better adapt to the testing requirements of different engines, ensuring sampling accuracy and equipment safety.

[0063] The sampling module 3 includes a particle sampling system 301 and a gas sampling system 302, which are used to respectively perform particle and gas sampling on the multi-stage diluted test object for use in high-altitude simulated emissions testing of aircraft engines. In practical applications, the particle sampling system 301 and the gas sampling system 302 can be implemented using existing sampling equipment capable of performing particle and gas sampling, and this application is not limited thereto.

[0064] In an optional embodiment, the sampling rake, the oil filter module 1, the multi-stage dilution module 2 and the sampling module 3 are connected through a pipeline; the pipeline is a double-layer insulation structure.

[0065] Specifically, the sampling pipelines from the heating pipe to various instruments after the sampling rake of the present application are equipped with pipeline insulation and heating settings to avoid the experimental environment from affecting the gas emitted by the aircraft engine, resulting in low detection accuracy.

[0066] In an optional embodiment, the double-layer insulation structure includes an inner layer and an outer layer; the inner layer is connected to a temperature regulating device, and the temperature regulating device is used to regulate the temperature of the inner layer; and an insulation layer is provided on the outer surface of the outer layer.

[0067] Specifically, the double-layer insulation structure features a two-layer design, with an outer insulation layer and an inner adjustable heating device, enabling heating to be tailored to the exhaust temperature of different engines. This entire pipeline reduces pollutant adsorption and improves sampling stability. In the laboratory, for different types of scaled-down small engines (turbofan, turbojet, turboshaft, piston), the heat tracing pipeline after the sampling rake is configured with appropriate insulation and heating settings based on the engine exhaust temperature and sampling requirements. For turbofan engines, exhaust temperatures typically range from 200-600°C, and the heating line is maintained at 180-200°C to prevent contaminant condensation and ensure sample gas stability. Turbojet engines have higher exhaust temperatures, reaching 300-800°C, and the heating line is maintained at 200-250°C to accommodate the high exhaust temperatures and prevent moisture condensation in the sample gas. Turboshaft engines have exhaust temperatures ranging from 250-700°C, and the heating line is maintained at 180-220°C to reduce contaminant adsorption and ensure sample gas uniformity. Reciprocating engines have relatively low exhaust temperatures, typically 150-400°C, and the heating line is maintained at 150-180°C to prevent water vapor condensation and ensure sample gas stability. Long pipelines can use a self-limiting electric heating system to automatically adjust the temperature, ensuring that the pipe wall temperature is above the dew point of the sample gas, thereby reducing contaminant adsorption and improving sampling stability and accuracy.

[0068] In an optional embodiment, the sampling module 3 is connected to a vacuum pump, and the sampling module 3 samples under the negative pressure conditions formed by the vacuum pump. A vacuum pump is placed after the entire sampling system to achieve sampling under negative pressure conditions and to achieve adjustable flow throughout the sampling process.

[0069] In summary, this application provides a high-altitude simulated sampling device suitable for various types of aircraft engines. The device can accurately monitor the emissions of the engine in a low-temperature and low-pressure environment that simulates high altitude. The system is equipped with an oil filter device to effectively remove unburned fuel and ensure sampling accuracy. At the same time, the entire pipeline has insulation and heating functions to prevent low temperatures from adversely affecting the sampling process. In addition, the exhaust sampling dilution ratio and flow rate are adjustable, and can be flexibly set according to the high-altitude requirements of different types of engines, thereby meeting diverse test requirements and providing an efficient and reliable solution for engine high-altitude emission research.

[0070] Based on the same principle, the present application also discloses an aircraft engine high-altitude simulation system, which includes the multi-type aircraft engine high-altitude simulation sampling device described in this embodiment.

[0071] Since the principle of solving the problem of this system is similar to that of the above device, the implementation of this system can refer to the implementation of the device and will not be repeated here.

