CN115683639A - High-temperature negative-pressure tail gas sampling system and sampling method suitable for high-altitude test bed - Google Patents
High-temperature negative-pressure tail gas sampling system and sampling method suitable for high-altitude test bed Download PDFInfo
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Abstract
The invention relates to a high-temperature negative-pressure tail gas sampling system and a sampling method suitable for a high-altitude test bed, wherein the high-temperature negative-pressure tail gas sampling system at least comprises: the system comprises a tail gas acquisition unit, a tail gas analyzer, a data acquisition and transmission unit and a plurality of upper computers; the tail gas collecting unit is correspondingly arranged behind the jet port of the aircraft engine or the outlet section of the combustion chamber; the air inlet end of the tail gas analyzer is connected with the air inlet end of the tail gas acquisition unit through an air conveying pipeline, and a vacuum pump is arranged on the air conveying pipeline; the input end of the data acquisition and transmission unit is connected with a tail gas analyzer; the plurality of upper computers are provided with first upper computers and second upper computers, the first upper computers are in communication connection with the output ends of the data acquisition and transmission units, and the second upper computers are connected with a plurality of sensors in the aircraft engine or the combustion chamber. The sampling system has the characteristics of simple and convenient operation and accurate result, and can solve the technical problem that the conventional high-altitude test bed is not provided with a special high-temperature negative-pressure tail gas sampling system.
Description
Technical Field
The invention belongs to the technical field of high-altitude tests of aero-engines, and particularly relates to a high-temperature negative pressure tail gas sampling system and a high-temperature negative pressure tail gas sampling method suitable for a high-altitude test bed.
Background
The high-altitude test bed is the only test bed which is recognized all over the world at present and has all-working-condition, all-environment and all-performance simulation tests. However, because the high-altitude test bed has a long construction period and high operation cost, only a few big aviation countries have construction, such as the united states, russia, france, the united kingdom and the like, the most complete of which is the united states, such as the arnold engineering research center (aecc) and the united states aerospace administration (NASA), and the most complete high-altitude test base in the world and with the largest volume is constructed, and the high-altitude test bed has the test capabilities of testing the power used by aircrafts such as a human machine, an unmanned aerial vehicle, a missile, an aerospace vehicle and the like, such as high-altitude pollution, high-altitude performance, high-altitude flameout, high supersonic speed and the like.
At present, the domestic units with the high-altitude test capability of the aero-engine are two, namely a Sichuan gas turbine research institute (624 th) and a academy of China, and light aero-engine high-altitude test benches built by the units have the test capabilities of high-altitude thrust, high-altitude functional boundaries, high-altitude point flameout and the like, but the high-altitude test benches are not provided with special high-temperature negative-pressure tail gas sampling systems, so that the high-altitude pollution measurement and analysis work cannot be carried out, and the pollutant measurement discharged by the aero-engine or a combustion chamber working in the high-altitude environment cannot be further analyzed.
Therefore, the key to solve the problems is how to develop a high-temperature negative-pressure tail gas sampling system suitable for a high-altitude test bed.
Disclosure of Invention
Aiming at the defects in the related art, the invention provides a high-temperature negative-pressure tail gas sampling system and a sampling method suitable for a high-altitude test bed, which have the characteristics of simple and convenient operation and accurate result and can solve the technical problem that the pollutant discharged by the work of an aeroengine or a combustion chamber in the high-altitude environment cannot be measured because the conventional high-altitude test bed is not provided with a special high-temperature negative-pressure tail gas sampling system.
The invention provides a high-temperature negative-pressure tail gas sampling system suitable for a high-altitude test bed, which at least comprises:
the tail gas collecting unit is arranged in the high altitude environment test simulation cabin, correspondingly arranged behind the outlet section of the jet nozzle of the aircraft engine or the outlet section of the combustion chamber and used for collecting tail gas discharged by the aircraft engine or the combustion chamber;
the tail gas analyzer is used for analyzing tail gas exhausted by the aircraft engine to obtain tail gas component information, the air inlet end of the tail gas analyzer is connected with the air entraining end of the tail gas acquisition unit through an air conveying pipeline, and a vacuum pump is arranged on the air conveying pipeline between the tail gas acquisition unit and the tail gas analyzer and used for controlling the tail gas to enter the tail gas analyzer from the tail gas acquisition unit;
the input end of the data acquisition and transmission unit is connected with the tail gas analyzer and is used for acquiring and transmitting the tail gas component information;
a plurality of host computers, it is a plurality of the host computer has first host computer and second host computer, first host computer with communication connection between the second host computer, first host computer communication is connected data acquisition and transmission unit's output is used for right tail gas composition information saves and the analysis, the second host computer is connected a plurality of sensors in aeroengine or the combustion chamber are used for right aeroengine or combustion chamber carry out the wholeness can analysis.
