CN209894487U - Aircraft engine exhaust emission detection system - Google Patents

Abstract

The utility model provides an aircraft engine exhaust emissions detecting system, include: a sampling support having a plurality of sampling apertures therein; the sampling probes are positioned in the sampling holes in a one-to-one correspondence manner; the sampling pipelines are correspondingly connected with the sampling holes one by one, and each sampling pipeline is provided with a sampling valve; the transmission pipeline is connected with the plurality of sampling pipelines; the flow dividing valve is connected to one end of the transmission pipeline, which is far away from the sampling pipeline, and is used for dividing the tail gas in the transmission pipeline into transmission branches, and each transmission branch at least comprises a first transmission branch and a second transmission branch; the online analysis device is connected with at least the first transmission branch; and the off-line analysis device is at least connected with the second transmission branch. The utility model discloses but real-time acquisition aircraft engine's exhaust tail gas carries out all-round analysis through online analytical equipment and off-line analytical equipment to the accurate component of understanding aircraft engine exhaust gas constitutes, easy operation, and the sampling is more high-efficient, and the analysis is more accurate.

Description

Aircraft engine exhaust emission detection system

Technical Field

The utility model relates to a civil aviation engine exhaust detection field, in particular to aircraft engine exhaust emission detecting system.

Background

With the rapid development of economy, the demand for air traffic continues to increase. Statistically, the annual average growth rate of air traffic demand in recent years is about 5%. One problem with the continuing growth in air traffic demand is the increase in the amount of pollutants emitted by aircraft. Despite the international civil aviation organization for Nitrogen Oxides (NO)_X) The regulation of the emission of pollutants such as gas is becoming more and more strict, but the emission of carbon dioxide from global airlines is still rising, and the emission of non-carbon dioxide is also drawing more and more attention, and the gas is widely regarded as one of the pioneers of the global climate environment deterioration (including global warming, acid rain increase and the like). However, at present, a scientific and effective system for accurately researching the potential influence of the emission of combustion products of the aircraft engine on the climate does not exist, and one of the difficulties is that an effective detection means for accurately detecting the output of various combustion products emitted by the aircraft engine at the cruising altitude does not exist. However, if the composition of the tail gas emitted 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 of the tail gas and the operating environment (idling, takeoff, climbing, approaching, cruising and the like) of the engine cannot be determined and represented, it is difficult to provide a basis for researching an aviation emission list and to make effective air pollution prevention and treatment strategies more difficult.

SUMMERY OF THE UTILITY MODEL

In view of the above-mentioned prior art's shortcoming, the utility model aims at providing an aircraft engine exhaust emission detecting system for there is not effectual detection means detectable aircraft engine's emission tail gas among the solution prior art, therefore is difficult to study aircraft engine emission tail gas and to the influence of weather, is difficult to make effectual atmosphere pollution prevention and treatment scheme scheduling problem.

In order to achieve the above objects and other related objects, the present invention provides an aircraft engine exhaust emission detection system, the detection system includes:

a sampling support having a plurality of sampling apertures therein;

the sampling probes are positioned in the sampling holes in a one-to-one correspondence manner;

the sampling pipes are connected with the sampling holes in a one-to-one correspondence mode, and each sampling pipe is provided with a sampling valve;

the transmission pipeline is connected with the plurality of sampling pipelines;

the flow dividing valve is connected to one end, far away from the sampling pipeline, of the transmission pipeline and is used for dividing tail gas in the transmission pipeline into transmission branches, and each transmission branch at least comprises a first transmission branch and a second transmission branch;

the online analysis device is at least connected with the first transmission branch and is used for performing online analysis on 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 carrying out off-line analysis on the tail gas in the second transmission branch.

Optionally, the aircraft engine exhaust emission detection system further includes a pressure sensor, a pressure regulating valve, and a flow rate sensor, all located on the transmission pipeline.

Optionally, the aircraft engine exhaust emission detection system further comprises a heat shield located at the periphery of the plurality of sampling pipes for maintaining the temperature of the sampling pipes at a desired temperature to prevent the exhaust gas from settling and condensing in the sampling pipes.

