General aero-engine sample gas measuring device, method and simulation system

Abstract

The invention discloses a general aero-engine sample gas measuring device and method and a simulation system, and the device comprises a bypass dilution module which is communicated with a sampling rake and can carry out the dilution or non-dilution of a first proportion on a sample gas sampled by the sampling rake; the gaseous five-component analyzer is communicated with the sampling rake and is used for detecting gaseous components of the sample gas output by the sampling rake; the first dilution module is communicated with the bypass dilution module and is used for diluting the discharged sample gas output by the bypass dilution module according to a second proportion to obtain a to-be-detected sample; and the multi-component analysis module is used for performing non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection on the to-be-detected sample output by the first dilution module. The method can be suitable for sample gas detection of various types of aero-engines.

Description

Technical Field

[0001] The present application relates to the field of aviation engine testing technology, and more specifically, to a general aviation engine sample gas measurement device, method, and simulation system. Background Art

[0002] One method for high-altitude performance testing of aircraft engines is high-altitude environment simulation, which recreates flight conditions on the ground and conducts high-altitude characteristic experimental measurements of aircraft engines. This facility platform is collectively referred to as an aircraft engine high-altitude simulation experimental platform, which is the most effective performance debugging and technical breakthrough experimental platform in the development of aircraft engines.

[0003] However, the existing high-altitude simulation test platform for aircraft engines can only measure the sample gas of civil aviation turbofan and turbojet engines, and cannot detect various types of aircraft engines, so its scope of application is narrow. Summary of the Invention

[0004] One object of the present application is to provide a general-purpose aviation engine gas sample measurement device to address at least one of the problems existing in the prior art. Another object of the present application is to provide an application method for the general-purpose aviation engine gas sample measurement device. Yet another object of the present application is to provide an aviation engine high-altitude simulation system.

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

[0006] The present application discloses a general aviation engine gas sample measurement device, comprising:

[0007] a bypass dilution module, connected to the sampling rake, capable of diluting the sample gas obtained by the sampling rake by a first ratio or not diluting the sample gas;

[0008] a gaseous five-component analyzer, connected to the sampling rake, for detecting gaseous components of the sample gas output by the sampling rake;

[0009] a first dilution module, connected to the bypass dilution module, for diluting the exhaust sample gas output by the bypass dilution module by a second ratio to obtain a sample to be tested;

[0010] The multi-component analysis module is used to perform non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection on the sample to be detected output by the first dilution module.

[0011] Optionally, it further includes a first diverter, a first isolation valve and a pressure control valve;

[0012] The sampling rake is communicated with the air inlet of the first flow splitter, and the three air outlets of the first flow splitter are communicated with the gaseous five-component analyzer, the bypass dilution module and the pressure control valve respectively.

[0013] Optionally, the first dilution module includes a first diluter, a first diluent heater, a second isolation valve and a first gas storage tank;

[0014] One air inlet of the first diluter is in communication with the bypass dilution device, and the other air inlet is in communication with the diluent heater, and the diluent heater is in communication with the first air storage tank via the second isolation valve;

[0015] The first gas storage tank stores filtered dilution gas.

[0016] Optionally, it further includes a cyclone separator and a second splitter;

[0017] The first dilution module is communicated with one end of the cyclone separator, the other end of the cyclone separator is communicated with the air inlet of the second splitter, and the multiple air outlets of the second splitter are communicated with the multi-component analysis module.

[0018] Optionally, the first dilution module is connected to the second flow splitter via a heat tracing pipe;

[0019] The heating pipe includes a detachably connected base section, a first extension section, and a second extension section.

[0020] Optionally, the multi-component analysis module includes an nvPM mass concentration analyzer, an nvPM number concentration analyzer, a black carbon analyzer, a rapid particle size spectrometer, and a VOCs and CO2 analyzer, which are respectively connected to the multiple gas outlets of the second splitter;

[0021] wherein the nvPM number concentration analyzer is connected to the air outlet of the second splitter through a volatile particle remover;

[0022] The VOCs and CO2 analyzers are connected to the gas outlet of the second splitter through a first high-efficiency particulate filter and a mass flow controller in sequence.

[0023] Optionally, the bypass dilution module includes a third isolation valve, a fourth isolation valve, a fifth isolation valve, a second diluter, a third flow divider, a flow combiner, a second diluent heater, a sixth isolation valve and a third gas storage tank;

[0024] The air inlet of the third diverter is connected to the first isolation valve, the first air outlet is connected to one end of the third isolation valve, and the second air outlet is connected to one end of the fourth isolation valve;

[0025] The other end of the third isolation valve is communicated with the flow combiner;

[0026] The other end of the fourth isolation valve is communicated with the first air inlet of the second diluter, the second air inlet of the second diluter is communicated with the second diluent heater, the air outlet of the second diluter is communicated with one end of the fifth isolation valve, and the other end of the fifth isolation valve is communicated with the flow combiner;

[0027] The second diluent heater is connected to the third gas storage tank through the sixth isolation valve, and the third gas storage tank stores filtered dilution gas; or,

[0028] The bypass dilution module includes a third diverter, a first electric regulating valve, a second high-efficiency particulate filter, a second electric regulating valve and a flow combiner;

[0029] The air inlet of the third diverter is communicated with the first isolation valve, the first air outlet is communicated with one end of the first electric regulating valve, and the second air outlet is communicated with one end of the second high-efficiency particulate filter;

[0030] The other end of the first electric regulating valve is communicated with the flow combiner, the other end of the second high efficiency particulate filter is communicated with one end of the second electric regulating valve, and the other end of the second electric regulating valve is communicated with the flow combiner.

