CN110657993B - Method for monitoring combustion field of aero-engine based on all-fiber optical frequency comb system - Google Patents
Method for monitoring combustion field of aero-engine based on all-fiber optical frequency comb system Download PDFInfo
- Publication number
- CN110657993B CN110657993B CN201910988885.3A CN201910988885A CN110657993B CN 110657993 B CN110657993 B CN 110657993B CN 201910988885 A CN201910988885 A CN 201910988885A CN 110657993 B CN110657993 B CN 110657993B
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- frequency comb
- optical fiber
- optical frequency
- analysis module
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/05—Testing internal-combustion engines by combined monitoring of two or more different engine parameters
Abstract
The invention provides a method for monitoring an aeroengine combustion field based on an all-fiber optical frequency comb system, which is characterized by comprising the following steps of: the optical frequency comb is divided into two beams after passing through the beam splitter, wherein one beam is connected with the spectral analysis module through an optical fiber, the other beam is connected with the combustion chamber monitoring device through an optical fiber, and the obtained output signal is coupled into the optical fiber and transmitted to the spectral analysis module. The optical frequency comb passes through the gas sample cell to be detected and is used for obtaining an absorption spectrum signal; the combustion chamber monitoring device is arranged at the outlet of the combustion chamber of the aero-engine and is used for obtaining multi-path collected signal light; and the spectrum analysis module performs comparative analysis on the obtained absorption spectrum signal and the optical frequency comb spectrum signal to obtain the change condition of each parameter of the gas component concentration in the combustion chamber of the aircraft engine. The invention has compact structure and simple method, and the all-fiber optical frequency comb system and the combustion chamber monitoring device greatly improve the integratability of the system and can quickly and accurately monitor the combustion field of the aircraft engine.
Description
(I) technical field
The invention relates to the technical field of laser and combustion diagnosis, in particular to the technical field of monitoring of an aeroengine combustion field by an all-fiber optical frequency comb system.
(II) background of the invention
The long-life and high-reliability aircraft engine combustion chamber is the key for developing high-performance aircraft engines. The combustion chamber of an aircraft engine can generate complex reaction during working, and the actual combustion process is difficult to accurately describe by using computational fluid mechanics. The effective combustion diagnosis technology can accurately measure key parameters in the combustion process of the aeroengine, and the structure of the aeroengine is further improved according to data obtained by measurement. In particular, reliable and accurate measurements of key parameters such as temperature, pressure, concentration of combustion components, etc. are needed. The optical diagnosis technology is one of the technologies with faster dynamic response, and the measurement of parameters such as the temperature, the pressure, the component concentration and the like of a combustion chamber can be realized by utilizing the laser absorption spectrum. However, the conventional absorption spectrum measuring device includes a prism, a grating, a fourier transform spectrometer, a single-frequency laser, and the like, and has low spectral resolution, low detection sensitivity, low frequency measurement accuracy and measurement speed, and the instantaneous temperature measurement capability of an unstable combustion field needs to be improved.
Based on the background, the existing method for monitoring the combustion field of the aircraft engine by using laser absorption spectroscopy needs to be further optimized.
Disclosure of the invention
In view of the above, the invention provides a method for monitoring an aircraft engine combustion field based on an all-fiber optical frequency comb system, which has the advantages of simple structure, high resolution, high sensitivity, high measurement speed and high system integratability.
In a first aspect, an embodiment of the present invention provides a method for monitoring an aircraft engine combustion field based on an all-fiber optical frequency comb system, where the method is characterized in that: the optical frequency comb is divided into two beams after passing through the beam splitter, wherein one beam is connected with the spectral analysis module through an optical fiber, the other beam is connected with an optical fiber input port of the combustion chamber monitoring device through an optical fiber, and an output port of the combustion chamber monitoring device is connected with the spectral analysis module; the optical frequency comb is used as signal light and passes through the combustion chamber to obtain an absorption spectrum signal after passing through the combustion chamber; the combustion chamber monitoring device is used for measuring gas at the outlet of the combustion chamber to obtain a plurality of paths of sampling signals; the spectrum analysis module is connected with the output ports of the optical frequency comb and the combustion chamber monitoring device and is used for analyzing the spectrum signals in real time.
