CN207379917U - Aero-engine gas component and density monitoring system - Google Patents
Aero-engine gas component and density monitoring system Download PDFInfo
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- CN207379917U CN207379917U CN201721531743.7U CN201721531743U CN207379917U CN 207379917 U CN207379917 U CN 207379917U CN 201721531743 U CN201721531743 U CN 201721531743U CN 207379917 U CN207379917 U CN 207379917U
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Abstract
The utility model discloses a kind of aero-engine gas component and density monitoring system, belongs to the technical field of gas detection, including sender unit, signal receiving device, protective device, light-source system and control system；Sender unit and signal receiving device are separately positioned on the opposite both sides in aeroengine combustor buring room；Protective device includes the quartz-optical window being sealingly disposed in the opposite sides of aeroengine combustor buring room and the protective cover being separately positioned on outside sender unit and signal receiving device；Quartz-optical window can be 1000 5500nm by the spectral region of light；Light-source system includes semiconductor laser with tunable and fiber coupler；Control system includes photodetector, signal amplifier, demodulation of phase locking module and memory module；Sender unit is electrically connected by optical fiber with fiber coupler；Signal receiving device is electrically connected by coaxial cable with photodetector.The system is realized carries out in situ detection to aero-engine combustion gas.
Description
Technical field
The utility model is related to the technical field of gas detection, more particularly to a kind of aero-engine gas component and dense
Spend monitoring system.
Background technology
Spacecraft during transmitting or operation on orbit, it is necessary to detect the gas componant in engine combustion room, for identifying,
Judge whether engine is working properly, provides Fuel-optimal control.The harmful components of engine gas mainly have CH compounds, NO
Compound, NH compounds and particulate matter；Wherein CH compounds are the main components of fuel, and the content reflection in combustion gas is started
The efficiency of combustion of machine；NO compounds be it is high-temperature oxygen-enriched under the conditions of product, reflect the health status of engine；NH compounds are CH
Compound and NO compound reaction products, detect it contamination control that can be achieved to engine.Engine chamber limit temperature
The direct power of test of the lower gas component of degree and concentration, is to solve the problems, such as engine emission active control and contamination control, can
The innovation and development of aero engine technology are greatly promoted, new approaches are provided for the barrier diagnosis of engine and status monitoring.
But conventional gas sensors can not work under high temperature, high pressure, high flow rate and multiphase flow adverse circumstances.Boat at present
Combustion gas is mainly introduced measuring instrumentss progress constituent analysis by the analysis of empty engine gas using sampler, then by combustion gas into
Divided data calculates a kind of measuring method of the parameters such as efficiency of combustion, ignition temperature and pollutant emission, can not realize that high temperature is disliked
The in situ detection of gas component in bad environment.
Utility model content
It is existing to improve the purpose of this utility model is to provide a kind of aero-engine gas component and density monitoring system
There is the technical issues of technology is difficult to carry out in situ detection to aero-engine combustion gas.
The utility model provides a kind of aero-engine gas component and density monitoring system, which is based on tunable half
Conductor Laser absorption spectroscopy techniques are implemented；Including sender unit, signal receiving device, protective device, light-source system and
Control system；Sender unit and signal receiving device are separately positioned on the opposite both sides in aeroengine combustor buring room；Protection
Device includes the quartz-optical window being sealingly disposed in the opposite sides of aeroengine combustor buring room and is separately positioned on signal
The protective cover made of iron and steel material quality outside emitter and signal receiving device；Quartz-optical window can pass through the spectrum model of light
It encloses for 1000-5500nm；Light-source system include set there are three laser channeling semiconductor laser with tunable and with it is adjustable
The fiber coupler of humorous semiconductor laser electrical connection；Three laser channelings difference launch wavelengths for 1.6um, 1.5 um and
The light beam of 5.2um is respectively as CH4、NH3With the absorption light of NO；Control system includes photodetector, is electrically connected with photodetector
The signal amplifier connect, the demodulation of phase locking module being electrically connected with signal amplifier and the storage being electrically connected with demodulation of phase locking module
Module；Sender unit is electrically connected by optical fiber with the fiber coupler；Signal receiving device passes through coaxial cable and light
Electric explorer is electrically connected.