In some embodiments, the exhaust gas collection unit is a hybrid sampling probe, and an air inlet end of the hybrid sampling probe is correspondingly arranged behind an outlet section of the aero-engine tail nozzle or a combustion chamber.
In some of these embodiments, the hybrid sampling probe further comprises:
the cooling cavity is internally provided with a first cavity, a tail gas mixing main pipe penetrates through the first cavity, and two ends of the tail gas mixing main pipe extend to the outside of the cooling cavity;
the vertical support part is provided with a long-strip plate-shaped structure, a plurality of sampling probes fixed inside the long-strip plate-shaped structure and a plurality of compressed gas outlets arranged at the top of the long-strip plate-shaped structure, the long-strip plate-shaped structure is integrally arranged above the cooling cavity, the bottom of the long-strip plate-shaped structure is inserted into the cooling cavity, a second cavity is arranged inside the long-strip plate-shaped structure, the sampling probes are arranged in the second cavity, the sampling probes are of an inverted L-shaped structure, the air inlet end of the inverted L-shaped structure penetrates through the side wall of the long-strip plate-shaped structure and extends to the outside of the long-strip plate-shaped structure for collecting tail gas exhausted by an aircraft engine, the air outlet end of the inverted L-shaped structure penetrates through the bottom of the long-strip plate-shaped structure and extends to the inside of the first cavity and is communicated with the tail gas mixing header pipe, the tail gas collected by the sampling probes is mixed in the tail gas mixing header pipe, and the flow rate of the tail gas flowing through the sampling probes is controlled to be 20m/s;
a compressed air cooling pipe, compressed air cooling pipe gives vent to anger the end and inserts inside the first cavity, compressed gas air feed source is connected to the inlet end, through to the intraductal compressed gas that lets in of compressed air cooling for to the inside tail gas of cooling chamber internal environment, tail gas mixing house steward and tail gas mixing house steward the processing of cooling down, the compressed gas via after the cooling is handled the compressed gas export discharge.
In some embodiments, one end of the tail gas mixing main pipe is a bleed end, the bleed end is communicated with the gas transmission pipeline through a bleed pipeline and is connected to the gas inlet end of the tail gas analyzer through the gas transmission pipeline, and the other end of the tail gas mixing main pipe is a blowback pipeline end.
In some embodiments, the end of the back flushing pipeline is connected with a back flushing pipeline, a first valve is further arranged on the back flushing pipeline, and the first valve is opened while the second valve is closed, so that redundant fuel oil entering the interior of the sampling probe is discharged or residual compressed air used for cleaning the tail gas analyzer after gas calibration is performed is discharged;
still set up the second valve on the bleed pipeline still set up the third valve on the gas-supply pipeline between tail gas collection unit and the tail gas analysis appearance, just the third valve set up in before the vacuum pump, through control the second valve with opening and closing of third valve for control gets into the tail gas aeration volume in the tail gas analysis appearance.
In some embodiments, a tail gas emptying pipeline is further arranged on the gas transmission pipeline between the vacuum pump and the tail gas analyzer, and a fourth valve is arranged on the tail gas emptying pipeline and is opened by opening the fourth valve to empty redundant tail gas.
In some embodiments, a temperature sensor and a pressure sensor are further arranged on the gas transmission pipeline and used for measuring the temperature and the pressure inside the gas transmission pipeline in real time.
In some of these embodiments, the exhaust gas analyzer is a combination gas analyzer for detecting the presence of O in the exhaust gas of an aircraft engine 2 、CO、CO 2 、NO 2 、NO、CH 4 、SO 2 The gas inside is analyzed for composition and content.
In some embodiments, the data acquisition and transmission unit is a PLC controller, an input end of the PLC controller is connected to the tail gas analyzer, and an output end of the PLC controller is connected to the first upper computer.
In some embodiments, the tail gas collection unit may be further disposed behind the outlet of the combustion chamber for collecting the tail gas discharged from the combustion chamber.