With reference to the first aspect, an embodiment of the present invention provides a first possible implementation manner of the first aspect, where the optical frequency comb obtains two optical frequency combs with different optical intensities through one beam splitter; the path with larger light intensity is connected with an optical fiber input port of the combustion chamber detection device and is used for obtaining a plurality of paths of absorption spectrum signals; and the path with smaller light intensity is connected with the spectral analysis module and is used for obtaining the spectral signal of the optical frequency comb.
In combination with the first aspect, embodiments of the present invention provide a second possible implementation manner of the first aspect, wherein the combustor monitoring device is an octahedron device, and includes 8 optical fiber input ports respectively embedded on eight edges of the octahedron, and 64 coupling output ports uniformly distributed on eight faces; the optical fiber input port is connected with an optical fiber of the transmission optical frequency comb; the coupling output port is connected with the spectral analysis module and is used for outputting a spectral signal to be coupled into the optical fiber and transmitted to the spectral analysis module.
With reference to the second possible implementation manner of the first aspect, the present invention provides a third possible implementation manner of the first aspect, wherein the optical fiber input port of the octahedral combustor monitoring apparatus includes an optical fiber collimator and a spectroscope; the optical fiber collimator is used for converting light transmitted in the optical fiber into collimated light; the beam splitter is used to obtain a single fan-shaped laser beam.
With reference to the second possible implementation manner of the first aspect, the example of the present invention provides a fourth possible implementation manner of the first aspect, wherein the coupling output port of the octahedral combustor monitoring apparatus includes a fiber collimator, which is used to couple the signal light into an optical fiber for output.
With reference to the second possible implementation manner of the first aspect, an embodiment of the present invention provides a fifth possible implementation manner of the first aspect, where the number of output ports evenly distributed on the eight faces is not limited to 64.
With reference to the third possible implementation manner of the first aspect, the embodiment of the present invention provides a sixth possible implementation manner of the first aspect, wherein the fiber collimator and the beam splitter in the fiber input port may be replaced with a combination of devices having the same function.
With reference to the first aspect, an embodiment of the present invention provides a seventh possible implementation manner of the first aspect, wherein the intensities of the light signals entering the spectrum analysis module are equal.
With reference to the first aspect, an eighth possible implementation manner of the first aspect is provided in an embodiment of the present invention, wherein the optical-frequency comb may be input from another optical fiber input port of the combustion chamber monitoring apparatus, and an absorption spectrum signal of the multiple optical-frequency combs is obtained and analyzed, so as to be used for omni-directionally monitoring the combustion field of the aircraft engine.
With reference to the first aspect, an embodiment of the present invention provides a ninth possible implementation manner of the first aspect, where the spectrum analysis module obtains real-time changes of temperature, pressure, and component concentration in the combustion chamber of the aircraft engine through a difference between the obtained multiple absorption spectrum signals and the obtained optical frequency comb spectrum signal.
In combination with the first aspect, the present invention provides a tenth possible implementation manner of the first aspect, where the combustion chamber monitoring device is not limited to an octahedron, and other polyhedral monitoring devices may be used.
In combination with the first aspect, the present invention provides an eleventh possible implementation manner of the first aspect, wherein the gas detected in the combustion chamber includes, but is not limited to, water, carbon monoxide, nitric oxide, and nitrogen dioxide.