[0031] Optionally, a measurement module is also included;

[0032] The measurement module includes an air compressor, a particle generator, a drying tube, a fourth flow divider, a seventh isolation valve, and two condensation particle counters;

[0033] The air compressor, the particle generator, the drying pipe and the fourth diverter are connected in sequence;

[0034] The air compressor is also connected to the seventh isolation valve and the second diluter in sequence;

[0035] The two air outlets of the fourth diverter are respectively connected to one of the condensation particle counters and the second diluter;

[0036] The gas outlet of the second diluter is communicated with another condensation particle counter.

[0037] The present application also discloses an application method of the above-mentioned general aviation engine sample gas measurement device, comprising:

[0038] Determine the dilution factor of the sample gas;

[0039] Setting the bypass dilution module to a first ratio of dilution or no dilution based on the dilution multiple;

[0040] Outputting the sample gas obtained by the sampling rake to a gaseous five-component analyzer to detect the volume concentrations of CO, CO2, HC, O2, and NO in real time;

[0041] The sample gas obtained by the sampling rake is output to the first dilution module and the multi-component analysis module in sequence through the bypass dilution module, so that the multi-component analysis module performs non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection on the sample to be detected output by the first dilution module.

[0042] The present application also discloses an aircraft engine high-altitude simulation system, including the general aircraft engine sample gas measurement device as described above.

[0043] The beneficial effects of this application are as follows:

[0044] The general aviation engine sample gas measurement device of the present application is provided with a gaseous five-component analyzer and a multi-component analysis module, and the volume concentrations of CO, CO2, HC, O2, and NO of the aviation engine sample gas are detected in real time by the gaseous five-component analyzer, and the mass concentration of non-volatile particulate matter, particle number concentration, brown carbon mass concentration, particle size distribution, volatile organic compound concentration and CO2 concentration are detected by the multi-component analysis module. Among them, the sample gas measurement device of the present application is also provided with a bypass dilution module and a first dilution module to meet the requirements of different component detections for the sample gas dilution multiple. Therefore, the present application integrates the gaseous five-component analyzer and the multi-component analysis module, so that the emission indicators such as nvPM, volatile particulate matter, gaseous pollutants of different types of engines can be universally and multi-dimensionally detected, and is suitable for sample gas detection of various types of aircraft engines to achieve airworthiness verification of various types of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] The specific implementation of this application is further described in detail below with reference to the accompanying drawings.

[0046] Figure 1 A schematic structural diagram showing a specific embodiment of the general aviation engine gas sample measurement device of the present application is shown;

[0047] Figure 2 A schematic structural diagram of a bypass dilution module of a specific embodiment of the general aviation engine gas sample measurement device of the present application is shown;

[0048] Figure 3 A schematic structural diagram of a measurement module in a specific embodiment of the general aviation engine gas sample measurement device of the present application is shown;

[0049] Figure 4A schematic structural diagram showing another bypass dilution module of a specific embodiment of the general aviation engine gas sample measurement device of the present application;

[0050] Figure 5 A schematic structural diagram showing another measurement module of a specific embodiment of the general aviation engine gas sample measurement device of the present application;

[0051] Figure 6 A flow chart showing a specific embodiment of the general aviation engine gas sample measurement method of the present application;

[0052] Figure 7 A schematic diagram showing the structure of a computer device suitable for implementing an embodiment of the present invention is shown.

[0053] Reference numerals:

[0054] 1. Sampling rake; 2. Bypass dilution module; 3. Five-component gaseous analyzer; 11. First diverter; 12. First isolation valve; 13. Pressure control valve; 41. First diluter; 42. First diluent heater; 43. Second isolation valve; 44. First gas storage tank; 51. Cyclone separator; 52. Second diverter; 61. nvPM mass concentration analyzer; 62. nvPM number concentration analyzer; 63. Black carbon analyzer; 64. Rapid particle size spectrometer; 65. VOCs and CO2 analyzer; 66. Volatile particle remover; 67. First high-efficiency particulate filter; 68. Mass flow controller; 691. First air pump; 692. Second air pump; 693. Second air storage tank;

[0055] 21. Third isolation valve; 22. Fourth isolation valve; 23. Fifth isolation valve; 24. Second diluter; 25. Third flow divider; 26. First flow combiner; 27. Second diluent heater; 28. Sixth isolation valve; 29. ​​Third gas storage tank;

[0056] 71. Air compressor; 72. Particle generator; 73. Drying tube; 74. Fourth diverter; 75. Seventh isolation valve; 76. Condensation particle counter;

[0057] 81. Fifth flow divider; 82. First electric regulating valve; 83. Second high-efficiency particulate filter; 84. Second electric regulating valve; 85. Second flow combiner; DETAILED DESCRIPTION

[0058] 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.

[0059] 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.

[0060] 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.

[0061] The aircraft engine high altitude simulation test platform usually includes a high altitude simulation system, a gas sampling and detection system, and an intake and exhaust system. Figure 1 As shown, a high-altitude simulation system typically includes an environmental chamber and a high-altitude simulation chamber. The environmental chamber houses the aircraft engine to be tested, and the high-altitude simulation chamber is connected to the aircraft engine, and is used to receive the aircraft engine's exhaust. This means that the aircraft engine is installed in the environmental chamber, and the exhaust generated by the aircraft engine can be discharged into the high-altitude simulation chamber. The environmental chamber is used to simulate the aircraft engine's environment at high altitude, that is, to simulate the fuselage environment. The high-altitude simulation chamber is used to simulate the high-altitude evolution of the aircraft engine's exhaust, facilitating subsequent accurate testing of the aircraft engine's exhaust characteristics and evolution at high altitude.

