CN112129538B - System and method for detecting tail gas emission of aircraft engine - Google Patents
System and method for detecting tail gas emission of aircraft engine Download PDFInfo
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- CN112129538B CN112129538B CN201910550020.9A CN201910550020A CN112129538B CN 112129538 B CN112129538 B CN 112129538B CN 201910550020 A CN201910550020 A CN 201910550020A CN 112129538 B CN112129538 B CN 112129538B
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- 238000005070 sampling Methods 0.000 claims abstract description 234
- 238000001514 detection method Methods 0.000 claims abstract description 109
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- 239000000523 sample Substances 0.000 claims abstract description 30
- 239000007789 gas Substances 0.000 claims description 97
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 claims description 39
- 239000013618 particulate matter Substances 0.000 claims description 22
- 238000012546 transfer Methods 0.000 claims description 20
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 claims description 16
- 239000003344 environmental pollutant Substances 0.000 claims description 13
- 231100000719 pollutant Toxicity 0.000 claims description 13
- 239000004215 Carbon black (E152) Substances 0.000 claims description 10
- 229910002090 carbon oxide Inorganic materials 0.000 claims description 10
- 229930195733 hydrocarbon Natural products 0.000 claims description 10
- 150000002430 hydrocarbons Chemical class 0.000 claims description 10
- 230000001105 regulatory effect Effects 0.000 claims description 10
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- 238000003921 particle size analysis Methods 0.000 claims description 8
- 239000002245 particle Substances 0.000 claims description 7
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- MGWGWNFMUOTEHG-UHFFFAOYSA-N 4-(3,5-dimethylphenyl)-1,3-thiazol-2-amine Chemical compound CC1=CC(C)=CC(C=2N=C(N)SC=2)=C1 MGWGWNFMUOTEHG-UHFFFAOYSA-N 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 238000003916 acid precipitation Methods 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/10—Testing internal-combustion engines by monitoring exhaust gases or combustion flame
- G01M15/102—Testing internal-combustion engines by monitoring exhaust gases or combustion flame by monitoring exhaust gases
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N33/00—Investigating or analysing materials by specific methods not covered by groups G01N1/00 - G01N31/00
- G01N33/0004—Gaseous mixtures, e.g. polluted air
- G01N33/0009—General constructional details of gas analysers, e.g. portable test equipment
- G01N33/0027—General constructional details of gas analysers, e.g. portable test equipment concerning the detector
- G01N33/0031—General constructional details of gas analysers, e.g. portable test equipment concerning the detector comprising two or more sensors, e.g. a sensor array
- G01N33/0032—General constructional details of gas analysers, e.g. portable test equipment concerning the detector comprising two or more sensors, e.g. a sensor array using two or more different physical functioning modes
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Combustion & Propulsion (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Medicinal Chemistry (AREA)
- Analytical Chemistry (AREA)
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- General Health & Medical Sciences (AREA)
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- Pathology (AREA)
- Sampling And Sample Adjustment (AREA)
Abstract
The invention provides an aircraft engine exhaust emission detection system, comprising: a sampling bracket with a plurality of sampling holes; the sampling probes are located in the sampling holes in a one-to-one correspondence manner; the sampling pipelines are connected with the sampling holes in a one-to-one correspondence manner, and each sampling pipeline is provided with a sampling valve; the transmission pipeline is connected with the plurality of sampling pipelines; the diverter valve is connected to one end of the transmission pipeline far away from the sampling pipeline and is used for diverting tail gas in the transmission pipeline into a transmission branch, and the transmission branch at least comprises a first transmission branch and a second transmission branch; the on-line analysis device is at least connected with the first transmission branch; and the off-line analysis device is at least connected with the second transmission branch. The invention can collect the exhaust gas of the aircraft engine in real time, and carries out omnibearing analysis through the online analysis device and the offline analysis device so as to accurately know the component composition of the exhaust gas of the aircraft engine, and has the advantages of simple operation, more efficient sampling and more accurate analysis.
Description
Technical Field
The invention relates to the field of civil aviation engine tail gas detection, in particular to an aircraft engine tail gas emission detection system and method.
Background
With the rapid development of economy, the demand for aviation traffic continues to increase. The average annual growth rate of aviation traffic demands in recent years is about 5%. One problem with the continued growth of aviation traffic demand is the increase in aircraft pollutant emissions. Although the international civil aviation organization regulates emissions of pollutants such as nitrogen oxide (NO X) gas more and more strictly, carbon dioxide emissions of global airlines are still rising, and non-carbon dioxide emissions are also attracting more and more attention, and these gases have been generally regarded as one of the leading causes of global climate environment deterioration (including global warming and acid rain increase, etc.). However, at present, a scientific and effective system is not available, so that potential influence of the emission of combustion products of an aircraft engine on the climate can be accurately researched, and one of the difficulties is that an effective detection means is not available for accurately detecting the output of various combustion products of the aircraft engine at the cruising altitude. If the composition of the tail gas discharged by the aircraft engine, such as the quantity and quality of smoke particles in the tail gas, cannot be known, and the relationship between the physicochemical properties and the engine running environment (idle speed, take-off, climb, approach, cruise, etc.) cannot be determined and characterized, it is difficult to provide a basis for researching an aviation emission list, and it is more difficult to make effective prevention and treatment measures for the atmospheric pollution.