Optionally, the aircraft engine exhaust emission detection system includes a first temperature controller, a second temperature controller, and a third temperature controller; the first temperature controller is positioned on the transmission pipeline, the second temperature controller is positioned on the first transmission branch, and the third temperature controller is positioned 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, and the total hydrocarbon detection module, the nitrogen oxide detection module, and the carbon oxide detection module are all connected to the first transmission branch; the off-line analysis device comprises a multi-stage particle size analysis module and a volatile organic compound analysis module, and 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 quality of particulate matter in the exhaust gas; the off-line analysis device further comprises a four-channel particulate matter analysis module; the aircraft engine tail gas emission detection system further comprises a third transmission branch and a fourth temperature controller located 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, the first filter being located on the first transmission branch between the diverter valve and the online analysis device; the second filter is located on the second transport leg between the diverter valve and the off-line analysis device.

Optionally, the sampling support is a lifting support, or the aircraft engine exhaust emission detection system further includes a cushion block, and the cushion block is used for adjusting the height of the sampling support.

Optionally, the number of the 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 the sampling pipelines is n × m, and the number of the 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 to all the sampling pipelines in which a single row or a single column is located, the other end of each transfer pipeline is connected to the corresponding transmission pipeline, and the plurality of control valves are located on the plurality of transfer pipelines in a one-to-one correspondence manner.

As described above, the utility model discloses an aircraft engine exhaust emission detecting system has following beneficial effect: the utility model discloses but real-time acquisition aircraft engine's exhaust tail gas carries out all-round analysis through online analytical equipment and off-line analytical equipment to the accurate component of understanding aircraft engine exhaust gas constitutes, and the help masters the real-time emission factor who discharges of aircraft engine pollutant, thereby discharges the manifest and provides the foundation for research aviation, and more atmosphere pollution prevention and treatment provide the foundation. Furthermore, the utility model discloses can realize carrying out the sampling analysis to the exhaust tail gas of the different positions of aircraft discharge port through the different combinations of sampling hole, help studying the potential influence of the nonuniformity of engine gas vent production gas and particulate matter emission index to discrete point, compensate the not enough scheduling problem of sample analysis data volume that single sampling mode exists, make and adopt the utility model discloses the analytical data who obtains is more convincing. The utility model is suitable for an engine exhaust pollutant emission of different models detects, helps practicing thrift the cost and improves work efficiency.

Drawings

Fig. 1 shows a schematic structural diagram of the aircraft engine exhaust emission detection system of the present invention.

Fig. 2 shows a schematic structural diagram of the sampling support of the present invention.

Fig. 3 is a schematic structural view of the region a of fig. 1.

Fig. 4 shows the schematic diagram for sampling the exhaust gas of the aircraft engine by using the system for detecting the exhaust gas emission of the aircraft engine of the present invention.

Fig. 5 shows a flow chart of a method for detecting tail gas by using the system for detecting tail gas emission of an aircraft engine of the present invention.

Fig. 6 to 11 show for adopting the utility model discloses an aircraft engine exhaust emission detecting system carries out the sampling position schematic diagram in the exhaust gas detection process.

Description of the element reference numerals

11 sampling support

111 sampling panel

112 support frame

12 sampling hole

13 cushion block

14 sampling probe

15 sampling pipeline

16 sampling valve

17 transfer line

18 flow divider

191 a 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

221 multistage particle size analysis module

222 volatile organic compound analysis module

223 four-channel particulate matter analysis module

224 air pump

23 pressure sensor

24 pressure regulating valve

25 flow rate 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 transit pipeline

41 Engine

S1-S2

Detailed Description

The following description is provided for illustrative purposes, and other advantages and features of the present invention will become apparent to those skilled in the art from the following detailed description.

Please refer to fig. 1 to 11. It should be understood that the structure, ratio, size and the like shown in the drawings attached to the present specification are only used for matching with the content disclosed in the specification, so as to be known and read by those skilled in the art, and are not used for limiting the limit conditions that the present invention can be implemented, so that the present invention has no technical essential meaning, and any structure modification, ratio relationship change or size adjustment should still fall within the scope covered by the technical content disclosed in the present invention without affecting the function and the achievable purpose of the present invention. Meanwhile, the terms such as "upper", "lower", "left", "right", "middle" and "one" used in the present specification are for convenience of description, and are not intended to limit the scope of the present invention, and changes or adjustments of the relative relationship thereof may be made without substantial technical changes.