[0062] The sample gas sampling and detection system is connected to the aircraft engine and is used to receive, collect, and detect the exhaust from the aircraft engine. In other words, the exhaust from the aircraft engine in this application is not only discharged into the high-altitude simulation cabin, but also partially discharged into the sample gas sampling and detection system. The sample gas sampling and detection system is used to collect and detect various sample gases in the exhaust, providing data support for the subsequent organization and regulation of the aircraft engine combustion flow. It can also evaluate the impact of the use of sustainable aviation fuel and zero-carbon fuel on aviation emissions.

[0063] A sampling rake 1 is provided at the exhaust port of the aircraft engine, and the sampling rake 1 is connected to a sample gas sampling and detection system so as to collect and detect the exhaust gas of the aircraft engine using the sample gas sampling and detection system.

[0064] However, the current gas sampling and detection system is only applicable to turbofan and turbojet engines for civil aviation, and does not take into account the differentiated combustion characteristics of non-civil aviation engines such as turboshafts and pistons, and the measurement method lacks universal applicability. Therefore, the present invention proposes a universal aviation engine gas sampling measurement device for multiple types of engines. By iterating the existing nvPM (Non-volatile Particulate Matter, non-volatile particulate matter, which is an emission particulate that exists on the engine exhaust pipe outlet plane and does not volatilize when heated to 350°C) emission measurement scheme that is only applicable to civil aviation, and integrating gaseous pollutant synchronous detection, volatile particle synchronous detection and particle size distribution spectrum detection modules, the present invention can universally and multi-dimensionally detect emission indicators such as nvPM, volatile particulate matter, gaseous pollutants, etc. of different types of engines, providing core data support for the construction of a unified aviation power unit airworthiness compliance verification system.

[0065] Based on this, in order to solve the problems of the prior art, this embodiment discloses a general aviation engine gas sample measurement device. Figure 1 As shown, in this embodiment, the device includes a bypass dilution module 2, a gaseous five-component analyzer 3, a first dilution module and a multi-component analysis module.

[0066] The bypass dilution module 2 is in communication with the sampling rake 1 and can dilute the sample gas obtained by the sampling rake 1 by a first ratio or not dilute it.

[0067] The gaseous five-component analyzer 3 is in communication with the sampling rake 1 and is used for detecting the gaseous components of the sample gas output by the sampling rake 1 .

[0068] The first dilution module is in communication with the bypass dilution module 2 and is used to dilute the exhaust sample gas output by the bypass dilution module 2 by a second ratio to obtain a sample to be detected.

[0069] The multi-component analysis module is used to perform non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection on the sample to be detected output by the first dilution module.

[0070] The general aviation engine sample gas measurement device of the present application is provided with a gaseous five-component analyzer 3 and a multi-component analysis module, and the volume concentrations of CO, CO2, HC, O2, and NO of the aviation engine sample gas are detected in real time by the gaseous five-component analyzer 3, and the mass concentration of non-volatile particulate matter, particle number concentration, brown carbon mass concentration, particle size distribution, volatile organic compound concentration and CO2 concentration are detected by the multi-component analysis module. Among them, the sample gas measurement device of the present application is also provided with a bypass dilution module 2 and a first dilution module to meet the requirements of different component detections for the sample gas dilution multiple. Therefore, the present application integrates the gaseous five-component analyzer 3 and the multi-component analysis module, so that the emission indicators such as nvPM, volatile particulate matter, gaseous pollutants of different types of engines can be universally and multi-dimensionally detected, and is suitable for sample gas detection of various types of aircraft engines to achieve airworthiness verification of various types of aircraft engines.

[0071] In an optional embodiment, the device further includes a first diverter 11 , a first isolation valve 12 and a pressure control valve 13 .

[0072] The sampling rake 1 is connected to the air inlet of the first diverter 11 , and the three air outlets of the first diverter 11 are connected to the gaseous five-component analyzer 3 , the bypass dilution module 2 and the pressure control valve 13 respectively.

[0073] Specifically, the sample gas obtained by the sampling rake 1 can be directly input into the gaseous five-component analyzer 3 for real-time detection of the volume concentrations of CO, CO2, HC, O2, and NO, while the detection of the multi-component analysis module requires diluting the sample gas obtained before continuing the detection step. Therefore, after the present application completes the dynamic sampling of the engine sample gas through the porous sampling rake 1, the sample gas obtained can be diverted by the first diverter 11, so that a part of the sample gas is directly input into the gaseous five-component analyzer 3 for component detection, and the other part is input into the bypass dilution module 2, and after being diluted by the bypass dilution module 2 and the first dilution module, it is input into the multi-component analysis module for further sample gas detection.

[0074] The first diverter 11 is further connected to a pressure control valve 13 , through which excess gas flowing through the first diverter 11 is discharged, thereby achieving active pressure relief and maintaining air pressure balance in the measuring device.

[0075] Optionally, a thermostatic pipeline connects the sampling rake 1 to the first diverter 11, and the sample gas obtained by the sampling rake 1 is transmitted to the first diverter 11 via the thermostatic pipeline. Preferably, the thermostatic pipeline is less than 8 meters long to prevent excessive heat loss. Similarly, a thermostatic pipeline optionally connects the first diverter 11 to the first isolation valve 12, the pressure control valve 13, and the five-component gaseous analyzer 3.

[0076] A first isolation valve 12 is provided between the first diverter 11 and the bypass dilution device. By controlling the opening or closing of the first isolation valve 12, whether the sample gas enters the subsequent dilution and detection process is controlled.