Disclosure of Invention
In view of the above-mentioned drawbacks of the prior art, the present invention aims to provide an exhaust emission detection system and an exhaust emission detection method for an aircraft engine, which are used for solving the problems that in the prior art, no effective detection means can detect the exhaust emission of the aircraft engine, so that it is difficult to study the influence of the exhaust emission of the aircraft engine on the climate, and it is difficult to create an effective scheme for preventing and treating the air pollution.
To achieve the above and other related objects, the present invention provides an aircraft engine exhaust emission detection system, comprising:
The sampling bracket is provided with a plurality of sampling holes;
the sampling probes are located in the sampling holes in a one-to-one correspondence manner;
The sampling pipelines are connected with the sampling holes in a one-to-one correspondence manner, and each sampling pipeline is provided with a sampling valve;
The transmission pipeline is connected with the plurality of sampling pipelines;
The diverter valve is connected to one end, far away from the sampling pipeline, of the transmission pipeline and is used for diverting tail gas in the transmission pipeline into a transmission branch, and the transmission branch at least comprises a first transmission branch and a second transmission branch;
The on-line analysis device is at least connected with the first transmission branch and is used for on-line analysis of the tail gas in the first transmission branch;
and the off-line analysis device is at least connected with the second transmission branch and is used for off-line analysis of the tail gas in the second transmission branch.
Optionally, the aircraft engine exhaust emission detection system further comprises a pressure sensor, a pressure regulating valve and a flow rate sensor, which are all located on the transmission pipeline.
Optionally, the exhaust emission detection system of the aircraft engine further comprises a heat shield located at the periphery of the plurality of sampling pipelines, and the heat shield is used for maintaining the temperature of the sampling pipelines at a required temperature so as to prevent the exhaust from settling and condensing in the sampling pipelines.
Optionally, the aircraft engine exhaust emission detection system comprises a first temperature controller, a second temperature controller and a third temperature controller; the first temperature controller is located on the transmission pipeline, the second temperature controller is located on the first transmission branch, and the third temperature controller is located on the second transmission branch.
Optionally, the online analysis device includes a total hydrocarbon detection module, a nitrogen oxide detection module, and a carbon oxide detection module, where the total hydrocarbon detection module, the nitrogen oxide detection module, and the carbon oxide detection module are all connected with the first transmission branch; the off-line analysis device comprises a multi-stage particle size analysis module and a volatile organic compound analysis module, wherein the multi-stage particle size analysis module and the volatile organic compound analysis module are connected with the second transmission branch.
Optionally, the online analysis device further comprises a particulate matter detection module for detecting the quantity and the quality of particulate matters in the tail gas; the off-line analysis device further comprises a four-channel particle analysis module; the tail gas emission detection system of the aircraft engine further comprises a third transmission branch and a fourth temperature controller positioned on the third transmission branch, the third transmission branch is connected with one end, far away from the transmission pipeline, of the diverter valve, and the particulate matter detection module and the four-channel particulate matter analysis module are connected with the third transmission branch.
Optionally, the aircraft engine exhaust emission detection system further comprises a first filter and a second filter, wherein the first filter is positioned on the first transmission branch between the diverter valve and the online analysis device; the second filter is located on the second transfer branch between the diverter valve and the off-line analysis device.
Optionally, the sampling support is a liftable support, or the aircraft engine exhaust emission detection system further comprises a cushion block, and the cushion block is used for adjusting the height of the sampling support.
Optionally, the number of sampling holes is n×m, the n×m sampling holes are distributed on the sampling support in an array of n rows and m columns, the number of sampling pipelines is n×m, and the number of sampling valves is n×m, where n and m are integers greater than or equal to 2.
Optionally, the aircraft engine exhaust emission detection system further includes a plurality of control valves and a plurality of transfer pipelines, one end of each transfer pipeline is connected with all sampling pipelines where a single row or a single column is located, the other end of each transfer pipeline is connected with the transmission pipeline, and the plurality of control valves are located on the plurality of transfer pipelines in a one-to-one correspondence.
The invention also provides a method for detecting the tail gas emission of the aircraft engine, which comprises the following steps:
Providing the aircraft engine exhaust emission detection system according to any one of the above schemes, placing the sampling bracket at an exhaust outlet of an aircraft engine to be sampled, so that the sampling probe can collect exhaust emitted by the aircraft engine;
And opening or closing the sampling pipelines corresponding to different sampling probes so as to sample and analyze tail gas of the sampling holes corresponding to different positions of the air outlet of the aircraft engine.
Optionally, when the sampling holes and the sampling pipelines are 25, and the 25 sampling holes are distributed in an array of 5 rows and 5 columns on the sampling bracket, the sampling scheme of the detection method comprises one or more of the following schemes: sampling all or part of the sampling holes located on the symmetry axis of the array distribution, sampling the sampling holes located on the circumference direction with the center of the array distribution as the center of the circle, and sampling the sampling holes located on all or part of the array distribution.
