CN211527960U - Aeroengine gas monitoring and analyzing system - Google Patents
Aeroengine gas monitoring and analyzing system Download PDFInfo
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- CN211527960U CN211527960U CN201922416602.6U CN201922416602U CN211527960U CN 211527960 U CN211527960 U CN 211527960U CN 201922416602 U CN201922416602 U CN 201922416602U CN 211527960 U CN211527960 U CN 211527960U
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Abstract
The utility model discloses an aeroengine gas monitoring and analyzing system, include: the sampling system is used for sampling the aircraft engine fuel gas in the experiment cabin; the pretreatment system is used for controlling the temperature and the flow of the sampled gas of the aircraft engine; the analysis system is used for performing hydrocarbon analysis and infrared analysis on the pretreated aircraft engine gas and outputting a signal; the sampling system, the preprocessing system and the analysis system are sequentially connected, the analysis system comprises a hydrocarbon analysis system and an infrared analysis system which are sequentially connected, and the output end of the residual preprocessing system of the hydrocarbon analysis system is connected. The utility model discloses simple structure, can be convenient carry out monitoring analysis to the aeroengine gas to analysis sample component, and send out the signal.
Description
Technical Field
The utility model relates to an aviation technical field, more specifically say, in particular to aeroengine gas monitoring and analyzing system.
Background
The aviation industry of China has been greatly promoted, but a more serious problem exists at present, namely that an aircraft engine can not realize major breakthrough all the time; in order to enable domestic aero-engines to make a great leap, the state is now energetically developing aero-engines. The aeroengine is separated from the original middle aviation industry group to form a Chinese aeroengine group. At present, the combustion efficiency of the engine can not be monitored by a set of monitoring system with a simple structure under various working conditions. Therefore, the gas monitoring and analyzing system for the aircraft engine needs to be developed.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aeroengine gas monitoring analytic system to overcome the defect that prior art exists.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
an aircraft engine gas monitoring and analyzing system comprising: the sampling system is used for sampling the aircraft engine fuel gas in the experiment cabin; the pretreatment system is used for controlling the temperature and the flow of the sampled gas of the aircraft engine; the analysis system is used for performing hydrocarbon analysis and infrared analysis on the pretreated aircraft engine gas and outputting a signal; the sampling system, the preprocessing system and the analysis system are sequentially connected, the analysis system comprises a hydrocarbon analysis system and an infrared analysis system which are sequentially connected, and the output end of the residual preprocessing system of the hydrocarbon analysis system is connected.
Further, sampling system is used for taking a sample the aeroengine gas in the experiment cabin, and this sampling system locates the flange in the protection cabin outside including the protection cabin of locating the experiment cabin outside, evenly be equipped with five groups of sampling unit on the flange, every group sampling unit includes three sample connection that is isosceles triangle, the sample connection passes through the sample pipeline and is connected with pretreatment systems.
Furthermore, the pretreatment system comprises a pretreatment box and a high-temperature box, the high-temperature box is arranged in the pretreatment box, five groups of pretreatment units are arranged in the high-temperature box, each group of pretreatment units is connected with one group of sampling units, a first sampling pipeline of each group of sampling units is connected with a first pretreatment pipeline of the pretreatment units, a second sampling pipeline of each group of sampling units is connected with a second pretreatment pipeline of the pretreatment units, and a third sampling pipeline of each group of sampling units is connected with a third pretreatment pipeline of the pretreatment units;
the output end of the first pretreatment pipeline is connected with a hydrocarbon analysis system, and the first pretreatment pipeline is sequentially provided with a pneumatic ball valve PV1, a T-shaped filter TF1, a pneumatic ball valve PV16, a pressure reducing valve PR, a bypass filter BF, a needle valve NV, a fine filter F17 and a filter F; the output ends of the second pretreatment pipeline and the third pretreatment pipeline are connected between a pneumatic ball valve PV16 and a pressure reducing valve PR; the second pretreatment pipeline is sequentially connected with a pneumatic ball valve PV2, a T-shaped filter TF2 and a pneumatic ball valve PV17, and the third pretreatment pipeline is sequentially connected with a pneumatic ball valve PV3, a T-shaped filter TF3 and a pneumatic ball valve PV 18.