[0077] It should be noted that the sample gas sampled by the sampling rake 1 of the present application can be transmitted to the first isolation valve 12, the pressure control valve 13 and the gaseous five-component analyzer 3 respectively through the first diverter 11, or can be transmitted to the first isolation valve 12, the pressure control valve 13 and the gaseous five-component analyzer 3 through separate heating pipes. Those skilled in the art can set it according to actual needs, and this application does not limit it.

[0078] In an optional embodiment, the first dilution module includes a first diluter 41 , a first diluent heater 42 , a second isolation valve 43 and a first gas storage tank 44 .

[0079] One air inlet of the first diluter 41 is connected to the bypass dilution device, and the other air inlet is connected to the diluent heater. The diluent heater is connected to the first gas storage tank 44 through the second isolation valve 43. The first gas storage tank 44 stores filtered dilution gas.

[0080] Specifically, the first diluter 41 receives the sample gas output by the bypass dilution device through the air inlet, and the filtered dilution gas output by the first gas tank 44 is heated by the first diluent heater 42 and then input into the first diluter 41. The sample gas entering the first diluter 41 is mixed with the dilution gas to achieve the dilution effect of the sample gas. Among them, a second isolation valve 43 is provided between the first gas tank 44 and the first diluter 41 to control the dilution process of the sample gas by controlling the opening and closing of the second isolation valve 43. Optionally, the dilution ratio of the first diluter 41 is 1:10. Of course, in actual applications, those skilled in the art can also set the dilution ratio of the first diluter 41 according to actual needs, and this application does not limit this.

[0081] In an optional embodiment, a cyclone separator 51 and a second splitter 52 are further included.

[0082] The first dilution module is communicated with one end of the cyclone separator 51 , the other end of the cyclone separator 51 is communicated with the air inlet of the second splitter 52 , and the multiple air outlets of the second splitter 52 are communicated with the multi-component analysis module.

[0083] Specifically, the sample gas diluted by the bypass dilution module 2 and the first diluter 41 needs to first pass through the cyclone separator 51 to remove impurities, and then enter the second diverter 52 to be transmitted to different detection instruments through the second diverter 52 to realize multiple detections such as non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection.

[0084] It should be noted that the sample gas output by the cyclone separator 51 of the present application can be transmitted to a variety of detection instruments through the second diverter 52, or can be transmitted to a variety of detection instruments through separate heating pipes. Those skilled in the art can set it according to actual needs, and the present application does not limit this.

[0085] In an optional embodiment, the first dilution module is connected to the second diverter 52 via a heat tracing pipe; the heat tracing pipe includes a detachably connected base section, a first extension section, and a second extension section.

[0086] It is understandable that aviation turbine engine emission measurement systems usually use a heating pipe with a length of 24.5±0.5m to maintain a safe distance for engine exhaust measurement. However, in the detection of particulate matter emissions from small engines, its low-concentration emission characteristics and the excessive length of the heating pipe will cause particulate matter deposition loss under the adsorption effect of the pipe wall, forming coupling interference, resulting in measurement signal attenuation or data fluctuation, and ultimately causing airworthiness compliance verification failure. The sample gas diluted by the first dilution module of the present application can be transmitted to the second diverter 52 by selecting at least one heating pipe from the basic section, the first extension section, and the second extension section according to demand, so as to reduce the particle loss caused by mechanical vibration and excessive pipe length.

[0087] Optionally, the lengths of the base section, first extension section, and second extension section can be set to 12.5 m, 6 m, and 6 m, respectively, resulting in a 24.5 m long heat tracer pipe. Of course, in actual applications, those skilled in the art can set the lengths of the base section, first extension section, and second extension section, as well as the desired heat tracer pipe length, based on actual needs, and this application does not impose any limitations thereon.

[0088] In a preferred embodiment, the detachable heat tracing pipe meets the following technical indicators:

[0089] a) The pipe material is electrically grounded carburized polytetrafluoroethylene, which complies with ISO 8031 ​​anti-static standards.

[0090] b) The inner diameter of the pipeline is controlled within 7.59-8.15mm. The interface is strictly consistent with the inner diameter of the pipeline and seamlessly connected. The inner diameter change of the entire pipeline is less than 0.5mm to avoid the formation of steps, prevent particle deposition, and ensure accurate detection.

[0091] c) Precision threaded interface: The extension section adopts trapezoidal thread connection (pitch 2.5mm), with a tolerance of ±0.02mm, supplemented by double-layer sealing, inner layer: fluororubber O-ring (temperature resistant to 300℃); outer layer: copper-nickel alloy gasket.

[0092] d) Bending control: The pipeline is covered with spiral stainless steel support rings (spacing 50mm), and the bending radius is limited to ≥0.5m.

[0093] e) The basic pipeline with a built-in temperature sensor triggers an interlock when the preset temperature Tline is reached, which serves as the basis for judging whether the preheating is complete. Tline accurately controls the power of the diluent heater and dynamically adjusts the diluent temperature. In view of the temperature difference characteristics of the exhaust gas of different types of engines, the system can achieve precise temperature control of the diluent, effectively suppress the thermophoresis effect, and ensure that the particulate matter enters the detection instrument stably. For example, when testing civil aviation engines, due to their high exhaust temperature, Tline can be set to 60±15℃; when testing small aircraft engines, their exhaust temperature is lower, and Tline should be set to 40±5℃.

[0094] The detachable heat tracer can be configured in varying lengths based on engine type, shortening the particle transport distance in the measurement line for small engines and reducing the wall deposition loss rate. This creates a technical advantage: through modular configuration of heat tracer length and dilution ratio parameters—for example, a turbine engine utilizes a 24.5m heat tracer with two bypass dilution modules enabled, while a small engine utilizes a basic heat tracer with two bypass dilution modules disabled—this successfully overcomes the engine type limitations of traditional solutions and establishes a universal nvPM testing system, encompassing the entire engine spectrum, from large turbofan engines to small engines.