Optionally, the detection method further comprises the step of calculating an emission factor of real-time emission of the aircraft engine pollutant based on the result of the sampling analysis in combination with the navigational speed of the aircraft corresponding to the aircraft engine, the exhaust gas amount and the fuel consumption rate of the aircraft engine.
As described above, the aircraft engine exhaust emission detection system and the detection method of the invention have the following beneficial effects: the invention can collect the exhaust gas of the aircraft engine in real time, and carries out omnibearing analysis through the online analysis device and the offline analysis device so as to accurately know the composition of the exhaust gas of the aircraft engine and help grasp the emission factors of the real-time emission of pollutants of the aircraft engine, thereby providing a basis for researching an aviation emission list and providing a basis for preventing and treating the atmospheric pollution. In addition, the invention can realize sampling analysis of exhaust gas at different positions of the aircraft exhaust through different combinations of the sampling holes, is beneficial to researching potential influence of non-uniformity of gas and particulate matter emission indexes generated by the engine exhaust on discrete points, and makes up the problems of insufficient sample analysis data quantity and the like existing in a single sampling mode, so that the analysis data obtained by adopting the invention is more convincing. The invention is suitable for detecting the emission of tail gas pollutants of engines of different types, and is beneficial to saving the cost and improving the working efficiency.
Drawings
Fig. 1 shows a schematic structural diagram of an aircraft engine exhaust emission detection system according to the invention.
Fig. 2 shows a schematic structural view of a sampling support according to the present invention.
Fig. 3 is a schematic structural diagram of the region a in fig. 1.
Fig. 4 shows a schematic diagram of an exhaust gas sampling of an aircraft engine using the aircraft engine exhaust gas emission detection system of the present invention.
Fig. 5 shows a flow chart of the method for detecting the exhaust emissions of an aircraft engine according to the invention.
Fig. 6 to 11 are schematic diagrams showing sampling positions during sampling analysis by using the method for detecting exhaust emission of an aircraft engine according to the present invention.
Description of element reference numerals
11. Sampling support
111. Sampling panel
112. Supporting frame
12. Sampling hole
13. Cushion block
14. Sampling probe
15. Sampling pipeline
16. Sampling valve
17. Transmission pipeline
18. Flow dividing valve
191. First transmission branch
192. Second transmission branch
193. Third transmission branch
211. Total hydrocarbon detection module
212. Nitrogen oxide detection module
213. Carbon oxide detection module
214. Particulate matter detection module
215. Computer with a memory for storing data
221. Multistage particle size analysis module
222. Volatile organic compound analysis module
223. Four-channel particle analysis module
224. Suction pump
23. Pressure sensor
24. Pressure regulating valve
25. Flow velocity sensor
26. Heat shield
271. First temperature controller
272. Second temperature controller
273. Third temperature controller
274. Fourth temperature controller
281. First filter
282. Second filter
29. Control valve
31. Transfer pipeline
41. Engine with a motor
S1-S2 steps
Detailed Description
Further advantages and effects of the present invention will become apparent to those skilled in the art from the disclosure of the present invention, which is described by the following specific examples.
Please refer to fig. 1 to 11. It should be understood that the structures, proportions, sizes, etc. shown in the drawings are for illustration purposes only and should not be construed as limiting the invention to the extent that it can be practiced, since modifications, changes in the proportions, or otherwise, used in the practice of the invention, are not intended to be critical to the essential characteristics of the invention, but are intended to fall within the spirit and scope of the invention. Also, the terms such as "upper", "lower", "left", "right", "middle" and "a" and the like are used in this specification for convenience of description, but are not intended to limit the scope of the invention, and the relative changes or modifications thereof are considered to be within the scope of the invention without any substantial technical changes.
As shown in fig. 1 to 3, the present invention provides an aircraft engine exhaust emission detection system, the detection system comprising: a sampling bracket 11, wherein a plurality of sampling holes 12 are formed on the sampling bracket 11; a plurality of sampling probes 14 located in the plurality of sampling holes 12 in a one-to-one correspondence; the sampling device comprises a plurality of sampling pipelines 15, wherein the sampling pipelines 15 are connected with the sampling holes 12 in a one-to-one correspondence manner, and each sampling pipeline 15 is provided with a sampling valve 16; a transmission line 17 connected to the plurality of sampling lines 15; the diverter valve 18 is connected to one end of the transmission pipeline 17 far away from the sampling pipeline 15, and is used for diverting the tail gas in the transmission pipeline 17 into a transmission branch, the transmission branch at least comprises a first transmission branch 191 and a second transmission branch 192, and the diverter valve 18 can separate the collection of the gas and the particulate matters in the tail gas, and has the function of mutually switching so as to realize multiple sampling modes of separately collecting the gas and the particulate matters or simultaneously collecting the gas and the particulate matters according to the requirement; the on-line analysis device is at least connected with the first transmission branch 191 and is used for on-line analysis of the tail gas in the first transmission branch 191; and the off-line analysis device is at least connected with the second transmission branch 192 and is used for performing off-line analysis on the tail gas in the second transmission branch 192.