As shown in fig. 1 to 3, the utility model provides an aircraft engine exhaust emission detecting system, detecting system includes: a sampling support 11, wherein the sampling support 11 is provided with a plurality of sampling holes 12; a plurality of sampling probes 14, one-to-one located in the plurality of sampling apertures 12; the sampling pipes 15 are connected with the sampling holes 12 in a one-to-one correspondence manner, and each sampling pipe 15 is provided with a sampling valve 16; a transfer line 17 connected to the plurality of sampling lines 15; the diverter valve 18 is connected to one end of the transmission pipeline 17, which is far away from the sampling pipeline 15, and is used for diverting the tail gas in the transmission pipeline 17 into transmission branches, each transmission branch at least comprises a first transmission branch 191 and a second transmission branch 192, and the diverter valve 18 can collect and separate gas and particulate matters in the tail gas, so that a function of switching between the gas and particulate matters is achieved, and multiple sampling modes of collecting the gas and the particulate matters separately or simultaneously are achieved according to needs; the online analysis device is at least connected with the first transmission branch 191 and is used for performing online analysis on the tail gas in the first transmission branch 191; and the offline analysis device is at least connected with the second transmission branch 192 and is used for performing offline analysis on the tail gas in the second transmission branch 192.

The utility model discloses but real-time acquisition aircraft engine's exhaust tail gas carries out all-round analysis through online analytical equipment and off-line analytical equipment to the accurate component of understanding aircraft engine exhaust gas constitutes, and the help masters the real-time emission factor who discharges of aircraft engine pollutant, thereby discharges the manifest and provides the foundation for research aviation, and more atmosphere pollution prevention and treatment provide the foundation. Furthermore, the utility model discloses can realize carrying out the sampling analysis to the exhaust tail gas of the different positions of aircraft discharge port through the different combinations of sampling hole, help studying the potential influence of the nonuniformity of engine gas vent production gas and particulate matter emission index to discrete point, compensate the not enough scheduling problem of sample analysis data volume that single sampling mode exists, make and adopt the utility model discloses the analytical data who obtains is more convincing. The utility model is suitable for an engine exhaust pollutant emission of different models detects, helps practicing thrift the cost and improves work efficiency.

As shown in fig. 2, in an example, the sampling bracket 11 is a stainless steel bracket, which includes a sampling panel 111 and a support bracket 112 for fixing the sampling panel 111, and the support bracket 112 is used to prevent the sampling bracket 11 from being blown down due to high wind speed at the outlet of the engine during sampling. The sampling holes 12 are positioned on the sampling panel 111 and are preferably uniformly distributed on the sampling panel 111 at intervals, and the sizes of all the sampling holes 12 are preferably consistent; the sampling panel 111 faces the air outlet of the aircraft engine 41 to be sampled during sampling; the size of the sampling panel 111 and the number and size of the sampling apertures 12 can be set as desired; the sampling panel 111 is preferably circular or square in shape and may be of the same size as the exhaust outlet of the aircraft engine 41 to be sampled or of an equal reduction in the size of the exhaust outlet, such as 1/2, 1/3, 1/4 or less of the area of the exhaust outlet. The sampling panel 111 is round or square, which is more beneficial to the uniform arrangement of the sampling holes 12 and is beneficial to the subsequent sampling of different positions of the air outlet by the opening or closing combination of the sampling holes 12.

The support frame 112 is preferably a tripod. In an example, the sampling bracket 11 may be a fixed height, so that the aircraft engine exhaust emission detection system may further include a spacer 13, such as a spacer 13 made of a high-mass material such as iron or lead, where the height of the spacer 13 may be set as needed or the spacer 13 may be multiple pieces, so as to adjust the height of the sampling bracket 11 from the aircraft engine 41 to be sampled through the setting of the spacer 13; in another example, the sampling support 11 may be a lifting support, which is not 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 the 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 sampling probe 14 is preferably sized to be no larger than the sampling aperture 12. In one example, the sampling probe 14 has a diameter of 0.8 to 1.2 mm.

The greater the number of sampling holes 12, the more advantageous it is to achieve a versatile combination of sampling positions, the more preferably the plurality of sampling holes 12 are distributed in an array on the sampling panel 111. By way of example, the sampling apertures 12 are n × m (and correspondingly the sampling probes 14 are n × m), the n × m sampling apertures 12 are distributed on the sampling rack 11 in an array of n rows and m columns, the sampling lines 15 are n × m and the sampling valves 16 are n × m, where n and m are each an integer greater than or equal to 2 and preferably the same, and in further examples, n and m are preferably greater than or equal to 5.

The sampling pipeline 15 is preferably an anti-adsorption Teflon pipe, and the diameter of the sampling pipeline is preferably 4-8.5 mm.