The invention also provides a high-temperature negative-pressure tail gas sampling method which is carried out by using the high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed in any embodiment and comprises the following steps:
calibrating a tail gas analyzer: calibrating the tail gas analyzer by using a plurality of standard gases, and introducing compressed air into the tail gas analyzer after calibration is finished for removing residual standard gases;
installing tail gas sampling equipment: firstly, correspondingly placing the air inlet end of the hybrid sampling probe behind the outlet section of the aircraft engine tail nozzle or the combustion chamber, starting the operation of the aircraft engine or the combustion chamber in a high-altitude environment, and discharging tail gas;
and (3) removing redundant fuel oil or residual compressed air: opening the first valve while closing the second valve, exhausting redundant fuel oil entering the sampling probe, exhausting compressed air in the tail gas analyzer, and closing the first valve after exhausting redundant fuel oil and compressed air;
tail gas collection and cooling: tail gas enters the interior of the sampling probes through the gas inlet ends of the sampling probes, and then enters the tail gas mixing main pipe through the gas outlet ends of the sampling probes for tail gas mixing, the flow rate of the tail gas in the sampling probes is controlled to be no more than 20m/s, meanwhile, compressed air is introduced into the compressed air cooling pipe to cool the tail gas in the environment inside the cooling cavity, the tail gas mixing main pipe and the tail gas mixing main pipe, so that the temperature of the mixed tail gas in the tail gas mixing main pipe is cooled to 65 ℃, and the compressed air after cooling treatment is discharged through the compressed gas outlet;
analyzing the components of the tail gas: opening the second valve and the third valve, enabling the cooled tail gas to sequentially enter a gas introducing pipeline and a gas conveying pipeline through a gas introducing end of the tail gas mixing main pipe, finally entering a tail gas analyzer for tail gas component analysis to obtain tail gas component information, and controlling the introduction amount of the tail gas in the tail gas analyzer by controlling the second valve on the gas introducing pipeline and the third valve on the gas conveying pipeline so as to prevent the tail gas analyzer from being damaged due to overhigh pressure of the tail gas;
tail gas component information acquisition and transmission: the PLC controller collects the tail gas composition information, then transmits the tail gas composition information to the first upper computer for storage, calibration and analysis, and meanwhile, the second upper computer collects monitoring information of a plurality of sensors in the aero-engine or the combustion chamber and analyzes the overall performance of the aero-engine or the combustion chamber.
Compared with the prior art, the invention has the advantages and beneficial effects that:
1. before tail gas is analyzed, redundant fuel oil entering a sampling probe is discharged through mutual matching of a back flushing pipeline and a control valve arranged on the back flushing pipeline, and compressed air in a tail gas analyzer is discharged at the same time, so that the accuracy of a tail gas component detection result is ensured;
2. the invention provides a high-temperature negative-pressure tail gas sampling system suitable for a high-altitude test bed and a sampling method thereof.A mixed sampling probe is arranged behind a tail nozzle of an aeroengine or an outlet of a combustion chamber to effectively collect tail gas discharged in the working process of the aeroengine or the combustion chamber in the high-altitude test bed, and simultaneously, the chemical reaction among different components in the tail gas is easily caused due to overhigh temperature of the tail gas so as to influence the accuracy of a final detection result;
3. according to the high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed, due to the arrangement of the PLC and the plurality of upper computers, the transmission, calibration and storage of tail gas analysis results can be realized, the overall performance of an aero-engine can be monitored and analyzed, the measurement of pollutants discharged by the aero-engine or a combustion chamber in a high-altitude environment is realized, and the high-altitude pollution research of the aero-engine under the long-time working condition is promoted;
4. the high-temperature negative-pressure tail gas sampling system and the sampling method thereof suitable for the high-altitude test bed have the characteristics of simplicity and convenience in operation and accurate measurement results, and solve the technical problem that the pollutant discharged by the operation of an aeroengine or a combustion chamber in the high-altitude environment cannot be measured because the conventional high-altitude test bed is not provided with a special high-temperature negative-pressure tail gas sampling system.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
fig. 1 is a schematic diagram of an overall structure of a high-temperature negative-pressure tail gas sampling system suitable for a high-altitude test bed according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a hybrid sampling probe according to an embodiment of the present invention;
FIG. 3 is a top view of a hybrid sampling probe in accordance with an embodiment of the present invention;
FIG. 4 is a perspective view of a hybrid sampling probe provided in accordance with an embodiment of the present invention;
FIG. 5 is an enlarged view of portion A of a hybrid sampling probe in accordance with an embodiment of the present invention.
In the figure:
1. a high-altitude environment test simulation cabin; 2. an aircraft engine tail nozzle; 3. a hybrid sampling probe; 4. a tail gas analyzer; 5. a PLC controller; 6. a first upper computer; 7. a second upper computer; 8. a gas transmission pipeline; 9. a vacuum pump; 10. a bleed air line; 11. a back flushing pipeline; 12. a tail gas vent pipeline; 13. a first valve; 14. a second valve; 15. a third valve; 16. a fourth valve; 17. temperature sensors and pressure sensors; 18. a tee joint; 31. a cooling chamber; 32. a vertical support; 33. a tail gas mixing main pipe; 34. a compressed air cooling tube; 321. a strip plate-like structure; 322. a sampling probe; 323. a compressed gas outlet; 324. an air inlet end with an inverted L-shaped structure; 325. an air outlet end of the inverted L-shaped structure; 331. a gas introducing end; 332. and a back flushing pipeline end.