The invention can collect the exhaust gas of the aircraft engine in real time, and carries out omnibearing analysis through the online analysis device and the offline analysis device so as to accurately know the composition of the exhaust gas of the aircraft engine and help grasp the emission factors of the real-time emission of pollutants of the aircraft engine, thereby providing a basis for researching an aviation emission list and providing a basis for preventing and treating the atmospheric pollution. In addition, the invention can realize sampling analysis of exhaust gas at different positions of the aircraft exhaust through different combinations of the sampling holes, is beneficial to researching potential influence of non-uniformity of gas and particulate matter emission indexes generated by the engine exhaust on discrete points, and makes up the problems of insufficient sample analysis data quantity and the like existing in a single sampling mode, so that the analysis data obtained by adopting the invention is more convincing. The invention is suitable for detecting the emission of tail gas pollutants of engines of different types, and is beneficial to saving the cost and improving the working efficiency.
As shown in fig. 2, in an example, the sampling support 11 is a stainless steel support, which includes a sampling panel 111 and a support bracket 112 for fixing the sampling panel 111, and the support bracket 112 is used for preventing the sampling support 11 from being blown down due to a high wind speed of an engine exhaust port during sampling. The sampling holes 12 are positioned on the sampling panel 111, and are preferably uniformly distributed at intervals on the sampling panel 111, and the sizes of all the sampling holes 12 are preferably uniform; the sampling panel 111 is opposite to the exhaust outlet of the aircraft engine 41 to be sampled in the sampling process; the size of the sampling panel 111 and the number and size of the sampling holes 12 may be set as required; the sampling panel 111 is preferably circular or square in shape and may be the same size as or scaled down in size from the exhaust port of the aircraft engine 41 to be sampled, such as 1/2,1/3,1/4 or less of the exhaust port area. The circular or square sampling panel 111 is more favorable for uniform arrangement of the sampling holes 12, and is favorable for realizing subsequent sampling of different positions of the exhaust outlet through the combination of opening or closing of the sampling holes 12.
The support 112 is preferably a tripod. In an example, the sampling support 11 may be a fixed height, so the exhaust emission detection system of the aircraft engine may further include a cushion block 13, for example, a cushion block 13 made of a large-mass material such as iron or lead, and the height of the cushion block 13 may be set as required or the cushion block 13 may be multiple blocks, so that the height of the sampling support 11 from the aircraft engine 41 to be sampled is adjusted through the setting of the cushion block 13; in another example, the sampling stand 11 may be a liftable stand, which is not strictly limited in this embodiment.
As an example, the plurality of sampling probes 14 are disposed one by one in the sampling hole 12 to sample exhaust gas of the aircraft engine 41 into the sampling hole 12, and the sampling probes 14 may protrude outward from the sampling hole 12. The size of the sampling probe 14 is preferably no greater than the size of the sampling bore 12. In one example, the sampling probe 14 has a diameter of 0.8-1.2 mm.
The greater the number of sampling apertures 12, the more advantageous it is to achieve a diverse combination of sampling locations, the plurality of sampling apertures 12 preferably being distributed in an array on the sampling panel 111. As an example, the number of sampling holes 12 is n×m (the number of sampling probes 14 is n×m, respectively), the number of n×m sampling holes 12 is distributed in an array of n rows and m columns on the sampling support 11, the number of sampling pipes 15 is n×m, and the number of sampling valves 16 is n×m, where n and m are integers equal to or greater than 2 and the n and m are preferably the same, and in a further example, the n and m are preferably equal to or greater than 5.
The sampling line 15 is preferably an anti-adsorption teflon tube, preferably having a diameter of 4 to 8.5mm.
The transmission pipeline 17 is preferably a polytetrafluoroethylene pipeline so as to play a role in heat insulation and adsorption prevention.
As an example, the exhaust emission detection system of the aircraft engine further comprises a pressure sensor 23, a pressure regulating valve 24 and a flow rate sensor 25, all located on the transmission pipeline 17; the pressure sensor 23 is used for detecting the gas pressure in the transmission line 17; the pressure regulating valve 24 may be connected to the pressure sensor 23, so as to regulate the pressure in the transmission pipeline 17 according to the detection result of the pressure sensor 23 and the combination requirement, so that the gas pressure meets the detection requirement; the flow rate sensor 25 is used for detecting the flow rate of the gas in the transmission pipeline 17; the relative positions of the pressure sensor 23, the pressure regulating valve 24 and the flow rate sensor 25 are not strictly sequential, but in a preferred example, the pressure sensor 23 may be located at one end of the transmission pipeline 17 close to the diverter valve 18, the flow rate sensor 25 is located at one side of the pressure sensor 23 away from the diverter valve 18, and the pressure regulating valve 24 is located between the flow rate sensor 25 and the pressure sensor 23, so as to timely regulate the pressure regulating valve 24 according to the detection result of the flow rate sensor 25, and timely detect the pressure in the transmission pipeline 17 through the pressure sensor 23, so as to ensure that the gas pressure meets the detection requirement.
As an example, the aircraft engine exhaust emission detection system further comprises a heat shield 26 located at the periphery of the plurality of sampling pipes 15, i.e. the heat shield 26 covers all the sampling pipes 15 for maintaining the temperature of the sampling pipes 15 at a desired temperature to prevent sedimentation and condensation of exhaust gases in the sampling pipes 15; the heat shield 26 may be made of aluminum plating.