Furthermore, the pretreatment box is also provided with an instrument air inlet and a back-blowing nitrogen inlet, the instrument air inlet is connected with an instrument air pipeline in the pretreatment box, the high-temperature box is provided with five joint interfaces SZ, the instrument air pipeline is provided with a filtering and reducing valve FR1, the output end of the filtering and reducing valve FR1 is connected with four branch pipelines, each branch pipeline is provided with a three-way electromagnetic valve (SXV1-SXV4), and the four branch pipelines are respectively connected with the four joint interfaces SZ; the back-blowing nitrogen inlet is connected with a back-blowing nitrogen pipeline in the pretreatment box, the back-blowing nitrogen pipeline is connected with another connector SZ on the high-temperature box, and a ball valve BV and a filtering pressure reducing valve FR2 are sequentially arranged on the back-blowing nitrogen pipeline.
Further, the hydrocarbon analysis system comprises five hydrocarbon analyzers, the five hydrocarbon analyzers are respectively connected with the output ends of the five pretreatment units, the model of each hydrocarbon analyzer is FIDMAT6E, and the output ends of the five hydrocarbon analyzers are connected with the infrared analysis system.
Further, the infrared analysis system comprises five infrared analyzers, the five infrared analyzers are respectively connected with the output ends of the five carbon hydrogen analyzers, and the model of each infrared analyzer is ULTRAMAT 6E.
Compared with the prior art, the utility model has the advantages of: the utility model discloses simple structure, can be convenient monitor the analysis to the aeroengine gas to analysis sample component, and send out the signal.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a frame diagram of the gas monitoring and analyzing system of the aircraft engine of the present invention.
Fig. 2 is a schematic diagram of the gas monitoring and analyzing system for an aircraft engine of the present invention.
Fig. 3 is a structural diagram of the sampling system of the present invention.
Fig. 4 is a structural diagram of the flange in the sampling system of the present invention.
Fig. 5 is a diagram of the structure of the pretreatment system of the present invention.
Detailed Description
The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, and the scope of the present invention can be more clearly and clearly defined.
Referring to fig. 1 and 2, the utility model provides an aeroengine gas monitoring and analyzing system, include: the sampling system 10 is used for sampling the aircraft engine gas in the experiment chamber 101; the pretreatment system 20 is used for controlling the temperature and the flow of the sampled aircraft engine gas; the analysis system 30 is used for performing hydrocarbon analysis and infrared analysis on the pretreated aircraft engine gas and outputting a signal; the sampling system 10, the pretreatment system 20 and the analysis system 30 are sequentially connected, the analysis system 30 comprises a hydrocarbon analysis system 40 and an infrared analysis system 50 which are sequentially connected, and the output ends of the pretreatment system 20 and the hydrocarbon analysis system 40 are connected.
Referring to fig. 3 and 4, the sampling system 10 is used for sampling aircraft engine fuel gas in a test chamber 101, the sampling system 10 includes a protection chamber 102 disposed outside the test chamber 101, and a flange 103 disposed outside the protection chamber 102, five groups of sampling units EHB1-EHB5 (i.e., five bundled tube cables) are uniformly disposed on the flange 103, each group of sampling units includes three sampling ports 104 in the shape of an isosceles triangle, and the sampling ports 104 are connected to the pretreatment system 20 through sampling pipes.
In this embodiment, there are 15 sampling points, which can ensure that the sample taken out from the test chamber will not change greatly when passing through the umbilical.
Referring to fig. 5, the pretreatment system 20 includes a pretreatment tank and a high temperature tank, the high temperature tank is disposed in the pretreatment tank, five groups of pretreatment units are disposed in the high temperature tank, each group of pretreatment units is connected with a group of sampling units, wherein a first sampling pipeline of each group of sampling units is connected with a first pretreatment pipeline of the pretreatment units, a second sampling pipeline of each group of sampling units is connected with a second pretreatment pipeline of the pretreatment units, and a third sampling pipeline of each group of sampling units is connected with a third pretreatment pipeline of the pretreatment units.