Detailed Description
The technical solutions in the embodiments will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the described embodiments are merely some embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "central," "lateral," "longitudinal," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present invention and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting.
The terms "first", "second" and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and "third" may explicitly or implicitly include one or more of the features.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1, in an exemplary embodiment of a high temperature and negative pressure tail gas sampling system suitable for a high altitude test bed according to the present invention, the high temperature and negative pressure tail gas sampling system at least includes: the system comprises a tail gas acquisition unit, a tail gas analyzer 4, a data acquisition and transmission unit and a plurality of upper computers; the tail gas collecting unit is arranged in the high-altitude environment test simulation cabin 1, correspondingly arranged behind the outlet section of an aircraft engine tail nozzle 2 or a combustion chamber (not shown in the figure) and used for collecting tail gas exhausted by the aircraft engine or the combustion chamber; the tail gas analyzer 4 is used for analyzing the tail gas discharged by the aircraft engine to obtain tail gas component information, and the tail gas analyzer 4 is a combined gas analyzer and is used for analyzing the tail gas discharged by the aircraft engine to obtain O 2 、CO、CO 2 、NO 2 、NO、CH 4 、SO 2 The method comprises the following steps that the components and the content of various gases in the tail gas analyzer are analyzed, the air inlet end of a tail gas analyzer 4 is connected with the air entraining end of a tail gas collecting unit through an air conveying pipeline 8 (namely a heat insulation pipeline), and a vacuum pump 9 is arranged on the air conveying pipeline 8 between the tail gas collecting unit and the tail gas analyzer and used for controlling tail gas to enter the tail gas analyzer 4 from the tail gas collecting unit; in addition, the size of the inner diameter of the conveying gas path 8 needs to be determined according to the capacity of the vacuum pump 9, the built-in pump of the tail gas analyzer 4, the performance parameters of the aero-engine, the aperture size of the sampling probe 322, the incoming flow temperature, the incoming flow pressure, the lowest pressure of the simulation environment and other comprehensive calculations, simulations and the like, meanwhile, the conveying gas path 8 needs to be as short as possible under practical and feasible conditions, and the conveying time of the sample gas in the path is smaller than 10s due to the flow rate of the sample gas; the input end of the data acquisition and transmission unit is connected with a tail gas analyzer 4 and is used for acquiring and transmitting tail gas composition information; the plurality of upper computers are provided with a first upper computer 6 and a second upper computer 7, the first upper computer 6 is in communication connection with the output end of the data acquisition and transmission unit and is used for storing and analyzing tail gas composition information, and the second upper computer 7 is used for storing and analyzing tail gas composition informationThe upper computer 7 is connected with a plurality of sensors installed in the aero-engine or the combustion chamber and used for analyzing the overall performance of the aero-engine or the combustion chamber. In addition, referring to fig. 1, in the embodiment of the present invention, a plurality of tail gas analyzers 4 may be further installed on the gas transmission pipeline 8, the present invention is not particularly limited, and a person skilled in the art may design according to actual needs. The embodiment provides a high-temperature negative-pressure tail gas sampling system suitable for a high-altitude test bed, which is characterized in that a mixed sampling probe 3 is arranged behind a tail nozzle 2 of an aircraft engine or an outlet of a combustion chamber, so that the tail gas discharged in the working process of the aircraft engine or the combustion chamber in the high-altitude test bed is effectively collected, the collected tail gas is sent to a tail gas analyzer 4 to be analyzed to obtain a tail gas component analysis result, functions of collecting, transmitting, storing, calibrating, displaying, analyzing and the like of the tail gas component analysis result are realized through a data collecting and transmitting unit and a plurality of upper computers, and meanwhile, a plurality of key data (including but not limited to parameters such as temperature and pressure) of a sensor in the aircraft engine or the combustion chamber are collected to analyze the overall performance of the aircraft engine or the combustion chamber, so that the technical problem that the pollutant measurement discharged by the operation of the aircraft engine or the combustion chamber in the high-altitude environment cannot be carried out due to the fact that a special high-temperature negative-pressure tail gas sampling system is not provided in the existing high-altitude test bed is solved.