Specifically, semiconductor laser with tunable is tunable distributed feedback laser.
Further, the minimum temperature that English optical window can be born is 1700 DEG C, and minimum pressure is 30Mp.
Further, sender unit and signal receiving device are fixed on aeroengine combustor buring room phase by flange
To both sides；Quartz-optical window is sealingly disposed on flange.
Further, the threading hole passed through for optical fiber and/or coaxial cable is provided on protective cover.
Compared with prior art, the advantage of the utility model is：
Aero-engine gas component and density monitoring system provided by the utility model are partly led by optical fiber by tunable
Laser beam in body laser is imported into sender unit, and combustion chamber opposite is transmitted to after sender unit adjustment light beam
Signal receiving device, after the light beam arriving signal reception device after combustion gas absorbs, visited by the photoelectricity in control system
Device detection signal is surveyed, the signal that detector detects passes through signal amplifier（PDA）After amplification, lock phase is entered by coaxial cable
Demodulation module carries out data processing, obtains gas component and concentration, is stored in memory module.Due to aeroengine combustor buring room
Ignition process can generate instantaneous high temperature, high pressure, HI high impact air-flow, be specifically designed protective device therefore, by being sent out in signal
Protective cover is installed outside injection device and signal receiving device additional to reduce the vibration of impact air-flow generation, in aeroengine combustor buring room phase
Sender unit and signal are connect to quartz-optical window is set to effectively prevent high temperature, high pressure, HI high impact air-flow on both sides
Coup injury is generated by device, sender unit and signal receiving device is effectively protected not to be damaged, to ensure to be entirely
System normal work, realizes and carries out in situ detection to aero-engine combustion gas.
Description of the drawings
It is required in being described below to embodiment in order to illustrate more clearly of the technical scheme in the embodiment of the utility model
Attached drawing to be used is briefly described, it should be apparent that, the accompanying drawings in the following description is only some realities of the utility model
Example is applied, it for those of ordinary skill in the art, without creative efforts, can also be according to these attached drawings
Other attached drawings are obtained, wherein：
Fig. 1 is the structure diagram of aero-engine gas component and density monitoring system provided in this embodiment；
Fig. 2 is that sender unit and signal receive in aero-engine gas component shown in Fig. 1 and density monitoring system
The scheme of installation of device；
Fig. 3 is NO, CH4, NH3Gaseous absorption line figure of three kinds of gases near 5um wave bands and 0.9um-1.6um wave bands
Spectrum.
Label：1- sender units；2- signal receiving devices；3- quartz-optical windows；4- protective covers；5- is tunable partly
Conductor laser；6- fiber couplers；7- photodetectors；8- signal amplifiers；9- demodulation of phase locking modules；10- memory modules；
11- flanges；100- aeroengine combustor burings room.
Specific embodiment
Below by the technical scheme in the utility model embodiment is clearly and completely described, it is clear that described
Embodiment is only the part of the embodiment of the utility model, instead of all the embodiments.Based on the implementation in the utility model
Example, all other embodiment that those of ordinary skill in the art are obtained without making creative work belong to
The scope of the utility model protection.
Real-time online spectroscopy detection technique extensively, in a manner of continuous work becomes gas detection by its multicomponent, scope
Desirable technique is the developing direction and technology mainstream of current conventional on-line checking pollutant emission technology.Spectroscopy technology is main
There is differential optical absorption spectroscopy（DOAS）, differential absorption lidar（DIAL）, Fourier Transform Spectroscopy（FTIR）
And tunable diode laser absorption spectroscopy（TDLAS）Wait absorption spectroscopy techniques.Compared with other gas measuring methods, TDLAS
Technology mainly has that detectivity is high, precision is high, online non-cpntact measurement in real time, selectivity is good, it is pre- that gas need not be carried out
The advantages that processing.