The output end of the first pretreatment pipeline is connected with a hydrocarbon analysis system 40, and a pneumatic ball valve PV1, a T-shaped filter TF1, a pneumatic ball valve PV16, a pressure reducing valve PR, a bypass filter BF, a needle valve NV, a fine filter F17 and a filter F are sequentially arranged on the first pretreatment pipeline; the output ends of the second pretreatment pipeline and the third pretreatment pipeline are connected between a pneumatic ball valve PV16 and a pressure reducing valve PR; the second pretreatment pipeline is sequentially connected with a pneumatic ball valve PV2, a T-shaped filter TF2 and a pneumatic ball valve PV17, and the third pretreatment pipeline is sequentially connected with a pneumatic ball valve PV3, a T-shaped filter TF3 and a pneumatic ball valve PV 18.
In this embodiment, the first pre-processing line is used for analysis, and the second pre-processing line and the third pre-processing line are bypassed, which reduces the lag time when switching the analysis.
In order to prevent the pipeline from being blocked in the pretreatment, the analysis system can be operated in a central control room through the PLC, and the analyzed data is stored and compared through the PLC. The pretreatment box is also provided with an instrument air inlet 201 and a back-blowing nitrogen inlet 202, the instrument air inlet 201 is connected with an instrument air pipeline in the pretreatment box, the high-temperature box is provided with five connector interfaces SZ, the instrument air pipeline is provided with a filtering and reducing valve FR1, the output end of the filtering and reducing valve FR1 is connected with four branch pipelines, each branch pipeline is provided with a three-way electromagnetic valve (SXV1-SXV4), and the four branch pipelines are respectively connected with the four connector interfaces SZ; the back-blowing nitrogen inlet 202 is connected with a back-blowing nitrogen pipeline in the pretreatment box, the back-blowing nitrogen pipeline is connected with another connector SZ on the high-temperature box, and a ball valve BV and a filtering pressure reducing valve FR2 are sequentially arranged on the back-blowing nitrogen pipeline.
Through the design, the temperature in the high-temperature box can be controlled within 160 +/-10 ℃, the temperature range is 0-200 ℃, the temperature can be set by self, the temperature control precision is +/-5 ℃, the surface temperature of the box body is less than or equal to 50 ℃, the flow of a sample is controlled by 0-60L/H, the pressure can be set to 0-1barG, and the pressure can be set.
Referring to fig. 2, the hydrocarbon analysis system 40 includes five hydrocarbon analyzers, the five hydrocarbon analyzers are respectively connected to the output ends of the five pretreatment units, each hydrocarbon analyzer is fidam 6E, and the output end of the five hydrocarbon analyzer is connected to the infrared analysis system 50.
Referring to fig. 2, the infrared analysis system 50 includes five infrared analyzers, and the five infrared analyzers are respectively connected to the output terminals of the five carbon hydrogen analyzers, and each infrared analyzer is of an ULTRAMAT6E type.
The utility model discloses a pass through the protection cabin to the sample after the burning of engine experiment cabin with the mode of sampling, get into analytic system and remove the analysis, according to the numerical value that different sampling points were surveyed, carry out combustion efficiency's calculating, provide help to the manufacturing performance of engine.
Because 15 sampling points are distributed in the experiment cabin, a protection cabin is arranged outside the experiment cabin, the sample pipelines are relatively concentrated on a circular surface with the diameter of 140 in the protection cabin, the 15 sample pipelines are divided into 5 pipe cables, each pipe cable is provided with 3 pipeline, and the samples are connected to the pretreatment box through the pipe cables; the analytical instrument and the pretreatment box are arranged in a combined cabinet (3-link cabinet), 5 groups of analyzers are arranged in the combined cabinet, 5 paths of samples can be analyzed simultaneously, and analyzed data are stored through external PLC configuration software so as to compare and analyze the combustion efficiency of the engine.
Although the embodiments of the present invention have been described with reference to the accompanying drawings, various changes and modifications can be made by the owner within the scope of the appended claims, and the protection scope of the present invention should not be exceeded by the claims.
Claims (6)
1. An aircraft engine gas monitoring and analyzing system, comprising: the sampling system is used for sampling the aircraft engine fuel gas in the experiment cabin; the pretreatment system is used for controlling the temperature and the flow of the sampled gas of the aircraft engine; the analysis system is used for performing hydrocarbon analysis and infrared analysis on the pretreated aircraft engine gas and outputting a signal; the sampling system, the preprocessing system and the analysis system are sequentially connected, the analysis system comprises a hydrocarbon analysis system and an infrared analysis system which are sequentially connected, and the output end of the residual preprocessing system of the hydrocarbon analysis system is connected.