The transmission pipeline 17 is preferably made of polytetrafluoroethylene, so that the effects of heat insulation and adsorption prevention are achieved.

As an example, the aircraft engine exhaust emission detection system further comprises a pressure sensor 23, a pressure regulating valve 24 and a flow rate sensor 25, all located on the transmission line 17; the pressure sensor 23 is used for detecting the gas pressure in the transmission pipeline 17; the pressure regulating valve 24 can be connected with the pressure sensor 23 to regulate the pressure in the transmission pipeline 17 according to the detection result of the pressure sensor 23 and the requirement, so that the gas pressure meets the detection requirement; the flow rate sensor 25 is used for detecting the gas flow rate 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 in strict sequence, but in a preferred example, the pressure sensor 23 may be located at one end of the transmission pipeline 17 close to the flow dividing valve 18, the flow rate sensor 25 is located at one side of the pressure sensor 23 far away from the flow dividing 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 adjust 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, and is used for maintaining the temperature of the sampling pipes 15 at a required temperature so as to prevent the exhaust gas from settling and condensing in the sampling pipes 15; the heat shield 26 may be an aluminum plate.

As an example, the aircraft engine exhaust emission detection system includes a first temperature controller 271, a second temperature controller 272, and a third temperature controller 273; the first thermostat 271 is located on the transmission line 17, the second thermostat 272 is located on the first transmission branch 191, and the third thermostat 273 is located on the second transmission branch 192. The temperature controller controls the temperature at a required temperature as the name implies, and the temperature controller can comprise a temperature sensing unit and a heating unit inside, and the heating unit is started timely according to the temperature sensed by the temperature sensing unit and the required level. The first temperature controller 271, the second temperature controller 272 and the third temperature controller 273 may have the same type, and may be respectively located inside or outside the corresponding pipes 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, and 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 includes a multi-stage particle size analysis module 221 and a volatile organic compound analysis module 222, and both the multi-stage particle size analysis module 221 and the volatile organic compound analysis module 222 are connected to 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 CO₂(carbon dioxide) detection units, and thus the carbon oxide detection modules 213 may be two; the nitrogen oxide detection module 212 may include a NO (nitric oxide) detection unit and a NO₂(nitrogen dioxide) detection unit, whereby the nitrogen oxide detection module 212 may also detect two nitrogen-containing gases simultaneously, either in two or with a single device; the temperature of the exhaust gas detected by the nitrogen oxide detection module 212 and the carbon oxide detection module 213 is usually 55-75 ℃ and the temperature of the exhaust gas detected by the total hydrocarbon detection module 211 is usually 150-170 ℃, so that the first transmission branch 191 can be further divided into a plurality of branches (not shown) through a three-way valve (not shown) to be respectively connected to the total hydrocarbon detection module 211, the carbon oxide detection module 213 and the nitrogen oxide detection module 212, and temperature controllers can be respectively arranged on the corresponding branches to adjust the temperatures of the corresponding branches. It should be noted that, the online analysis is usually performed by the computer 215, the aforementioned online analysis modules may be connected to the same computer 215 or each of the online analysis modules may be connected to different computers 215, which is not strictly limited in this embodiment, however, in consideration of cost and structural simplification, it is preferable to connect to the same computer 215 for on-line analysis, and the data analyzed by each on-line analysis module is displayed in the computer 215 in real time, and stored in the computer 215, 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 can also be connected to the computer 215 to realize timely storage of data and facilitate further analysis, meanwhile, the modules needing to be controlled can be controlled based on the computer 215 (for example, the computer 215 controls the work of a plurality of temperature controllers).

As an example, the multi-stage particle size analysis module 221 may employ a MOUDI sampler, such as a MOUDI impact classification sampler manufactured by MSP, to collect particles in the exhaust gas in a size-separated manner, so as to more effectively understand particle morphology and chemical composition in the exhaust gas; the volatile organic compound analysis module 222 can adopt a SUMMA (surface plasmon resonance) tank, and can realize online and offline measurement of trace volatile organic compounds, and the principle is that a freezing and enriching device adopts an electric refrigeration mode, a target compound is captured at a low temperature of-150 ℃, the temperature is rapidly heated to 100 ℃ during thermal analysis, and then a sample enters a GC-MS (gas chromatography-mass spectrometer) for analysis.