Tunable diode laser absorption spectroscopy（TDLAS）Technology is a kind of advanced spectral absorption technology.Laser has
High monochromaticity, directionality and high intensity, and the concentration of specific gas, TDLAS skills can be measured in very wide range ability
The operation principle of art be by measure the variation of spectral signal caused by tested absorption of the gas molecule on feature wave crest come
Analyze its concentration.Electric current excitation under, semiconductor laser with tunable 5 launches the laser of specific wavelength, the wavelength sent by
The chemical constituent of 5 crystal of semiconductor laser with tunable determines, with the variation of current strength, semiconductor laser with tunable 5
Launch wavelength can change in a narrow scope, can be special to tested gas molecule with high speed test by this characteristic
Levy the consistent wavelength of wave crest.Since the wavelength of transmitting is very accurate, for specific under test gas ingredient may be selected its from
The absorption bands of interference is analyzed so that is measured the anti-interference with height.The appearance of TDLAS, well solves
Some problems encountered in traditional spectral detection, for example, be exceedingly fast response time, high sensitivity, some realities such as highly selective
When continuous monitoring requirement.Measurement technology based on TDLAS principles natural calamity, industrial process pernicious gas content detection and
The severe environmental conditions application aspect such as mine and the detection of natural gas line methane concentration has great potential value.
Aero-engine gas component and density monitoring system provided in this embodiment, are based on tunable semiconductor and swash
What optical absorption spectra technology was implemented；As depicted in figs. 1 and 2, including sender unit 1, signal receiving device 2, protective device,
Light-source system and control system；Sender unit 1 and signal receiving device 2 are separately positioned on aeroengine combustor buring room
100 opposite both sides；Protective device includes the quartz optical window being sealingly disposed in 100 opposite sides of aeroengine combustor buring room
Mouth 3 and protective cover 4 made of iron and steel material quality being separately positioned on outside sender unit 1 and signal receiving device 2；Quartz
Optical window 3 can be 1000-5500nm by the spectral region of light；Light-source system includes setting, and there are three the adjustable of laser channeling
Humorous semiconductor laser 5 and the fiber coupler 6 being electrically connected with semiconductor laser with tunable 5；Three laser channeling difference
Launch wavelength is the light beam of 1.6um, 1.5 um and 5.2um respectively as CH4、NH3With the absorption light of NO；Control system includes light
Electric explorer 7, the signal amplifier 8 being electrically connected with photodetector 7, the demodulation of phase locking module 9 being electrically connected with signal amplifier 8
And the memory module 10 being electrically connected with demodulation of phase locking module 9；Sender unit 1 is electrically connected by optical fiber and fiber coupler 6
It connects；Signal receiving device 2 is electrically connected by coaxial cable with photodetector 7.
Several aspects are taken into full account when choice of spectrum is carried out to gas molecules sorb spectrum：First, absorption line
Intensity is sufficiently large, convenient for detection, also allows for distinguishing with the absorption line of surrounding；2nd, selection absorption line to avoid and other
The absorption line of gas molecule overlaps, and improves detection accuracy；3rd, selection absorption line will with current laser and
Detection device is consistent.According to 2012 databases of HITRAN, three kinds of under test gas NO, CH are can obtain4, NH3With two kinds of interference gas
Body H2O and CO2Absorption line.As shown in figure 3, it can be seen from the figure that CH4And NH3It absorbs and imitates in 0.9um-1.6um wave bands
Fruit is strong and interference is weaker, therefore selects 1.6um and 1.5 um respectively as respective absworption peak.Since NO is in 0.9um-
1.6um wave bands and CH4And H2O absorption spectras overlap, therefore selection makes choice near 5um wavelength, and final choice 5.2um makees
It is disturbed for the characteristic absorption peak of NO with reducing.
The present embodiment calculates the concentration parameter for obtaining gas by Lambert-Beer (Lambert-Beer) law；It surveys first
The original light intensity signal of the light intensity signal after gas absorbs and laser is measured, then according to selected characteristic absorption line, is calculated
Go out that the spectral line line that actually measures is strong and line style, it is possible to derive the concentration of gas.According to Lambert-Beer laws, in medium
One timing of the environmental conditions such as temperature and pressure, if light beam, by the medium, medium is proportional to medium to the absorbance of light
The product of concentration and dielectric thickness.Since portions incident light intensity is by Absorption of Medium, through medium transmitted light intensity just
Weaken, the concentration of absorbing medium is bigger, then the attenuation of incident light is more apparent.Incident light pass through medium after intensity expression formula such as
Under：
In formula：I0For incident intensity；ItFor output intensity；α (v) be absorption coefficient of the gas at frequency v, unit cm-1⋅atm−1；P is pressure, unit atm；C is the volumetric concentration percentage for absorbing gas；L is that total gas absorbs light path, single
Position cm.Therefore, when acquisition gas absorption light path, under test gas pressure, incidence and output intensity, medium are to absorption coefficient of light etc.