2. The aircraft engine gas monitoring and analyzing system as claimed in claim 1, wherein the sampling system is used for sampling the aircraft engine gas in the experiment chamber, the sampling system comprises a protection chamber arranged outside the experiment chamber and a flange arranged outside the protection chamber, five groups of sampling units are uniformly arranged on the flange, each group of sampling units comprises three sampling ports in the shape of an isosceles triangle, and the sampling ports are connected with the pretreatment system through sampling pipelines.
3. The aircraft engine gas monitoring and analyzing system of claim 2, wherein the pretreatment system comprises a pretreatment tank and a high temperature tank, the high temperature tank is arranged in the pretreatment tank, five groups of pretreatment units are arranged in the high temperature tank, each group of pretreatment units is connected with one group of sampling units, wherein a first sampling pipeline of each group of sampling units is connected with a first pretreatment pipeline of the pretreatment unit, a second sampling pipeline of each group of sampling units is connected with a second pretreatment pipeline of the pretreatment unit, and a third sampling pipeline of each group of sampling units is connected with a third pretreatment pipeline of the pretreatment unit;
the output end of the first pretreatment pipeline is connected with a hydrocarbon analysis system, and the first pretreatment pipeline is sequentially provided with a pneumatic ball valve PV1, a T-shaped filter TF1, a pneumatic ball valve PV16, a pressure reducing valve PR, a bypass filter BF, a needle valve NV, a fine filter F17 and a filter F; the output ends of the second pretreatment pipeline and the third pretreatment pipeline are connected between a pneumatic ball valve PV16 and a pressure reducing valve PR; the second pretreatment pipeline is sequentially connected with a pneumatic ball valve PV2, a T-shaped filter TF2 and a pneumatic ball valve PV17, and the third pretreatment pipeline is sequentially connected with a pneumatic ball valve PV3, a T-shaped filter TF3 and a pneumatic ball valve PV 18.
4. The aircraft engine gas monitoring and analyzing system of claim 3, wherein the pretreatment tank is further provided with an instrument air inlet and a back-blowing nitrogen inlet, the instrument air inlet is connected with an instrument air pipeline in the pretreatment tank, the high-temperature tank is provided with five connector interfaces SZ, the instrument air pipeline is provided with a filter pressure reducing valve FR1, the output end of the filter pressure reducing valve FR1 is connected with four branch pipelines, each branch pipeline is provided with a three-way solenoid valve (SXV1-SXV4), and the four branch pipelines are respectively connected with the four connector interfaces SZ; the back-blowing nitrogen inlet is connected with a back-blowing nitrogen pipeline in the pretreatment box, the back-blowing nitrogen pipeline is connected with another connector SZ on the high-temperature box, and a ball valve BV and a filtering pressure reducing valve FR2 are sequentially arranged on the back-blowing nitrogen pipeline.
5. The aircraft engine gas monitoring and analyzing system as claimed in claim 3, wherein the hydrocarbon analyzing system comprises five hydrocarbon analyzers, the five hydrocarbon analyzers are respectively connected with the output ends of the five preprocessing units, each hydrocarbon analyzer is FIDMAT6E, and the output end of the five hydrocarbon analyzer is connected with the infrared analyzing system.
6. The aircraft engine gas monitoring and analyzing system as claimed in claim 3, wherein the infrared analyzing system comprises five infrared analyzers, the five infrared analyzers are respectively connected with the output ends of the five carbon hydrogen analyzers, and each infrared analyzer is of an ULTRAMAT6E type.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922416602.6U CN211527960U (en) | 2019-12-29 | 2019-12-29 | Aeroengine gas monitoring and analyzing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922416602.6U CN211527960U (en) | 2019-12-29 | 2019-12-29 | Aeroengine gas monitoring and analyzing system |
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| Publication Number | Publication Date |
|---|---|
| CN211527960U true CN211527960U (en) | 2020-09-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201922416602.6U Active CN211527960U (en) | 2019-12-29 | 2019-12-29 | Aeroengine gas monitoring and analyzing system |
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| CN (1) | CN211527960U (en) |
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- 2019-12-29 CN CN201922416602.6U patent/CN211527960U/en active Active
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