[0072] The various embodiments in this specification are described in a progressive manner. Similar parts between the various embodiments can be referred to in conjunction with each other. Each embodiment focuses on the differences between the other embodiments. In particular, the system embodiments are generally similar to the method embodiments, so the description is relatively simple. For relevant parts, refer to the description of the method embodiments.

[0073] Obviously, the above embodiments of the present application are merely examples for clearly illustrating the present application, and are not intended to limit the implementation methods of the present application. For ordinary technicians in this field, other different forms of changes or modifications can be made based on the above description. It is impossible to list all the implementation methods here. All obvious changes or modifications derived from the technical solution of the present application are still within the scope of protection of the present application.

Claims

1. A high-altitude simulation sampling device for multiple types of aircraft engines, characterized in that: It includes an oil filter module, a multi-stage dilution module and a sampling module which are sequentially connected to a sampling rake, wherein the sampling rake is used to collect emissions simulated at high altitude from an aircraft engine; The oil filter module is in communication with the sampling rake and includes a plurality of channels, each of which is provided with a filter screen and a plurality of filter layers, and is used to filter the emissions output by the sampling rake using a corresponding channel based on the type of the aircraft engine to obtain a test object; The multi-stage dilution module includes a plurality of diluters for performing multi-stage dilution on the test object discharged from the oil filter module; The sampling module includes a particle sampling system and a gas sampling system, which are used to respectively perform particle and gas sampling on the test object after multi-stage dilution for use in the detection of high-altitude simulated emissions of aircraft engines.

2. The multi-type aircraft engine high-altitude simulation sampling device according to claim 1 is characterized in that: The oil filter module includes an input main pipeline, an output main pipeline and multiple channels; Both ends of each channel are connected to the input main pipeline and the output main pipeline respectively; Each of the channels is provided with a valve for opening or closing the corresponding channel.

3. The multi-type aircraft engine high-altitude simulation sampling device according to claim 1 is characterized in that: The pore sizes of the filter screen and the filter layer on each channel are different, and the size of the pore size corresponds to the engine type of the aircraft engine emissions that need to be filtered.

4. The multi-type aircraft engine high-altitude simulation sampling device according to claim 1, characterized in that: The filter screen is in a ring shape with a side wall fixedly connected to the channel. The multiple filter layers include two filter layers, which are respectively arranged at both ends of the filter screen. The size of the filter layer matches the filter screen.

5. The high-altitude simulation sampling device for multiple types of aircraft engines according to claim 1, characterized in that: It further comprises a centrifugal separation device, which is arranged between the sampling rake and the oil filter module.

6. The multi-type aircraft engine high-altitude simulation sampling device according to claim 1, characterized in that: The multi-stage dilution module includes a plurality of dilution units connected in sequence; The dilution unit includes a mass flow controller, a diluter and a pressure relief channel; The mass flow controller controls the flow rate of the transmitted test object under the action of the control system; The diluter receives the test object input by the mass flow controller, mixes the test object with the input dilution gas to dilute the exhaust, and then outputs it to the next level dilution unit or sampling module; The pressure relief channel is in communication with the diluter and is used to balance the air pressure in the diluter.

7. The high-altitude simulation sampling device for multiple types of aircraft engines according to claim 1, characterized in that: The sampling rake, the oil filter module, the multi-stage dilution module and the sampling module are connected through pipelines; The pipeline has a double-layer thermal insulation structure.

8. The high-altitude simulation sampling device for multiple types of aircraft engines according to claim 7, characterized in that: The double-layer thermal insulation structure includes an inner layer and an outer layer; The inner layer is connected to a temperature regulating device, and the temperature regulating device is used to regulate the temperature of the inner layer; The outer surface of the outer layer is provided with a heat-insulating layer.

9. The high-altitude simulation sampling device for multiple types of aircraft engines according to claim 7, characterized in that: The sampling module is connected to a vacuum pump, and the sampling module samples under the negative pressure condition formed by the vacuum pump.

10. An aircraft engine high altitude simulation system, characterized in that: It comprises the high-altitude simulation sampling device for multiple types of aircraft engines as described in any one of claims 1-9.

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