During parameter, it becomes possible to acquire under test gas concentration C according to formula.
The requirement to light source is detected for TDLAS gases, semiconductor laser with tunable 5 is tunable point in the present embodiment
Cloth is fed back（DFB）Laser.The spectral width of Distributed Feedback Laser is much smaller than under test gas line-width（General tens MHZ ~ hundreds of
MHZ）So that TDLAS technologies have very high spectral resolution, can be to a certain specific absorption spectral line of gas absorption spectrum to be measured
Making choice property is analyzed, and obtains under test gas concentration.Since the variation of Distributed Feedback Laser output frequency is by temperature, PN junction area electric current
With the influence of Injection Current, it is possible to which, using two kinds of modulation techniques of temperature modulation and current-modulation, wherein temperature modulation is excellent
Point is that scope is big, and shortcoming is that modulation accuracy is low；The advantages of current-modulation is precision height, and shortcoming is that modulation range is small.The present embodiment
Its wavelength is locked with the method that Injection Current is combined using control light source internal operating temperature.
Further, the minimum temperature that English optical window 3 can be born is 1700 DEG C, and minimum pressure is 30Mp, to ensure
The purpose of protection signal emitter 1 and signal receiving device 2 can be played.
Further, sender unit 1 and signal receiving device 2 are fixed on aeroengine combustor buring by flange 11
The opposite both sides in room 100；Quartz-optical window 3 is sealingly disposed on flange 11.
Further, it is provided with the threading hole passed through for optical fiber and/or coaxial cable on protective cover 4.
In conclusion aero-engine gas component provided in this embodiment and density monitoring system, based on TDLAS technologies
Three classes gas component can be achieved at the same time（Hydrocarbon, hydronitrogen, oxynitrides）Detection and measurement of concetration, have
Detectivity is high, precision is high, online non-cpntact measurement in real time, selectivity is good, the advantages that need not being pre-processed to gas,
Overcome the shortcomings that conventional gas sensors can not work under high temperature, high pressure, high flow rate and multiphase flow adverse circumstances, protection dress
The setting put solves the problems, such as aero-engine gas component and concentration in-situ test.In hypersonic aircraft, near space
There is the wide market demand in the fields such as aircraft, aero-engine, high temperature ground experiment platform, and popularization and application will be state
Anti-, industry and development in science and technology generate extremely important effect, so as to create great social benefit.
It these are only the embodiment of the utility model, it does not limit the scope of the patent of the present invention, every utilization
The equivalent structure or equivalent flow shift that the utility model description is made directly or indirectly is used in other relevant
Technical field is equally included in the patent within the scope of the utility model.
Claims (5)
1. a kind of aero-engine gas component and density monitoring system, which is characterized in that the system is based on tunable semiconductor
Laser absorption spectroscopy is implemented；Including sender unit（1）, signal receiving device（2）, protective device, light-source system with
And control system；
The sender unit（1）With signal receiving device（2）It is separately positioned on aeroengine combustor buring room（100）Opposite
Both sides；
The protective device includes being sealingly disposed in aeroengine combustor buring room（100）Quartz-optical window in opposite sides
（3）And it is separately positioned on the sender unit（1）With signal receiving device（2）Outer protects made of iron and steel material quality
Cover（4）；
The quartz-optical window（3）Can be 1000-5500nm by the spectral region of light；
The light-source system includes setting the semiconductor laser with tunable there are three laser channeling（5）And with it is described tunable
Semiconductor laser（5）The fiber coupler of electrical connection（6）；
Three laser channelings difference launch wavelength is the light beam of 1.6um, 1.5 um and 5.2um respectively as CH4、NH3And NO
Absorption light；
The control system includes photodetector（7）And the photodetector（7）The signal amplifier of electrical connection（8）And
The signal amplifier（8）The demodulation of phase locking module of electrical connection（9）And with the demodulation of phase locking module（9）The storage of electrical connection
Module（10）；
The sender unit（1）Pass through optical fiber and the fiber coupler（6）Electrical connection；
The signal receiving device（2）Pass through coaxial cable and the photodetector（7）Electrical connection.