The embodiment of the invention has the following beneficial effects:
the method for monitoring the combustion field of the aero-engine based on the all-fiber optical frequency comb system provided by the embodiment of the invention is characterized in that one optical frequency comb with stable frequency and phase is used as an input spectrum and is divided into two optical frequency combs with unequal optical intensity by a beam splitter, wherein one path with larger optical intensity is input into a combustion chamber monitoring device through an optical fiber, a plurality of paths of absorption spectrum signals obtained at an output port of the combustion chamber monitoring device are input into a spectrum analysis module, the other path with smaller optical intensity is connected with the spectrum analysis module and is used for obtaining spectrum signals of the optical frequency comb, and the spectrum analysis module compares and analyzes each path of the obtained absorption spectrum signals with the spectrum signals of the optical frequency comb in real time, so that various parameter change conditions of gas component concentration in the combustion chamber of the aero-engine are obtained.
Compared with the prior art, the method for monitoring the combustion field of the aero-engine based on the all-fiber optical frequency comb system, which is simple in structure and high in integratability, is obtained through optical fiber connection.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
(IV) description of the 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, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural diagram of a method for monitoring an aircraft engine combustion field based on an all-fiber optical frequency comb system according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a path acquisition process of a method for detecting an aircraft engine combustion field based on an all-fiber optical frequency comb system according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of an octahedral combustor monitor according to an embodiment of the present invention;
icon:
110-optical frequency comb; 120-a beam splitter; 200-a combustion chamber monitoring device; 210 — input fiber port; 211-fiber collimator; 212-a beam splitter; 220-output port; 221-a fiber collimator; 130-a spectral analysis module; 140-optical fiber.
(V) detailed description of the preferred embodiments
To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides a method for monitoring an aeroengine combustion field based on an all-fiber optical frequency comb system, which is simple in structure and high in integratability, and can realize accurate measurement of the change conditions of temperature, pressure and gas concentration in an aeroengine combustion chamber.
To facilitate understanding of the present embodiment, first, a method for monitoring an aircraft engine combustion field by an all-fiber optical frequency comb system disclosed in the present embodiment is described in detail, referring to a schematic structural diagram of a method for monitoring an aircraft engine combustion field by an all-fiber optical frequency comb system shown in fig. 1, where an optical frequency comb 110 is connected to a beam splitter 120 to obtain two optical signals with different optical intensities, one path with a smaller optical intensity is connected to a spectral analysis module 130, the other path with a larger optical intensity is connected to a combustion chamber monitoring device 200, the combustion chamber monitoring device 200 is configured to obtain multiple collected signals, and a port of the combustion chamber monitoring device outputting the spectral signals is connected to the spectral analysis module 130. The spectrum analysis module analyzes the change condition of each parameter of gas component concentration in the combustion chamber of the aircraft engine according to the difference between the obtained optical frequency comb spectrum signal and the obtained absorption spectrum signal.
In order to facilitate further understanding of the method provided by the above embodiment, an embodiment of the present invention further provides a schematic diagram of a path of collecting process for monitoring an aircraft engine combustion field by an all-fiber optical frequency comb system, and refer to a schematic diagram of a path of collecting process for monitoring an aircraft engine combustion field based on an all-fiber optical frequency comb system shown in fig. 2, where the process includes:
110-optical frequency comb; 210-a combustion chamber monitoring device optical fiber input port; 220-combustor monitoring device output port; 120-a spectral analysis module; 140-optical fiber.
The optical frequency comb 110 with a large light intensity is connected to an optical fiber input port 210 of the combustion chamber monitoring apparatus through an optical fiber 140, the optical fiber input port 210 is used for obtaining a laser beam with a fan-shaped distribution, and the laser beam is symmetrically projected onto a surface opposite to the input end, wherein a path of spectral signal is transmitted to the spectral analysis module 130 through the optical fiber 140 after being output from a coupling output port 220 of the combustion chamber monitoring apparatus, so as to perform real-time spectral analysis.
Further, the optical-frequency comb 110 can simultaneously obtain multiple spectral signals, for example, 16 signals, by using the fan-shaped laser beam formed by one optical fiber input port 210. And analyzing the change condition of each parameter of the gas component concentration in the combustion chamber of the aircraft engine according to the obtained 16 paths of absorption spectrum signals and optical frequency comb spectrum signals.