In one example, the online analysis device further includes a particulate matter detection module 214 for detecting the quantity and quality of particulate matter in the exhaust gas, and the particulate matter detection module 214 can realize rapid determination of the particle size distribution of the particulate matter, and can perform transient cycle test on the dynamic behavior of the particulate matter emission in the exhaust gas emitted by the aircraft engine 41; the off-line analysis apparatus further comprises a four-channel particulate matter analysis module 223; the aircraft engine exhaust emission detection system further comprises a third transmission branch 193 and a fourth temperature controller 274 positioned on the third transmission branch 193, the third transmission branch 193 is connected with one end of the diverter valve 18 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 particle analysis module can adopt a four-channel particle sampler which is provided with 4 sampling channels, can realize homologous collection of 4 samples, is internally provided with 4 independent gas circuits (4 air pumps 224, 4 flow sensors and 4 filter membrane clamps), and can simultaneously or independently implement constant-current sampling of each gas circuit; by adopting the particle detection module 214 and the four-channel particle analysis module 223 to perform online and offline analysis, the particles in the tail gas emitted by the aircraft engine can be comprehensively analyzed, the real-time emission condition and the deposition condition of the particles can be known, and the real-time influence and the potential influence of the tail gas emitted by the aircraft engine on the atmospheric environment and the climate can be analyzed.

The analysis of the particles is usually performed in a room temperature environment (ambient temperature), so the gas temperature in the third transmission branch 193 can be controlled to room temperature by arranging 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 transmission branch 191 between the diverter valve 18 and the online 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.

As an example, the aircraft engine exhaust emission detection system further includes a plurality of control valves 29 and a plurality of transit pipelines 31, one end of the transit pipeline 31 is connected to all the sampling pipelines 15 in a single row or a single column, and the other end of the transit pipeline 31 is connected to the transmission pipeline 17, and the plurality of control valves 29 are located on the transit 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 the area a of fig. 1). That is, all the sampling pipes 15 (i.e. sampling holes 12) in a single row or single column are connected to the same transfer pipe 31, and the control valves 29 arranged on the corresponding transfer pipes 31 can close all the sampling pipes 15 in a single row or single column (opening of a single sampling pipe 15 requires simultaneous cooperation of the control valve 29 and the sampling valve 16 on the sampling pipe 15); through such setting, can realize the sampling in-process to the difference sampling pipeline 15's fast switch-over obtains the tail gas of different positions and mixes and obtain the waste gas sample through quick porous position sampling to detect aircraft engine 41 and discharge pollutant concentration's average value, compensate the not enough of single sampling mode collection sample analysis, this is very important to the potential influence of discrete point to the nonuniformity of evaluating research aircraft engine 41 gas vent production gas and particulate matter emission index, makes to adopt the utility model discloses the data of carrying out the analysis more have convincing power. The control valve 29 and the sampling valve 16 can be all connected to a controller (such as the computer 215) to be automatically controlled by the controller, so that manual operation by workers on site is not required, and the harm to human bodies caused by the discharged tail gas can be avoided. Furthermore, depending on the thrust of the aircraft engine 41, it is also possible to study the combination of different sampling holes 12 for analyzing the collected gas and particulate matter, for example, when the thrust is 7%, a combination of 2 sampling holes 12 may be selected; when the pushing force is 85%, a combination of 4 sampling holes 12 can be selected.

As shown in FIG. 4, adopt the utility model discloses an during aircraft engine exhaust emissions detecting system carries out sampling analysis, will sampling support 11 places in the wind gap department under the aircraft engine 41 emission that waits to detect, makes sampling panel 111 just discharges the wind gap, for example makes sampling probe 14 can begin to detect the analysis apart from the position of discharging about 5 centimetres of wind gap, and the operation is very simple. Just the utility model discloses can be used for the engine exhaust pollutant emission of different models to detect, help practicing thrift the cost and improve work efficiency.

For making the technical solution and the advantages of the utility model clearer, following signal one kind according to the utility model discloses an aircraft engine exhaust emission detection method that aircraft engine exhaust emission detection system goes on, as shown in fig. 5, detection method includes the step:

s01: providing an aircraft engine exhaust emission detection system according to any one of the above aspects, placing the sampling bracket 11 at an exhaust outlet of an aircraft engine 41 to be sampled so that the sampling probe 14 can collect exhaust emitted by the aircraft engine 41;

s02: opening or closing the sampling pipelines 15 corresponding to different sampling probes 14 so as to perform sampling analysis on the exhaust gas of the sampling holes 12 corresponding to different positions of the exhaust outlet of the aircraft engine 41.