[0095] In an optional embodiment, the multi-component analysis module includes an nvPM mass concentration analyzer 61 (nvPMmi), an nvPM number concentration analyzer 62 (nvPMni), a black carbon analyzer 63, a rapid particle size spectrometer 64 and VOCs (Volatile Organic Compounds), and a CO2 analyzer, which are respectively connected to multiple air outlets of the second diverter 52.

[0096] The nvPM number concentration analyzer 62 is connected to the air outlet of the second splitter 52 through the volatile particle remover 66;

[0097] The VOCs and CO2 analyzer 65 is connected to the gas outlet of the second splitter 52 through a first high efficiency particulate filter 67 (HEPA) and a mass flow controller 68 in sequence.

[0098] It is understandable that during the operation of a small engine, incomplete combustion of fuel not only produces non-volatile particulate matter, but is also accompanied by the emission of a large amount of volatile substances. In view of the fact that the existing sample gas measurement method cannot fully reflect the emission characteristics of various types of engines, the present application optimizes the aviation engine sample gas measurement device, integrating a gaseous five-component analyzer 3 after the first diverter 11, connecting a fast particle size spectrometer 64 and a black carbon analyzer 63 in sequence after the second diverter 52, and configuring VOCs and CO2 analyzers after the first high-efficiency particulate filter 67 filters the particles, so as to achieve comprehensive monitoring of multi-component emission characteristics. Among them, the gaseous five-component analyzer 3 can detect the CO2 volume concentration ([CO2]) and the volume concentrations of gaseous pollutants CO, HC, O2, and NO before the sample gas is diluted, and the multi-component analysis module detects the CO2 volume concentration ([CO2]) after dilution. dill ), the total dilution factor DF of the bypass dilution module 2 and the first dilution module can be inverted using formula (1).

[0099]

[0100] The multi-component analysis module includes five branches to respectively realize non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection:

[0101] The first branch is directly introduced into the nvPM mass concentration analyzer 61, which measures the mass concentration of non-volatile particulate matter based on the charge transfer principle.

[0102] After the second branch completes the stripping of volatile substances through the volatile particle remover 66 (VPR) and dilution with the filtered dilution gas (generally air) input from the second gas storage tank 693, it is connected to the nvPM number concentration analyzer 62 to realize particle number concentration detection.

[0103] The third branch is connected to the Black Carbon Analyzer 63 (AE33), which analyzes the mass concentration of brown carbon based on the characteristic absorption peak and is suitable for detecting incomplete combustion conditions of small engines.

[0104] The fourth branch is connected to the fast particle size spectrometer 64 (DMS500) to obtain particle size distribution data in real time through the electromigration classification technology.

[0105] After being purified by the first high-efficiency particulate filter 67 (HEPA), the fifth branch has its supply flow precisely controlled by a mass flow controller 68 (MFC) and is connected to a VOCs analyzer (for detecting the volume concentration of volatile organic compounds such as alkanes, alkenes, and aromatic hydrocarbons) and a CO2 analyzer.

[0106] Preferably, in order to control the flow of sample gas entering each analyzer, the VOCs and CO2 analyzer 65 is connected to a first air pump 691 , and the rapid particle size spectrometer 64 and the black carbon analyzer 63 are connected to a second air pump 692 .

[0107] In civil aviation engine emission testing, due to high combustion efficiency, the sample gas primarily consists of non-volatile particulate matter. To accurately characterize these emissions, the second air pump 692 is shut down, allowing the sample gas to enter the nvPM mass detector, nvPM number detector, and gaseous five-component analyzer 3 at a steady flow rate, ensuring the accuracy and reliability of the measurement data.

[0108] In contrast, small engines have low combustion efficiency, and incomplete combustion of fuel not only produces non-volatile particulate matter, but is also accompanied by the emission of a large amount of volatile substances. When characterizing its emission characteristics, the first air pump 691 and the second air pump 692 are turned on, and a flow meter is connected in series in front of the second air pump 692 to detect the flow rate, so that the sample gas enters the fast particle size spectrometer 64 at a stable flow rate (greater than 5slpm) to measure the particle size distribution and calculate the number concentration, the black carbon meter 63 to detect the mixed mass concentration of black carbon and brown carbon in the light-absorbing aerosol, and enters the VOCs analyzer to quantitatively detect the volume concentration of volatile organic compounds such as alkanes, alkenes, and aromatic hydrocarbons. Therefore, this application can achieve multi-dimensional and precise analysis of the emission characteristics of different types of engines to ensure the comprehensiveness and reliability of the detection data.

[0109] This application sets up a black carbon analyzer 63 to detect the concentrations of brown carbon (BrC) and black carbon (BC), providing accurate data support for optimizing combustion efficiency and reducing pollutant emissions. The gas analyzer monitors the dynamic changes of VOCs in real time by virtue of its rapid response characteristics, so that the emission control strategy can be dynamically adjusted based on high-timeliness data. The DMS500 analyzer simultaneously measures the concentration and particle size distribution of particulate matter, accurately quantifies the proportion of PM2.5 and PM1 and other particles of different particle sizes, and meets the quantitative requirements of airworthiness certification for particulate matter characteristics. The three work together to form a multi-dimensional detection system, taking into account the composition, concentration and particle size characteristics of gaseous and solid pollutants, and building a complete data chain from pollution source control to terminal certification.