Furthermore, the omnibearing absorption spectrum signals in the combustion chamber of the aero-engine can be obtained by changing the optical fiber input port of the optical frequency comb, and further, the combustion field of the aero-engine can be analyzed in an omnibearing manner through the difference between the collected multipath absorption spectrum signals and the optical frequency comb spectrum signals.
It can be understood that the combustion field monitoring method of the aircraft engine is of an all-fiber structure.
In order to facilitate understanding of the combustor monitoring device provided in the above embodiments, an embodiment of the present invention further provides a schematic diagram of an octahedral combustor detection device, referring to a schematic structural diagram of an octahedral combustor monitoring device shown in fig. 3, where the octahedral combustor monitoring device includes:
210-fiber input port; 211-fiber collimator; 212-a beam splitter; 220-output port; 221-fiber collimator.
The optical fiber collimator 211 of the optical fiber input port 210 is used for converting light transmitted in the optical fiber into collimated light to enter the combustion chamber monitoring device, the beam splitter 212 is used for obtaining a single fan-shaped laser beam, and the optical fiber collimator 221 of the output port 220 is used for coupling a spectral signal into the optical fiber for output.
Further, the collected signals obtained by the combustion chamber detecting device are not limited to 16 paths, and the beam splitter 212 and the beam splitter 120 can be adjusted to obtain different numbers of collected signals and keep the light intensity of each light beam input into the spectrum analysis module equal.
In summary, the method for monitoring the combustion field of the aircraft engine based on the all-fiber optical frequency comb system provided by the embodiment of the invention is used for the optical frequency comb, the combustion chamber monitoring device and the spectrum analysis module, and the monitoring of the combustion field of the aircraft engine is skillfully realized in the all-fiber system. The optical frequency comb measurement technology can improve the measurement precision of the absorption spectrum, and the all-fiber structure improves the integratability of the monitoring system.
It can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working process of the method for monitoring the combustion field of the aircraft engine by using the all-fiber optical frequency comb system described above may refer to the corresponding device in the foregoing embodiment, and will not be described herein again.
In addition, in the description of the embodiments of the present invention, 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; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present patent can be understood in a specific case by those skilled in the art.
In the description of the present patent, it is to be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of describing the present patent and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present patent. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present invention, which are used for illustrating the technical solutions of the present invention and not for limiting the same, and the protection scope of the present invention is not limited thereto, although the present invention is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: any person skilled in the art can modify or easily conceive the technical solutions described in the foregoing embodiments or equivalent substitutes for some technical features within the technical scope of the present disclosure; such modifications, changes or substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the present invention. Therefore, the protection scope of the present patent shall be subject to the protection scope of the claims.
Claims (6)
1. A method for monitoring an aircraft engine combustion field based on an all-fiber optical frequency comb system is characterized by comprising the following steps: the optical frequency comb is divided into two beams of optical signals with different light intensities after passing through the beam splitter, wherein one path with smaller light intensity is connected with the spectral analysis module through an optical fiber and is used for obtaining the optical frequency comb spectral signals, the other path with larger light intensity is connected with an optical fiber input port of the combustion chamber monitoring device through the optical fiber, and the combustion chamber monitoring device is used for measuring gas at the outlet of the combustion chamber and obtaining a plurality of paths of absorption spectral signals; the output port of the combustion chamber monitoring device is connected with the spectral analysis module; the spectrum analysis module is used for analyzing the spectrum signal in real time and analyzing the change condition of the gas component concentration in the combustion chamber of the aircraft engine according to the difference between the obtained optical frequency comb spectrum signal and the obtained absorption spectrum signal; the combustion chamber monitoring device is an octahedral combustion chamber monitoring device and comprises 8 optical fiber input ports which are respectively embedded on eight edges of an octahedron and 64 coupling output ports which are uniformly distributed on eight surfaces; the optical fiber input port is connected with an optical fiber of the transmission optical frequency comb; the coupling output port is connected with the spectral analysis module and used for coupling the output spectral signal into the optical fiber and transmitting the output spectral signal to the spectral analysis module.