As an example, the aircraft engine exhaust emission detection system includes a first thermostat 271, a second thermostat 272, and a third thermostat 273; the first temperature controller 271 is located on the transmission line 17, the second temperature controller 272 is located on the first transmission branch 191, and the third temperature controller 273 is located on the second transmission branch 192. The temperature controller is used for controlling the temperature to be at a required temperature, and the temperature controller can comprise a temperature sensing unit and a heating unit inside the temperature controller, and the heating unit is started timely according to the temperature sensed by the temperature sensing unit and the temperature is controlled to be at a required level according to the requirement. The first temperature controller 271, the second temperature controller 272 and the third temperature controller 273 may be identical in type and may be located inside or outside the corresponding pipeline according to different specific structures.
As an example, the online analysis device includes a total hydrocarbon detection module 211, a nitrogen oxide detection module 212, and a carbon oxide detection module 213, where the total hydrocarbon detection module 211, the nitrogen oxide detection module 212, and the carbon oxide detection module 213 are all connected to the first transmission branch 191; the offline analysis device comprises a multi-stage particle size analysis module 221 and a volatile organic compound analysis module 222, wherein the multi-stage particle size analysis module 221 and the volatile organic compound analysis module 222 are connected with the second transmission branch 192.
As an example, the total hydrocarbon detection module 211 may employ a FID analyzer, the carbon oxide detection module 213 may employ an NDIR analyzer, and the nitrogen oxide detection module 212 may employ a CLD analyzer. Further, the carbon oxide detection module 213 may include a CO (carbon monoxide) detection unit and a CO 2 (carbon dioxide) detection unit, and thus the carbon oxide detection module 213 may be two; the nitrogen oxide detection module 212 may include a NO (nitric oxide) detection unit and a NO 2 (nitrogen dioxide) detection unit, so the nitrogen oxide detection module 212 may also detect two nitrogen-containing gases simultaneously, either in two or with a single device; the exhaust gas temperature detected by the nox detection module 212 and the nox detection module 213 is typically 55 to 75 ℃ and the exhaust gas temperature to be detected by the total hydrocarbon detection module 211 is typically 150 to 170 ℃, so that the first transmission branch 191 may further be divided into a plurality of branches (not shown) by a three-way valve (not shown) to be connected to the total hydrocarbon detection module 211, the nox detection module 213 and the nox detection module 212, respectively, and temperature controllers may be provided on these corresponding branches to adjust the temperatures of the corresponding branches, respectively. It should be noted that, in the present embodiment, the aforementioned multiple on-line analysis modules may be connected to the same computer 215 or each connected to a different computer 215, but the on-line analysis is not strictly limited, but from the factors of cost and structural simplicity, it is preferable to connect to the same computer 215 for on-line analysis, the data analyzed by each on-line analysis module is displayed in real time in the computer 215 and stored in the computer 215, and the aforementioned pressure sensor 23, pressure regulating valve 24, flow rate sensor 25, first temperature controller 271, second temperature controller 272 and third temperature controller 273 may be connected to the computer 215 to achieve timely storage of the data and facilitate subsequent further analysis, and the control of the modules to be controlled (such as controlling the operations of multiple temperature controllers by the computer 215) may also be performed based on the computer 215.
As an example, the multi-stage particle size analysis module 221 may use a MOUDI sampler, such as a MOUDI impact type classification sampler manufactured by MSP, to collect particles in the exhaust gas in a size separation manner, so as to more effectively understand the morphology and chemical composition of the particles in the exhaust gas; the volatile organic compound analysis module 222 can adopt SUMMA tanks, can realize online and offline trace volatile organic compound measurement, and adopts the principle that a refrigeration enrichment device adopts an electric refrigeration mode to trap target compounds at a low temperature of-150 ℃, and rapidly heats the target compounds to 100 ℃ during thermal analysis, and then samples enter a GC-MS for analysis.
In an example, the online analysis device further includes a particulate matter detection module 214 for detecting the amount and quality of particulate matters in the exhaust gas, where the particulate matter detection module 214 can implement rapid measurement of particle size distribution of particulate matters, and can test the dynamics behavior of particulate matters in the exhaust gas discharged from the aircraft engine 41 in a transient cycle manner; the off-line analysis device further comprises a four-way particulate matter analysis module 223; the exhaust emission detection system of the aircraft engine further comprises a third transmission branch 193 and a fourth temperature controller 274 positioned on the third transmission branch 193, wherein the third transmission branch 193 is connected with one end of the diverter valve 18, which is far away from the transmission pipeline 17, and the particulate matter detection module 214 and the four-channel particulate matter analysis module 223 are both connected with the third transmission branch 193; the four-channel particulate matter analysis module can adopt a four-channel particulate matter sampler which is provided with 4 sampling channels, can realize the homologous collection of 4 samples, is internally provided with 4 independent air channels (4 air extracting pumps 224,4 flow sensors and 4 filter membrane clamps), and can simultaneously or independently implement constant-current sampling of each air channel; the particulate matter detection module 214 and the four-way particulate matter analysis module 223 are adopted to perform online and offline analysis, so that the particulate matters in the tail gas discharged by the aircraft engine can be comprehensively analyzed, the real-time discharge condition and the deposition condition of the tail gas can be known, and the real-time influence and the potential influence of the tail gas discharged by the aircraft engine on the atmospheric environment and the climate can be analyzed.