[0110] In an optional embodiment, if Figure 2As shown, the bypass dilution module 2 includes a third isolation valve 21, a fourth isolation valve 22, a fifth isolation valve 23, a second diluter 24, a third flow splitter 25, a first flow combiner 26, a second diluent heater 27, a sixth isolation valve 28 and a third gas storage tank 29;

[0111] The air inlet of the third diverter 25 is connected to the first isolation valve 12, the first air outlet is connected to one end of the third isolation valve 21, and the second air outlet is connected to one end of the fourth isolation valve 22;

[0112] The other end of the third isolation valve 21 is connected to the first flow combiner 26;

[0113] The other end of the fourth isolation valve 22 is in communication with the first air inlet of the second diluter 24 , the second air inlet of the second diluter 24 is in communication with the second diluent heater 27 , the air outlet of the second diluter 24 is in communication with one end of the fifth isolation valve 23 , and the other end of the fifth isolation valve 23 is in communication with the first flow combiner 26 ;

[0114] The second diluent heater 27 is connected to the third gas storage tank 29 through the sixth isolation valve 28 . The third gas storage tank 29 stores filtered diluent gas.

[0115] Specifically, when measuring non-volatile particulate matter (nvPM), a modular dilution architecture can be used. The primary concentration is first controlled by the bypass dilution module 2, and then diluted by the jet-type first diluter 41. This two-stage dilution system can achieve dynamic adjustment from 1:10 to 1:100, ensuring that the concentration of particulate matter emitted by engines with different combustion characteristics adapts to the dynamic range of the downstream detection instrument, while effectively suppressing the condensation and thermophoretic deposition effects of particulate matter. Dilute high-concentration particles to the analyzer range (1-10,000 particles / cm 3 ) to solve the sensor overload caused by intermittent high-concentration emissions from different types of engines.

[0116] In actual application, when the dilution multiple needs to be increased, the bypass dilution module 2 can be enabled. The bypass dilution module 2 can be enabled through the following steps: switch the third isolation valve 21 to the closed position, the fourth to sixth isolation valves 28 are synchronously switched to the open position, and the gas path is adjusted. The sample gas flows through the fourth isolation valve 22 into the dilution branch of the bypass dilution module 2, and is mixed with the heated dilution gas in multiple stages. When the bypass dilution module 2 is disabled, the reverse control is performed: the third isolation valve 21 is switched to the fully open state, the fourth to sixth isolation valves 28 enter the closed state, and the sample gas is directly transported to the first diluter 41 through the main channel to complete the basic dilution treatment.

[0117] In an optional embodiment, if Figure 3As shown, the general aviation engine sample gas measurement device further includes a measurement module. The measurement module includes an air compressor 71, a particle generator 72, a drying pipe 73, a fourth diverter 74, a seventh isolation valve 75, and two condensation particle counters 76;

[0118] The air compressor 71, the particle generator 72, the drying pipe 73 and the fourth diverter 74 are connected in sequence;

[0119] The air compressor 71 is also connected to the second diluter 24 through the seventh isolation valve 75;

[0120] The two air outlets of the fourth diverter 74 are respectively connected to the condensation particle counter 76 and the second diluter 24;

[0121] The gas outlet of the second diluter 24 is communicated with another condensation particle counter 76 .

[0122] It is understandable that before applying the bypass dilution module 2, the dilution multiple of the bypass dilution module 2 can be measured and adjusted in advance. In a specific example, Figure 3 As shown, after the measurement module's gas circuit system is connected, the monodisperse aerosol particle generator 72 is activated to generate a test particle population. After dehumidification and drying through a silica gel drying tube 73, gas circuit diversion is performed. The system is allowed to enter a equilibrium phase, for example, by standing for three minutes until turbulent effects are eliminated and the particle concentration stabilizes. The first branch is directly connected to a condensation particle counter (CPC) 76 in full-flux mode to measure the baseline particle number concentration n1. The second branch is quantitatively diluted through a secondary diluter and then connected to the CPC to measure the diluted particle number concentration n2. Data from five parallel experiments is collected to eliminate the effects of transient fluctuations. The geometric mean values ​​of n1 and n2 are calculated, and the dilution ratio calibration value of the second diluter 24 is ultimately determined from the n1 / n2 ratio.

[0123] In another optional embodiment, as Figure 4 As shown, the bypass dilution module 2 includes a fifth flow divider 81 , a first electric regulating valve 82 , a second high efficiency particulate filter 83 (HEPA), a second electric regulating valve 84 and a second flow combiner 85 .

[0124] The air inlet of the fifth diverter 81 is connected to the first isolation valve 12, the first air outlet is connected to one end of the first electric regulating valve 82, and the second air outlet is connected to one end of the second high-efficiency particulate filter 83;

[0125] The other end of the first electric regulating valve 82 is in communication with the second flow combiner 85 , the other end of the second HEPA filter 83 is in communication with one end of the second electric regulating valve 84 , and the other end of the second electric regulating valve 84 is in communication with the second flow combiner 85 .

[0126] It is understood that the bypass dilution module 2 of the present application can also be implemented using components such as an electric control valve and a second high-efficiency particulate filter 83. In this embodiment, when the system does not enable the bypass dilution function, the opening of the first electric control valve 82 is controlled to 100%, and the opening of the second electric control valve 84 is controlled to 0%. At this time, the sample gas will be directly delivered to the first diluter 41 through the main channel to complete the basic dilution process.

[0127] When the system needs to increase the dilution factor, the bypass dilution function module is activated. In this mode, the opening of the first electric control valve 82 is gradually reduced from 100% to a lower limit of 30%, and the opening of the second electric control valve 84 is gradually increased from 0%. This operation, through the staged adjustment of the openings of the first and second electric control valves 82 and 84, removes the flow of the particulate matter air path through the second high-efficiency particulate filter 83 to achieve the purpose of diluting the particulate matter concentration. The system can achieve dynamic and precise control of the dilution factor of the bypass dilution device.