Furthermore, the tail gas acquisition unit is a mixed sampling probe 3, and the air inlet end of the mixed sampling probe 3 is correspondingly arranged behind the jet nozzle 2 of the aircraft engine or the outlet section of the combustion chamber.
Further, referring to fig. 2-4, the hybrid sampling probe 3 further includes: a cooling chamber 31, a vertical support portion 32 and a compressed air cooling pipe 34; a first cavity is formed in the cooling cavity 31, a tail gas mixing main 33 penetrates through the first cavity, and two ends of the tail gas mixing main 33 extend to the outside of the cooling cavity 31; the vertical support portion 32 has an elongated plate-shaped structure 321, a plurality of sampling probes 322 fixed inside the elongated plate-shaped structure 321, and a plurality of compressed gas outlets 323 arranged at the top of the elongated plate-shaped structure 321, wherein the elongated plate-shaped structure 321 is integrally arranged above the cooling cavity 31, the bottom of the elongated plate-shaped structure 321 is inserted into the cooling cavity 31, a second cavity is arranged inside the elongated plate-shaped structure 321, the plurality of sampling probes 322 are arranged in the second cavity, the sampling probes 322 are made of 316H stainless steel (meeting quenching requirements), the sampling probes 322 are integrally in an inverted L-shaped structure, referring to fig. 4, the plurality of sampling probes 322 integrally in the inverted L-shaped structure are uniformly arranged inside the second cavity, an air inlet end 324 of the inverted L-shaped structure extends to the outside of the elongated plate-shaped structure 321 through a sidewall of the elongated plate-shaped structure 321, and is used for collecting tail gas discharged from the aircraft engine (according to the diameter of the tail injection section or the combustion chamber outlet, sampling holes of the sampling probes 322 are designed according to the same area, and simultaneously, the blockage ratio of the engine tail injection section is less than 5%, if the blockage ratio affects the flow of the tail gas generated in the aircraft engine, the mixed tail gas flows through the elongated plate-shaped structure, the sampling probes 322, and the exhaust gas flow control system is carried out the first exhaust gas flow through the elongated plate-shaped exhaust probe 33 which flows through the elongated plate-shaped structure 322 and the elongated plate-shaped exhaust gas flow 20 and the elongated plate-shaped structure 322, and the sampling probes 322, the elongated plate-shaped exhaust gas flow control device is severely connected to the elongated plate-shaped exhaust gas flow control system, the elongated plate-shaped exhaust gas flow control device, the sampling probes 322; the air outlet end of the compressed air cooling pipe 34 is inserted into the first cavity, the air inlet end is connected with a compressed air supply source (different cooling media are selected according to different engine exhaust temperatures, when the exhaust temperature is less than 1000 ℃, compressed air can be used for cooling like the invention, when the exhaust temperature is more than or equal to 1000 ℃, cooling water can be selected for cooling treatment), the compressed air is introduced into the compressed air cooling pipe 34 to be used for cooling treatment of tail gas in the internal environment of the cooling cavity 31, the tail gas mixing header pipe 33 and the tail gas mixing header pipe 33, and the compressed gas after cooling treatment is discharged from the compressed gas outlet 323 and two sides of the second cavity.
Further, referring to fig. 2-4, one end of the exhaust gas mixing main pipe 33 is a bleed air end 331, the bleed air end 331 is communicated with the air pipe 8 through a bleed air pipe 10, and is connected to an air inlet end of the exhaust gas analyzer 4 through the air pipe 8, and the other end of the exhaust gas mixing main pipe 33 is a blowback pipe end 332.
Further, the back-flushing pipeline end 332 is connected with a back-flushing pipeline 11, a first valve 13 is further arranged on the back-flushing pipeline 11, and the first valve 11 is opened while the second valve 14 is closed, so that redundant fuel oil entering the interior of the sampling probe 322 is discharged or residual compressed air used for cleaning after gas calibration is performed on the tail gas analyzer 4 is discharged; a second valve 14 is further arranged on the gas introduction pipeline 10, a third valve 15 is further arranged on the gas transmission pipeline 8 between the tail gas collection unit and the tail gas analyzer 4, and the third valve 15 is arranged in front of the vacuum pump 9 and used for controlling the introduction amount of the tail gas entering the tail gas analyzer 4 by controlling the opening and closing of the second valve 14 and the third valve 15; a tail gas emptying pipeline 12 is further arranged on the gas transmission pipeline 8 between the vacuum pump 9 and the tail gas analyzer 4, and a fourth valve 16 is arranged on the tail gas emptying pipeline 12 and is opened by opening the fourth valve 16 for emptying redundant tail gas. In addition, a temperature sensor and a pressure sensor 17 are arranged on the air transmission pipeline 8 and used for measuring the temperature and the pressure inside the air transmission pipeline 8 in real time.