The analysis of the particulate matter is typically performed in a room temperature environment (ambient temperature) so that the temperature of the gas in the third transfer branch 193 can be controlled to room temperature by providing the fourth temperature controller 274.
As an example, the aircraft engine exhaust emission detection system further comprises a first filter 281 and a second filter 282, the first filter 281 being located on the first transfer branch 191 between the diverter valve 18 and the on-line analysis device; the second filter 282 is located on the second transfer branch 192 between the diverter valve 18 and the off-line analysis device; the first filter 281 and the second filter 282 may be the same or different in model numbers.
As an example, the exhaust emission detection system of the aircraft engine further includes a plurality of control valves 29 and a plurality of transfer pipelines 31, one end of the transfer pipeline 31 is connected to all the sampling pipelines 15 where a single row or a single column is located, the other end is connected to the transmission pipeline 17, and the plurality of control valves 29 are located on the plurality of transfer pipelines 31 in a one-to-one correspondence; the transfer pipeline 31 can also adopt a Teflon pipe; the control valve 29 may be a solenoid valve, and the connection relationship between the control valve 29 and the sampling valve 16 may be as shown in fig. 3 (fig. 3 corresponds to region a of fig. 1). I.e. all the sampling lines 15 in a single row or column (i.e. sampling holes 12) are connected to the same transfer line 31, and closing of all the sampling lines 15 in a single row or column is achieved by means of the control valves 29 provided on the corresponding transfer lines 31 (opening of a single sampling line 15 requires simultaneous cooperation of the control valves 29 and the sampling valves 16 located on that sampling line 15); through the arrangement, the sampling pipelines 15 can be rapidly switched in the sampling process, the tail gas at different positions is obtained through rapid porous position sampling and mixed to obtain the waste gas sample, so that the average value of the pollutant concentration discharged by the aircraft engine 41 is detected, the defect of sample analysis acquired in a single sampling mode is overcome, the potential influence of non-uniformity of gas and particulate matter discharge indexes generated by the exhaust port of the aircraft engine 41 on discrete points is very important to evaluation and research, and the data analyzed by the method provided by the invention is more convincing. The control valve 29 and the sampling valve 16 may all be connected to a controller (such as the computer 215) for automatic control by the controller, so that no manual operation by a worker in the field is required, and damage to the human body caused by exhaust gas can be avoided. In addition, according to the thrust of the aircraft engine 41, the gas and the particulate matters collected by the combination analysis of different sampling holes 12 can be studied, for example, when the thrust is 7%, the combination of 2 sampling holes 12 can be selected; when the thrust is 85%, a combination of 4 sampling holes 12 may be selected.
As shown in fig. 4, when the exhaust emission detection system for an aircraft engine of the present invention is used for sampling and analyzing, the sampling bracket 11 is placed at the exhaust air outlet of the aircraft engine 41 to be detected, so that the sampling panel 111 faces the exhaust air outlet, for example, the sampling probe 14 can start to detect and analyze at a position about 5 cm away from the exhaust air outlet, and the operation is very simple. The invention can be used for detecting the emission of tail gas pollutants of engines of different types, and is beneficial to saving the cost and improving the working efficiency.
As shown in fig. 5, the invention further provides a method for detecting exhaust emission of an aircraft engine, which comprises the following steps:
S01: providing the aircraft engine exhaust emission detection system according to any one of the above aspects, placing the sampling bracket 11 at an exhaust outlet of the aircraft engine 41 to be sampled, so that the sampling probe 14 can collect exhaust gas emitted by the aircraft engine 41;
s02: the sampling pipes 15 corresponding to the different sampling probes 14 are opened or closed to sample and analyze the exhaust gas of the sampling holes 12 corresponding to the different positions of the exhaust outlet of the aircraft engine 41.
Before the start of the detection, the sampling bracket 11 of the exhaust emission detection system of an aircraft engine according to any one of the foregoing aspects is placed at an exhaust down-hole (as shown in fig. 4) of the aircraft engine 41 to be detected, for example, the sampling probe 14 is located about 5cm from the exhaust down-hole; then, the opening or closing of different sampling pipelines 15 is controlled according to the requirement so as to obtain tail gas at different positions through different combinations of the opening or closing of different sampling holes 12 and mix the tail gas to obtain an exhaust gas sample; and as previously mentioned, the sampling lines 15 (i.e. sampling orifices 12), which are preferably located in a single row or column, are controlled by the same control valve 29 to achieve rapid switching of different sampling positions during sampling.