[0128] When the bypass dilution device is activated, the dilution process is completed by the entire bypass dilution system. Therefore, when calibrating the dilution factor of this alternative solution, the bypass dilution device must be calibrated as a whole system.

[0129] like Figure 5 As shown, after the measurement module is connected, the monodisperse aerosol particle generator 72 is started to generate a test particle group, which is then dehumidified and dried through the silica gel drying tube 73 before gas path diversion is implemented. The system enters the equilibrium stage, for example, after standing for 3 minutes, and after the turbulent effect is eliminated and the particle concentration is stable, the first branch is directly connected to the CPC in full-flux mode to measure the baseline particle number concentration n1; the second branch is diluted by the bypass dilution device and connected to the CPC to measure the diluted particle number concentration n2. Through five sets of parallel experimental data collection (eliminating the influence of transient fluctuations), the geometric mean values ​​of n1 and n2 are calculated respectively, and finally the calibration value of the comprehensive dilution factor of the bypass dilution module 2 is determined by the ratio n1 / n2.

[0130] Based on the same principle, Figure 6 As shown, the present application also discloses an application method of the general aviation engine sample gas measurement device as described in this embodiment. The method includes:

[0131] S100: Setting the bypass dilution module 2 to a first ratio of dilution or no dilution based on the dilution multiple of the sample gas;

[0132] S200: Outputting the sample gas obtained by the sampling rake 1 to the gaseous five-component analyzer 3 to detect the volume concentrations of CO, CO2, HC, O2, and NO in real time;

[0133] S300: The sample gas obtained by the sampling rake 1 is output to the first dilution module and the multi-component analysis module in sequence through the bypass dilution module 2 so that the multi-component analysis module performs non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection on the sample to be detected output by the first dilution module.

[0134] Since the principle of solving the problem by this method is similar to that of the above device, the implementation of this method can refer to the implementation of the device and will not be repeated here.

[0135] Based on the same principle, the present application also discloses an aircraft engine high-altitude simulation system, which includes the general aircraft engine sample gas measurement device described in this embodiment.

[0136] Since the principle of solving the problem by 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.

[0137] Since the principle of solving the problem by this system is similar to that of the above method, the implementation of this system can refer to the implementation of the method and will not be repeated here.

[0138] The systems, devices, modules, or units described in the above embodiments may be implemented by computer chips or entities, or by products having certain functions. A typical implementation device is a computer device. Specifically, the computer device may be, for example, a personal computer, a laptop computer, a cellular phone, a camera phone, a smartphone, a personal digital assistant, a media player, a navigation device, an email device, a game console, a tablet computer, a wearable device, or a combination of any of these devices.

[0139] In a typical example, a computer device specifically includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the method executed by the client as described above is implemented, or when the processor executes the program, the method executed by the server as described above is implemented.

[0140] Reference below Figure 7 , which shows a structural diagram of a computer device 600 suitable for implementing an embodiment of the present application.

[0141] like Figure 7As shown, computer device 600 includes a central processing unit (CPU) 601, which can perform various appropriate tasks and processes according to a program stored in a read-only memory (ROM) 602 or a program loaded from a storage portion 608 into a random access memory (RAM) 603. Various programs and data required for the operation of system 600 are also stored in RAM 603. CPU 601, ROM 602, and RAM 603 are connected to each other via a bus 604. An input / output (I / O) interface 605 is also connected to bus 604.

[0142] The following components are connected to the I / O interface 605: an input section 606 including a keyboard, a mouse, and the like; an output section 607 including devices such as a cathode ray tube (CRT), a liquid crystal display (LCD), and a speaker; a storage section 608 including devices such as a hard disk; and a communication section 609 including a network interface card such as a LAN card or a modem. The communication section 609 performs communication processing via a network such as the Internet. A drive 610 is also connected to the I / O interface 605 as needed. Removable media 611, such as a magnetic disk, an optical disk, a magneto-optical disk, or a semiconductor memory, is installed in the drive 610 as needed, so that computer programs read therefrom can be installed in the storage section 608 as needed.

[0143] In particular, according to embodiments of the present invention, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of the present invention include a computer program product comprising a computer program tangibly embodied on a machine-readable medium, the computer program including program code for executing the methods illustrated in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication portion 609 and / or installed from removable media 611.

[0144] Computer-readable media includes permanent and non-permanent, removable and non-removable media that can be implemented by any method or technology to store information. The information can be computer-readable instructions, data structures, program modules or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technology, compact disc read-only memory (CD-ROM), digital versatile disc (DVD) or other optical storage, magnetic cassettes, magnetic disk storage or other magnetic storage devices or any other non-transmission media that can be used to store information that can be accessed by a computing device. As defined herein, computer-readable media does not include transitory computer-readable media (transitory media), such as modulated data signals and carrier waves.

[0145] For the convenience of description, the above devices are described as being divided into various units according to their functions. Of course, when implementing this application, the functions of each unit can be implemented in the same or multiple software and / or hardware.

[0146] The present invention is described with reference to flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowcharts and / or block diagrams, as well as combinations of processes and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowcharts and / or block diagrams. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0147] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0148] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 The steps for the function specified in one or more boxes.

[0149] It should also be noted that the terms "comprises," "includes," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, method, commodity, or apparatus that includes a series of elements includes not only those elements but also other elements not explicitly listed, or includes elements inherent to such process, method, commodity, or apparatus. In the absence of further limitations, an element defined by the phrase "comprises a ..." does not exclude the presence of other identical elements in the process, method, commodity, or apparatus that includes the element.