Before the detection starts, the sampling bracket 11 of the aircraft engine exhaust emission detection system according to any one of the preceding aspects is placed at an exhaust downdraft of an aircraft engine 41 to be detected (as shown in fig. 4), for example, the sampling probe 14 is located at a position about 5 cm away from the exhaust downdraft; then, opening or closing of different sampling pipelines 15 is controlled according to requirements so as to obtain tail gas at different positions through different combinations of opening or closing of different sampling holes 12 and mix the tail gas to obtain waste gas samples; and as mentioned before, the sampling lines 15, i.e. sampling apertures 12, which are preferably located in a single row or column, are controlled by the same control valve 29 to enable a fast switching of the different sampling positions during sampling.

By way of example, when the sampling holes 12 and the sampling pipeline 15 are 25 and 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 schemes, preferably all of the following schemes are adopted for sampling one by one to obtain a plurality of sampling samples, which helps to improve the comprehensiveness and accuracy of the analysis (the sampling holes 12 marked in black in the figure represent the sampling holes 12 to be sampled):

1. as shown in fig. 6, sampling and analyzing all the exhaust gas at the positions corresponding to the sampling holes 12 to know the overall exhaust condition (including specific components and contents of different components of the exhaust gas, etc.) of the exhaust gas emitted by the aircraft engine 41;

2. as shown in fig. 7 to 9, the exhaust gas at the positions corresponding to the partial sampling holes 12 on the symmetry axes distributed in the array is sampled, for example, 2 or more (preferably 3) samples are analyzed along the 45 °, 135 ° and 225 ° axes in the clockwise direction, so as to analyze the exhaust gas emitted by the aircraft engine 41 in different directions, and as the sampling process continues (for example, before the aircraft takes off, during the engine starts, or after the aircraft lands, during the engine is turned off), the sampling manner helps to study the diffusion of the exhaust gas in different directions;

3. as shown in fig. 10, sampling and analyzing the exhaust gas at the positions corresponding to the sampling holes 12 in the circumferential direction around the center of the array distribution, for example, sampling and analyzing the exhaust gas at the positions corresponding to the 8 sampling holes 12 around the sampling holes 12 in the center in fig. 10; of course, in other examples, the exhaust gas at the position corresponding to the 4 sampling holes 12 in the circumferential direction may also be sampled and analyzed, and this embodiment is not limited strictly; by analyzing the distribution of the exhaust gas along the circumferential direction, the exhaust gas distribution from the center to the edge of the exhaust port can be researched;

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 is sampled and analyzed, for example, the exhaust gas at the position corresponding to all the sampling holes 12 where adjacent multiple rows or multiple 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 condition of exhaust gas discharged from one side of the discharge port.

The combination of multiple sampling mode more than adopting realizes carrying out the sampling analysis to the exhaust tail gas of the different positions of aircraft discharge port, helps studying the potential influence of the heterogeneity of engine gas vent production gas and particulate matter emission index to discrete point, remedies the not enough scheduling problem of sample analysis data volume that single sampling mode exists, makes the adoption the utility model discloses the analytical data who obtains is more convincing.

As an example, the detection method further includes a step of calculating an emission factor of the real-time pollutant emission of the aircraft engine 41 based on the result of the sampling analysis by combining the speed of the aircraft corresponding to the aircraft engine 41, the exhaust gas volume of the aircraft engine 41 and the fuel consumption rate. Since this calculation process is well known to those skilled in the art, it is not expanded in detail. Adopt the utility model discloses a data that detection method obtained can provide the foundation for studying aviation emission list, and more the atmosphere pollution prevention provides the foundation with administering.

Of course, the implementation process of the above detection method is only illustrative, and the setting of the sampling position may also have other options according to different needs, for example, according to different types of aircraft engines, and the present embodiment is not limited strictly.