2. aero-engine gas component according to claim 1 and density monitoring system, which is characterized in that described adjustable
Humorous semiconductor laser（5）For tunable distributed feedback laser.
3. aero-engine gas component according to claim 1 and density monitoring system, which is characterized in that the English light
Learn window（3）The minimum temperature that can be born is 1700 DEG C, and minimum pressure is 30Mp.
4. aero-engine gas component and density monitoring system according to claim 1 or 3, which is characterized in that described
Sender unit（1）With signal receiving device（2）Pass through flange（11）It is fixed on aeroengine combustor buring room（100）Relatively
Both sides；
The quartz-optical window（3）It is sealingly disposed in the flange（11）On.
5. aero-engine gas component according to claim 1 and density monitoring system, which is characterized in that the protection
Cover（4）On be provided with the threading hole passed through for optical fiber and/or coaxial cable.
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| CN201721531743.7U CN207379917U (en) | 2017-11-16 | 2017-11-16 | Aero-engine gas component and density monitoring system |
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| CN201721531743.7U CN207379917U (en) | 2017-11-16 | 2017-11-16 | Aero-engine gas component and density monitoring system |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109632664A (en) * | 2018-12-14 | 2019-04-16 | 中国航空工业集团公司北京长城航空测控技术研究所 | It is a kind of for installing the device of optic probe under high temperature and vibration condition |
| CN110501306A (en) * | 2019-09-26 | 2019-11-26 | 哈尔滨工程大学 | A kind of highly sensitive diesel emission NO based on TDLAS technology2Apparatus for measuring concentration |
| CN111323387A (en) * | 2020-03-21 | 2020-06-23 | 哈尔滨工程大学 | Methane number on-line real-time monitoring system |
| CN112461786A (en) * | 2020-09-30 | 2021-03-09 | 北京工业大学 | Aviation oxygen detection method and system based on TDLAS and optical frequency comb |
| CN112964662A (en) * | 2021-02-07 | 2021-06-15 | 中国科学院长春光学精密机械与物理研究所 | Method for measuring concentration and temperature of high-temperature fuel gas of aircraft engine |
| US11513060B2 (en) * | 2018-12-05 | 2022-11-29 | Horiba Stec, Co., Ltd. | Absorption analyzer |
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2017
- 2017-11-16 CN CN201721531743.7U patent/CN207379917U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11513060B2 (en) * | 2018-12-05 | 2022-11-29 | Horiba Stec, Co., Ltd. | Absorption analyzer |
| CN109632664A (en) * | 2018-12-14 | 2019-04-16 | 中国航空工业集团公司北京长城航空测控技术研究所 | It is a kind of for installing the device of optic probe under high temperature and vibration condition |
| CN110501306A (en) * | 2019-09-26 | 2019-11-26 | 哈尔滨工程大学 | A kind of highly sensitive diesel emission NO based on TDLAS technology2Apparatus for measuring concentration |
| CN111323387A (en) * | 2020-03-21 | 2020-06-23 | 哈尔滨工程大学 | Methane number on-line real-time monitoring system |
| US11493438B2 (en) * | 2020-03-21 | 2022-11-08 | Harbin Engineering University | Methane value online real-time monitoring system |
| CN112461786A (en) * | 2020-09-30 | 2021-03-09 | 北京工业大学 | Aviation oxygen detection method and system based on TDLAS and optical frequency comb |
| CN112964662A (en) * | 2021-02-07 | 2021-06-15 | 中国科学院长春光学精密机械与物理研究所 | Method for measuring concentration and temperature of high-temperature fuel gas of aircraft engine |
| CN112964662B (en) * | 2021-02-07 | 2022-07-15 | 中国科学院长春光学精密机械与物理研究所 | Method for measuring concentration and temperature of high-temperature fuel gas of aircraft engine |
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