[0150] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware. Furthermore, the present application may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to magnetic disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0151] The present application may be described in the general context of computer-executable instructions executed by a computer, such as program modules. Generally, program modules include routines, programs, objects, components, data structures, etc. that perform specific tasks or implement specific abstract data types. The present application may also be practiced in distributed computing environments where tasks are performed by remote processing devices connected through a communications network. In a distributed computing environment, program modules may be located in local and remote computer storage media, including storage devices.

[0152] 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.

[0153] 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 general aviation engine gas sample measuring device, characterized in that: include: a bypass dilution module, connected to the sampling rake, capable of diluting the sample gas obtained by the sampling rake by a first ratio or not diluting the sample gas; a gaseous five-component analyzer, connected to the sampling rake, for detecting gaseous components of the sample gas output by the sampling rake; a first dilution module, connected to the bypass dilution module, for diluting the exhaust sample gas output by the bypass dilution module by a second ratio to obtain a sample to be tested; The multi-component analysis module is used to perform non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection on the sample to be detected output by the first dilution module.

2. The general aviation engine sample gas measuring device according to claim 1, characterized in that: Also included is a first flow diverter, a first isolation valve, and a pressure control valve; The sampling rake is communicated with the air inlet of the first flow splitter, and the three air outlets of the first flow splitter are communicated with the gaseous five-component analyzer, the bypass dilution module and the pressure control valve respectively.

3. The general aviation engine sample gas measuring device according to claim 1, characterized in that: The first dilution module includes a first diluter, a first diluent heater, a second isolation valve and a first gas storage tank; One air inlet of the first diluter is in communication with the bypass dilution device, and the other air inlet is in communication with the diluent heater, and the diluent heater is in communication with the first air storage tank via the second isolation valve; The first gas storage tank stores filtered dilution gas.

4. The general aviation engine sample gas measuring device according to claim 1, characterized in that: Also included is a cyclone separator and a second splitter; The first dilution module is communicated with one end of the cyclone separator, the other end of the cyclone separator is communicated with the air inlet of the second splitter, and the multiple air outlets of the second splitter are communicated with the multi-component analysis module.

5. The general aviation engine gas sample measuring device according to claim 4, characterized in that: The first dilution module is connected to the second diverter via a heat tracing pipe; The heating pipe includes a detachably connected base section, a first extension section, and a second extension section.

6. The general aviation engine sample gas measuring device according to claim 4, characterized in that: The multi-component analysis module includes an nvPM mass concentration analyzer, an nvPM number concentration analyzer, a black carbon analyzer, a rapid particle size spectrometer, and a VOCs and CO2 analyzer, which are respectively connected to the multiple gas outlets of the second splitter; wherein the nvPM number concentration analyzer is connected to the air outlet of the second splitter through a volatile particle remover; The VOCs and CO2 analyzers are connected to the gas outlet of the second splitter through a first high-efficiency particulate filter and a mass flow controller in sequence.

7. The general aviation engine gas sample measuring device according to claim 2, characterized in that: The bypass dilution module includes a third isolation valve, a fourth isolation valve, a fifth isolation valve, a second diluter, a third flow divider, a flow combiner, a second diluent heater, a sixth isolation valve and a third gas storage tank; The air inlet of the third diverter is connected to the first isolation valve, the first air outlet is connected to one end of the third isolation valve, and the second air outlet is connected to one end of the fourth isolation valve; The other end of the third isolation valve is communicated with the flow combiner; The other end of the fourth isolation valve is communicated with the first air inlet of the second diluter, the second air inlet of the second diluter is communicated with the second diluent heater, the air outlet of the second diluter is communicated with one end of the fifth isolation valve, and the other end of the fifth isolation valve is communicated with the flow combiner; The second diluent heater is connected to the third gas storage tank through the sixth isolation valve, and the third gas storage tank stores filtered dilution gas; or the bypass dilution module includes a third diverter, a first electric regulating valve, a second high-efficiency particulate filter, a second electric regulating valve and a combiner; The air inlet of the third diverter is communicated with the first isolation valve, the first air outlet is communicated with one end of the first electric regulating valve, and the second air outlet is communicated with one end of the second high-efficiency particulate filter; The other end of the first electric regulating valve is communicated with the flow combiner, the other end of the second high efficiency particulate filter is communicated with one end of the second electric regulating valve, and the other end of the second electric regulating valve is communicated with the flow combiner.

8. The general aviation engine sample gas measuring device according to claim 7, characterized in that: Also included is a determination module; The measurement module includes an air compressor, a particle generator, a drying tube, a fourth flow divider, a seventh isolation valve, and two condensation particle counters; The air compressor, the particle generator, the drying pipe and the fourth diverter are connected in sequence; The air compressor is also connected to the seventh isolation valve and the second diluter in sequence; The two air outlets of the fourth diverter are respectively connected to one of the condensation particle counters and the second diluter; The gas outlet of the second diluter is communicated with another condensation particle counter.

9. An application method of the general aviation engine sample gas measurement device according to any one of claims 1 to 8, characterized in that: include: Determine the dilution factor of the sample gas; Setting the bypass dilution module to a first ratio of dilution or no dilution based on the dilution multiple; Outputting the sample gas obtained by the sampling rake to a gaseous five-component analyzer to detect the volume concentrations of CO, CO2, HC, O2, and NO in real time; The sample gas obtained by the sampling rake is output to the first dilution module and the multi-component analysis module in sequence through the bypass dilution module, so that the multi-component analysis module performs non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection on the sample to be detected output by the first dilution module.

10. An aircraft engine high altitude simulation system, characterized in that: The invention comprises the general aviation engine sample gas measuring device according to any one of claims 1 to 8.

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