As an example, when the sampling holes 12 and the sampling pipes 15 are 25 and the 25 sampling holes 12 are distributed in an array of 5 rows and 5 columns on the sampling support 11, the sampling scheme of the detection method includes one or more of the following, preferably all of the following sampling schemes are adopted for sampling one by one to obtain a plurality of sampling samples, so as to help to improve the comprehensiveness and accuracy of analysis (the black marked sampling holes 12 represent the sampled sampling holes 12 in the figure):
1. as shown in fig. 6, the exhaust gas at the position corresponding to all the sampling holes 12 is sampled and analyzed to understand the overall exhaust condition (including the specific components and the content of different components of the exhaust gas, etc.) of the exhaust gas discharged by the aircraft engine 41;
2. As shown in fig. 7 to fig. 9, the exhaust gas at the position corresponding to the part of the sampling holes 12 on the symmetry axis of the array distribution is sampled, for example, 2 or more (preferably 3) of the exhaust gas discharged from the aircraft engine 41 is sampled and analyzed along the axes of 45 °, 135 ° and 225 ° in the clockwise direction, so as to analyze the exhaust conditions of the exhaust gas discharged from the aircraft engine 41 in different directions, and as the sampling process is continued (for example, before the aircraft takes off, during the engine start process or after the aircraft landing, during the engine shutdown process), the sampling process is helpful for researching the diffusion conditions of the exhaust gas discharged in different directions;
3. As shown in fig. 10, the exhaust gas at the position corresponding to the sampling hole 12 in the circumferential direction around the center of the array distribution is sampled and analyzed, for example, in fig. 10, the exhaust gas at the position corresponding to 8 sampling holes 12 around the periphery of the sampling hole 12 at the center position is sampled and analyzed; of course, in other examples, the exhaust gas at the positions corresponding to the 4 sampling holes 12 in the circumferential direction may be sampled and analyzed, which is not strictly limited in the present embodiment; by analyzing the distribution condition of the exhaust gas along the circumferential direction, the exhaust gas distribution condition from the center of the exhaust port to the edge can be studied;
4. As shown in fig. 11, the exhaust gas at the position corresponding to the sampling hole 12 on the local array distributed in the array manner is sampled and analyzed, for example, the exhaust gas at all the positions corresponding to the sampling holes 12 where adjacent rows or columns (2 rows, 3 rows or 4 rows, or 2 columns, 3 columns or 4 columns) are located is sampled and analyzed, so as to analyze the exhaust gas discharged from the single side of the discharge port.
The combination of the multiple sampling modes is adopted to realize sampling analysis on the exhaust gas at different positions of the aircraft exhaust, so that potential influence of non-uniformity of gas and particulate matter emission indexes generated by the engine exhaust on discrete points is studied, the problem of insufficient sample analysis data quantity and the like in a single sampling mode is solved, and the analysis data obtained by the method is more convincing.
As an example, the detection method further includes a step of calculating an emission factor of real-time emission of pollutants of the aircraft engine 41 based on the result of the sampling analysis in combination with the speed of the aircraft corresponding to the aircraft engine 41, the exhaust gas amount and the fuel consumption rate of the aircraft engine 41. This is not elaborated on as the calculation process is well known to the person skilled in the art. The data obtained by the detection method can provide basis for researching aviation emission list and further provide basis for preventing and treating air pollution.
Of course, the implementation of the above detection method is merely illustrative, and the setting of the sampling position may be selected according to different needs, for example, according to the specific type of the aircraft engine, which is not strictly limited in this embodiment.
In summary, the present invention provides an exhaust emission detection system of an aircraft engine, the detection system comprising: the sampling bracket is provided with a plurality of sampling holes; the sampling probes are located in the sampling holes in a one-to-one correspondence manner; the sampling pipelines are connected with the sampling holes in a one-to-one correspondence manner, and each sampling pipeline is provided with a sampling valve; the transmission pipeline is connected with the plurality of sampling pipelines; the diverter valve is connected to one end, far away from the sampling pipeline, of the transmission pipeline and is used for diverting tail gas in the transmission pipeline into a transmission branch, and the transmission branch at least comprises a first transmission branch and a second transmission branch; the on-line analysis device is at least connected with the first transmission branch and is used for on-line analysis of the tail gas in the first transmission branch; and the off-line analysis device is at least connected with the second transmission branch and is used for off-line analysis of the tail gas in the second transmission branch. The invention can collect the exhaust gas of the aircraft engine in real time, and carries out omnibearing analysis through the online analysis device and the offline analysis device so as to accurately know the composition of the exhaust gas of the aircraft engine and help grasp the emission factors of the real-time emission of pollutants of the aircraft engine, thereby providing a basis for researching an aviation emission list and providing a basis for preventing and treating the atmospheric pollution. In addition, the invention can realize sampling analysis of exhaust gas at different positions of the aircraft exhaust through different combinations of the sampling holes, is beneficial to researching potential influence of non-uniformity of gas and particulate matter emission indexes generated by the engine exhaust on discrete points, and makes up the problems of insufficient sample analysis data quantity and the like existing in a single sampling mode, so that the analysis data obtained by adopting the invention is more convincing. The invention is suitable for detecting the emission of tail gas pollutants of engines of different types, and is beneficial to saving the cost and improving the working efficiency. Therefore, the invention effectively overcomes various defects in the prior art and has high industrial utilization value.
The above embodiments are merely illustrative of the principles of the present invention and its effectiveness, and are not intended to limit the invention. Modifications and variations may be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the invention. Accordingly, it is intended that all equivalent modifications and variations of the invention be covered by the claims, which are within the ordinary skill of the art, be within the spirit and scope of the present disclosure.