To sum up, the utility model provides an aircraft engine exhaust emission detecting system, detecting system includes: a sampling support having a plurality of sampling apertures therein; the sampling probes are positioned in the sampling holes in a one-to-one correspondence manner; the sampling pipes are connected with the sampling holes in a one-to-one correspondence mode, and each sampling pipe is provided with a sampling valve; the transmission pipeline is connected with the plurality of sampling pipelines; the flow dividing valve is connected to one end, far away from the sampling pipeline, of the transmission pipeline and is used for dividing tail gas in the transmission pipeline into transmission branches, and each transmission branch at least comprises a first transmission branch and a second transmission branch; the online analysis device is at least connected with the first transmission branch and is used for performing online analysis on 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 carrying out off-line analysis on the tail gas in the second transmission branch. The utility model discloses but real-time acquisition aircraft engine's exhaust tail gas carries out all-round analysis through online analytical equipment and off-line analytical equipment to the accurate component of understanding aircraft engine exhaust gas constitutes, and the help masters the real-time emission factor who discharges of aircraft engine pollutant, thereby discharges the manifest and provides the foundation for research aviation, and more atmosphere pollution prevention and treatment provide the foundation. Furthermore, the utility model discloses can realize carrying out the sampling analysis to the exhaust tail gas of the different positions of aircraft discharge port through the different combinations of sampling hole, help studying the potential influence of the nonuniformity of engine gas vent production gas and particulate matter emission index to discrete point, compensate the not enough scheduling problem of sample analysis data volume that single sampling mode exists, make and adopt the utility model discloses the analytical data who obtains is more convincing. The utility model is suitable for an engine exhaust pollutant emission of different models detects, helps practicing thrift the cost and improves work efficiency. Therefore, the utility model effectively overcomes various defects in the prior art and has high industrial utilization value.

The above embodiments are merely illustrative of the principles and effects of the present invention, and are not to be construed as limiting the invention. Modifications and variations can be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.

Claims (10)

1. An aircraft engine exhaust emission detection system, comprising:

a sampling support having a plurality of sampling apertures therein;

the sampling probes are positioned in the sampling holes in a one-to-one correspondence manner;

the sampling pipes are connected with the sampling holes in a one-to-one correspondence mode, and each sampling pipe is provided with a sampling valve;

the transmission pipeline is connected with the plurality of sampling pipelines;

the flow dividing valve is connected to one end, far away from the sampling pipeline, of the transmission pipeline and is used for dividing tail gas in the transmission pipeline into transmission branches, and each transmission branch at least comprises a first transmission branch and a second transmission branch;

the online analysis device is at least connected with the first transmission branch and is used for performing online analysis on 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 carrying out off-line analysis on the tail gas in the second transmission branch.

2. The aircraft engine exhaust emission detection system of claim 1, wherein: the aircraft engine tail gas emission detection system further comprises a pressure sensor, a pressure regulating valve and a flow velocity sensor which are all located on the transmission pipeline.

3. The aircraft engine exhaust emission detection system of claim 1, wherein: the aircraft engine exhaust emission detection system further comprises a heat shield located at the periphery of the plurality of sampling pipes and used for maintaining the temperature of the sampling pipes at a required temperature so as to prevent the exhaust gas from settling and condensing in the sampling pipes.

4. The aircraft engine exhaust emission detection system of 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 positioned on the transmission pipeline, the second temperature controller is positioned on the first transmission branch, and the third temperature controller is positioned on the second transmission branch.

5. The aircraft engine exhaust emission detection system of claim 1, wherein: the online 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, and the multi-stage particle size analysis module and the volatile organic compound analysis module are connected with the second transmission branch.

6. The aircraft engine exhaust emission detection system of claim 5, wherein: the online analysis device also comprises a particulate matter detection module for detecting the quantity and quality of particulate matters in the tail gas; the off-line analysis device further comprises a four-channel particulate matter analysis module; the aircraft engine tail gas emission detection system further comprises a third transmission branch and a fourth temperature controller located 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.

7. The aircraft engine exhaust emission detection system of claim 5, wherein: the aircraft engine exhaust emission detection system further comprises a first filter and a second filter, the first filter being located on the first transmission branch between the diverter valve and the online analysis device; the second filter is located on the second transport leg between the diverter valve and the off-line analysis device.

8. The aircraft engine exhaust emission detection system of 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.

9. The aircraft engine exhaust emission detection system according to any one of claims 1 to 8, wherein: the sampling device comprises a sampling support, sampling valves and sampling holes, wherein the sampling holes are n x m, the n x m sampling holes are distributed on the sampling support in an n-row-m-column array mode, the number of the sampling pipelines is n x m, the number of the sampling valves is n x m, and both n and m are integers larger than or equal to 2.

10. The aircraft engine exhaust emission detection system of claim 9, wherein: 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 the sampling pipelines in a single row or a single row, 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.

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