Further, the data acquisition and transmission unit is a PLC (programmable logic controller) 5, the input end of the PLC 5 is connected with the tail gas analyzer 4, and the output end of the PLC 5 is connected with the first upper position 6.
The embodiment of the invention also provides a method for sampling the high-temperature negative-pressure tail gas by adopting the high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed, which comprises the following steps:
(1) Calibrating a tail gas analyzer: calibrating the tail gas analyzer 4 by using various standard gases, and introducing compressed air into the tail gas analyzer 4 after calibration is finished for removing residual standard gases;
in the step (1), the tail gas analyzer 4 is calibrated by using a plurality of standard gases to ensure the accuracy of tail gas detection, and compressed air is introduced into the tail gas analyzer 4 after calibration is finished to avoid the standard gas remaining in the tail gas analyzer 4 to influence the detection result, so that the remaining standard gas is exhausted.
(2) Installing tail gas sampling equipment: firstly, correspondingly placing the air inlet end of a mixed sampling probe 3 behind the outlet section of the jet nozzle 2 of the aircraft engine or the outlet section of a combustion chamber, starting the operation of the aircraft engine or the combustion chamber in a high-altitude environment, and discharging tail gas;
the step (2) is an installation step of the hybrid sampling probe 3, during installation, the size of the tail jet section or the diameter of the outlet of the combustion chamber is determined, the sampling hole position of the sampling probe 322 is designed according to the equal area, and meanwhile, the blockage ratio of the tail jet section of the engine is required to be less than or equal to 5%, and if the blockage ratio exceeds 5%, the thrust of the aero-engine is seriously influenced.
(3) And (3) removing redundant fuel oil or residual compressed air: closing the second valve 14, opening the first valve 13 at the same time, exhausting the redundant fuel oil entering the sampling probe 322, exhausting the compressed air in the tail gas analyzer 4 at the same time, and closing the first valve 13 after the redundant fuel oil and the compressed air are exhausted;
the step (3) also belongs to preparation work before the sampling of the tail gas is started, and considering that fuel oil is discharged from the tail nozzle into the sampling probe 322 due to ignition failure when the aircraft engine is started, in order to completely discharge the fuel oil entering the sampling probe 322, the step (3) enables the fuel oil in the sampling probe 322 and compressed air in the tail gas analyzer 4 to be exhausted by opening the second valve 14 so as to prepare for formally starting the sampling work of the tail gas.
(4) Tail gas collection and cooling: tail gas enters the interior of the sampling probes 322 through the gas inlet ends of the sampling probes 322, and then enters the tail gas mixing main pipe 33 through the gas outlet ends of the sampling probes 322 to be mixed with the tail gas, the flow velocity of the tail gas in the sampling probes 322 is controlled to be not more than 20m/s, meanwhile, the temperature of the mixed tail gas in the tail gas mixing main pipe 33 and the tail gas in the tail gas mixing main pipe 33 is reduced by introducing compressed air into the compressed air cooling pipe 34, so that the temperature of the mixed tail gas in the tail gas mixing main pipe 33 is reduced to 65 ℃, and the compressed air after the temperature reduction treatment is discharged through a compressed gas outlet 323;
in the step (4), the tail gas collected by the plurality of sampling probes 322 is mixed in the tail gas mixing main pipe 33, and meanwhile, when the temperature of the tail gas is too high, chemical reactions occur among different components in the tail gas, so that the analysis result of the tail gas is influenced, therefore, the temperature of the tail gas is also reduced by introducing compressed air into the cooling cavity 31, the analysis temperature of the tail gas needs to be controlled at 65 ℃, and chemical freezing can be achieved under the condition (that is, chemical reactions do not occur among components in the tail gas).
(5) Analyzing the components of the tail gas: opening the second valve 14 and the third valve 13, allowing the cooled tail gas to sequentially enter the bleed gas pipeline 10 and the gas transmission pipeline 8 through the bleed gas end 331 of the tail gas mixing header pipe 33, and finally enter the tail gas analyzer 4 for tail gas component analysis to obtain tail gas component information, and controlling the amount of the tail gas introduced into the tail gas analyzer 4 by controlling the second valve 14 on the bleed gas pipeline 10 and the third valve 15 on the gas transmission pipeline 8;
in the step (5), a manual valve is arranged on the pipeline 10 for controlling the cooled mixed tail gas to enter the gas transmission pipeline 8, an electric valve is arranged on the gas transmission pipeline 8 for controlling the ventilation volume of the cooled mixed tail gas entering the tail gas analyzer, and the accurate control of the tail gas introduction volume is realized through double valve control. In addition, still set up a tail gas unloading pipeline and install the control flap on tail gas unloading pipeline on the transport gas circuit 8 between vacuum pump 9 and tail gas analysis appearance 4 for even discharge sampling system with unnecessary tail gas, in order to avoid influencing the accuracy that tail gas analysis appearance 4 detected.