Claims (8)
1. An aircraft engine exhaust emissions detection system, comprising:
The sampling bracket is provided with a plurality of sampling holes;
the sampling probes are located in the sampling holes in a one-to-one correspondence manner;
The sampling pipelines are connected with the sampling holes in a one-to-one correspondence manner, and each sampling pipeline is provided with a sampling valve;
The transmission pipeline is connected with the plurality of sampling pipelines;
The diverter valve is connected to one end, far away from the sampling pipeline, of the transmission pipeline and is used for diverting tail gas in the transmission pipeline into a transmission branch, and the transmission branch at least comprises a first transmission branch and a second transmission branch;
The on-line analysis device is at least connected with the first transmission branch and is used for on-line analysis of the tail gas in the first transmission branch;
the off-line analysis device is at least connected with the second transmission branch and is used for off-line analysis of the tail gas in the second transmission branch;
The on-line analysis device comprises a total hydrocarbon detection module, a nitrogen oxide detection module and a carbon oxide detection module, wherein the total hydrocarbon detection module, the nitrogen oxide detection module and the carbon oxide detection module are all connected with the first transmission branch; the off-line analysis device comprises a multi-stage particle size analysis module and a volatile organic compound analysis module, wherein the multi-stage particle size analysis module and the volatile organic compound analysis module are connected with the second transmission branch;
The online analysis device also comprises a particulate matter detection module for detecting the quantity and the quality of particulate matters in the tail gas; the off-line analysis device further comprises a four-channel particle analysis module; the tail gas emission detection system of the aircraft engine further comprises a third transmission branch and a fourth temperature controller positioned on the third transmission branch, the third transmission branch is connected with one end, far away from the transmission pipeline, of the diverter valve, and the particulate matter detection module and the four-way particulate matter analysis module are both connected with the third transmission branch;
The aircraft engine exhaust emission detection system further comprises a first filter and a second filter, wherein the first filter is positioned on the first transmission branch between the diverter valve and the online analysis device; the second filter is located on the second transfer branch between the diverter valve and the off-line analysis device;
The number of the sampling holes is n multiplied by m, the n multiplied by m sampling holes are distributed on the sampling support in an array mode of n rows and m columns, the number of the sampling pipelines is n multiplied by m, the number of the sampling valves is n multiplied by m, and n and m are integers which are greater than or equal to 2;
The aircraft engine tail gas emission detection system further comprises a plurality of control valves and a plurality of transfer pipelines, one end of each transfer pipeline is connected with all sampling pipelines where a single row or a single column is located, the other end of each transfer pipeline is connected with the transmission pipeline, and the control valves are located on the transfer pipelines in a one-to-one correspondence mode.
2. The aircraft engine exhaust emission detection system according to claim 1, wherein: the aircraft engine tail gas emission detection system further comprises a pressure sensor, a pressure regulating valve and a flow rate sensor, and the pressure sensor, the pressure regulating valve and the flow rate sensor are all located on the transmission pipeline.
3. The aircraft engine exhaust emission detection system according to claim 1, wherein: the aircraft engine exhaust emission detection system further comprises a heat shield which is positioned at the periphery of the sampling pipelines and used for maintaining the temperature of the sampling pipelines at a required temperature so as to prevent the exhaust from settling and condensing in the sampling pipelines.
4. The aircraft engine exhaust emission detection system according to claim 1, wherein: the aircraft engine tail gas emission detection system comprises a first temperature controller, a second temperature controller and a third temperature controller; the first temperature controller is located on the transmission pipeline, the second temperature controller is located on the first transmission branch, and the third temperature controller is located on the second transmission branch.
5. The aircraft engine exhaust emission detection system according to claim 1, wherein: the sampling support is a lifting support, or the aircraft engine exhaust emission detection system further comprises a cushion block, and the cushion block is used for adjusting the height of the sampling support.
6. An aircraft engine exhaust emission detection method, characterized in that the detection method comprises the steps of:
Providing an aircraft engine exhaust emission detection system according to any one of claims 1 to 5, placing the sampling support at an exhaust outlet of an aircraft engine to be sampled, so that the sampling probe can collect exhaust emitted by the aircraft engine;
And opening or closing the sampling pipelines corresponding to different sampling probes so as to sample and analyze tail gas of the sampling holes corresponding to different positions of the air outlet of the aircraft engine.
7. The method of claim 6, wherein when the sampling holes and the sampling lines are 25 and the 25 sampling holes are distributed in an array of 5 rows and 5 columns on the sampling support, the sampling scheme of the method comprises one or more of the following schemes: sampling all or part of the sampling holes located on the symmetry axis of the array distribution, sampling the sampling holes located on the circumference direction with the center of the array distribution as the center of the circle, and sampling the sampling holes located on all or part of the array distribution.
8. The detection method according to claim 6 or 7, characterized in that: the detection method further comprises the step of calculating an emission factor of real-time emission of pollutants of the aircraft engine based on the result of the sampling analysis and in combination with the navigational speed of the aircraft corresponding to the aircraft engine, the exhaust gas quantity and the fuel consumption rate of the aircraft engine.
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