(6) Tail gas component information acquisition and transmission: the PLC 5 collects tail gas composition information, then transmits the tail gas composition information to the first upper computer 6 for storage, calibration and analysis, and meanwhile, the second upper computer 7 collects monitoring information of a plurality of sensors in the aero-engine or the combustion chamber to analyze the overall performance of the aero-engine or the combustion chamber.
Finally, it should be noted that: the embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the invention, it is intended to cover all modifications within the scope of the invention as claimed.
Claims (10)
1. The utility model provides a high temperature negative pressure tail gas sampling system suitable for high altitude test platform which characterized in that includes at least:
the tail gas collecting unit is arranged in the high altitude environment test simulation cabin, correspondingly arranged behind the outlet section of the jet nozzle of the aircraft engine or the outlet section of the combustion chamber and used for collecting tail gas discharged by the aircraft engine or the combustion chamber;
the tail gas analyzer is used for analyzing tail gas exhausted by the aircraft engine to obtain tail gas component information, the air inlet end of the tail gas analyzer is connected with the air entraining end of the tail gas acquisition unit through an air conveying pipeline, and a vacuum pump is arranged on the air conveying pipeline between the tail gas acquisition unit and the tail gas analyzer and used for controlling the tail gas to enter the tail gas analyzer from the tail gas acquisition unit;
the input end of the data acquisition and transmission unit is connected with the tail gas analyzer and is used for acquiring and transmitting the tail gas component information;
a plurality of host computers, it is a plurality of the host computer has first host computer and second host computer, first host computer with communication connection between the second host computer, first host computer communication is connected data acquisition and transmission unit's output is used for right tail gas composition information saves and the analysis, the second host computer is connected a plurality of sensors in aeroengine or the combustion chamber are used for right aeroengine or combustion chamber carry out the wholeness can analysis.
2. The high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed as claimed in claim 1, wherein the tail gas collecting unit is a hybrid sampling probe, and an air inlet end of the hybrid sampling probe is correspondingly arranged behind an outlet section of the aero-engine tail nozzle or the combustion chamber.
3. The high temperature negative pressure tail gas sampling system suitable for use in a high altitude test rig of claim 2, wherein the hybrid sampling probe further comprises:
the cooling cavity is internally provided with a first cavity, a tail gas mixing main pipe penetrates through the first cavity, and two ends of the tail gas mixing main pipe extend to the outside of the cooling cavity;
the vertical support part is provided with a long strip-shaped plate-shaped structure, a plurality of sampling probes fixed inside the long strip-shaped plate-shaped structure and a plurality of compressed gas outlets arranged at the top of the long strip-shaped plate-shaped structure, the whole long strip-shaped plate-shaped structure is arranged above the cooling cavity, the bottom of the long strip-shaped plate-shaped structure is inserted into the cooling cavity, a second cavity is arranged inside the long strip-shaped plate-shaped structure, the plurality of sampling probes are arranged in the second cavity, the sampling probes are of an inverted L-shaped structure, the air inlet end of the inverted L-shaped structure penetrates through the side wall of the long strip-shaped plate-shaped structure and extends to the outside of the long strip-shaped plate-shaped structure for collecting tail gas discharged by an aircraft engine, the air outlet end of the inverted L-shaped structure penetrates through the bottom of the long strip-shaped plate-shaped structure and extends to the inside of the first cavity and is communicated with the tail gas mixing header pipe, the tail gas collected by the plurality of probes is mixed in the tail gas mixing header pipe, and the flow rate of the tail gas flowing through the sampling probes is controlled to be 20m/s;
a compressed air cooling pipe, compressed air cooling pipe gives vent to anger the end and inserts inside the first cavity, compressed gas air feed source is connected to the inlet end, through to the intraductal compressed gas that lets in of compressed air cooling for to the inside tail gas of cooling chamber internal environment, tail gas mixing house steward and tail gas mixing house steward the processing of cooling down, the compressed gas via after the cooling is handled the compressed gas export discharge.
4. The high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed as claimed in claim 3, wherein one end of the tail gas mixing header pipe is a bleed air end, the bleed air end is communicated with the gas transmission pipeline through a bleed air pipeline and then is connected to the gas inlet end of the tail gas analyzer through the gas transmission pipeline, and the other end of the tail gas mixing header pipe is a blowback pipeline end.
5. The high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed as claimed in claim 4, wherein the back-flushing pipeline is connected to the back-flushing pipeline, a first valve is further arranged on the back-flushing pipeline, and the first valve is opened while the second valve is closed, so that redundant fuel oil entering the interior of the sampling probe is discharged or residual compressed air used for cleaning the tail gas analyzer after gas calibration is discharged;
still set up the second valve on the bleed pipeline still set up the third valve on the gas-supply pipeline between tail gas collection unit and the tail gas analysis appearance, just the third valve set up in before the vacuum pump, through control the second valve with opening and closing of third valve for control gets into the tail gas aeration volume in the tail gas analysis appearance.
6. The high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed as claimed in claim 5, wherein a tail gas emptying pipeline is further arranged on a gas transmission pipeline between the vacuum pump and the tail gas analyzer, a fourth valve is arranged on the tail gas emptying pipeline, and the fourth valve is opened to empty redundant tail gas.
7. The high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed as claimed in claim 1, wherein a temperature sensor and a pressure sensor are further arranged on the gas transmission pipeline and used for measuring the temperature and the pressure inside the gas transmission pipeline in real time.
8. The device as defined in claim 1 adapted for use at high altitudesThe high-temperature negative-pressure tail gas sampling system of the test bed is characterized in that the tail gas analyzer is a combined gas analyzer and is used for analyzing O contained in tail gas exhausted by an aircraft engine 2 、CO、CO 2 、NO 2 、NO、CH 4 、SO 2 The gas inside is analyzed for composition and content.
9. The high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed as claimed in claim 1, wherein the data acquisition and transmission unit is a PLC controller, an input end of the PLC controller is connected with the tail gas analyzer, and an output end of the PLC controller is connected with the first upper computer.
10. A high-temperature negative-pressure tail gas sampling method, which is carried out by using the high-temperature negative-pressure tail gas sampling system suitable for the high-altitude test bed as claimed in any one of claims 1 to 9, and comprises the following steps:
calibrating a tail gas analyzer: calibrating the tail gas analyzer by using a plurality of standard gases, and introducing compressed air into the tail gas analyzer after calibration is finished for removing residual standard gases;
installing tail gas sampling equipment: firstly, correspondingly placing the air inlet end of the hybrid sampling probe behind the outlet section of the aircraft engine tail nozzle or the combustion chamber, starting the operation of the aircraft engine or the combustion chamber in a high-altitude environment, and discharging tail gas;
and (3) removing redundant fuel oil or residual compressed air: opening the first valve while closing the second valve, exhausting redundant fuel oil entering the sampling probe, exhausting compressed air in the tail gas analyzer, and closing the first valve after exhausting redundant fuel oil and compressed air;
tail gas collection and cooling: tail gas enters the sampling probes through the gas inlet ends of the sampling probes, and then enters the tail gas mixing main pipe through the gas outlet ends of the sampling probes for tail gas mixing, the flow rate of the tail gas in the sampling probes is controlled to be no more than 20m/s, meanwhile, compressed air is introduced into the compressed air cooling pipe for cooling the tail gas in the environment inside the cooling cavity, the tail gas mixing main pipe and the tail gas mixing main pipe, so that the temperature of the mixed tail gas in the tail gas mixing main pipe is cooled to 65 ℃, and the compressed air after the cooling treatment is discharged through the compressed gas outlet;
analyzing the components of the tail gas: opening the second valve and the third valve, enabling the cooled tail gas to sequentially enter a gas introducing pipeline and a gas conveying pipeline through a gas introducing end of the tail gas mixing main pipe, finally entering a tail gas analyzer for tail gas component analysis to obtain tail gas component information, and controlling the introduction amount of the tail gas in the tail gas analyzer by controlling the second valve on the gas introducing pipeline and the third valve on the gas conveying pipeline;
tail gas component information acquisition and transmission: the PLC controller collects the tail gas composition information, then transmits the tail gas composition information to the first upper computer for storage, calibration and analysis, and meanwhile, the second upper computer collects monitoring information of a plurality of sensors in the aero-engine or the combustion chamber and analyzes the overall performance of the aero-engine or the combustion chamber.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117990381A (en) * | 2024-04-03 | 2024-05-07 | 成都晨发泰达航空科技股份有限公司 | Test device for simulating and verifying aeroengine combustion chamber aerodynamic performance |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117990381A (en) * | 2024-04-03 | 2024-05-07 | 成都晨发泰达航空科技股份有限公司 | Test device for simulating and verifying aeroengine combustion chamber aerodynamic performance |
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