2. The method of claim 1, wherein the fiber optic input port of the octahedral combustor monitoring device comprises a fiber optic collimator and a spectroscope; the optical fiber collimator is used for converting light transmitted in the optical fiber into collimated light; the beam splitter is used to obtain a single fan-shaped laser beam.
3. The method of claim 1, wherein the coupling output port of the octahedral combustor monitor device comprises a fiber collimator for coupling the signal light into an optical fiber.
4. The method of claim 1, wherein the light signals entering the spectral analysis module are of equal intensity.
5. The method as claimed in claim 1, wherein the spectral analysis module comprises a high-resolution spectrometer, and real-time changes of temperature, pressure and component concentration in the combustion chamber of the aircraft engine are obtained through the difference between the obtained multi-path absorption spectrum signal and the optical frequency comb spectrum signal.
6. The method of claim 1, wherein the composition of the combustor exit gas comprises water, carbon monoxide, nitric oxide, and nitrogen dioxide.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910988885.3A CN110657993B (en) | 2019-10-17 | 2019-10-17 | Method for monitoring combustion field of aero-engine based on all-fiber optical frequency comb system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910988885.3A CN110657993B (en) | 2019-10-17 | 2019-10-17 | Method for monitoring combustion field of aero-engine based on all-fiber optical frequency comb system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110657993A CN110657993A (en) | 2020-01-07 |
| CN110657993B true CN110657993B (en) | 2021-02-02 |
Family
ID=69041116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910988885.3A Active CN110657993B (en) | 2019-10-17 | 2019-10-17 | Method for monitoring combustion field of aero-engine based on all-fiber optical frequency comb system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110657993B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111795829A (en) * | 2020-07-07 | 2020-10-20 | 西安热工研究院有限公司 | TDLAS technology-based gas turbine combustion state parameter monitoring system |
| CN112413642B (en) * | 2020-11-09 | 2022-02-15 | 中国人民解放军空军工程大学 | Intelligent combustion chamber of aero-engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6741629B1 (en) * | 2000-09-22 | 2004-05-25 | Blueleaf, Inc. | Optical transmitter having optically pumped vertical external cavity surface emitting laser |
| CN101331391A (en) * | 2005-12-16 | 2008-12-24 | 丰田自动车株式会社 | Method for analyzing exhaust gas and apparatus for analyzing exhaust gas |
| CN103411923A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Normalized noise reduction method adopting two-path tunable laser absorption spectrum technology |
| CN108645623A (en) * | 2018-05-11 | 2018-10-12 | 中国人民解放军战略支援部队航天工程大学 | Engine chamber efficiency of combustion measuring device and its measurement method |
| CN106802288B (en) * | 2017-03-22 | 2019-06-04 | 河北大学 | Gas-detecting device and method based on tunable laser and super continuous spectrums laser |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103337777A (en) * | 2013-06-24 | 2013-10-02 | 上海理工大学 | Light source device for measuring concentration of nitrogen oxide |
| CN103592260B (en) * | 2013-11-06 | 2016-11-16 | 郑州光力科技股份有限公司 | A kind of on-line monitoring system of transformer oil |
| US9557625B2 (en) * | 2014-05-20 | 2017-01-31 | The United States Of America, As Represented By The Secretary Of Commerce | Fiber frequency comb article |
| CN206146554U (en) * | 2016-11-09 | 2017-05-03 | 哈尔滨理工大学 | Gas temperature detection device based on but tuning diode laser absorption spectrum |
| CN107576505B (en) * | 2017-10-16 | 2019-06-04 | 上海交通大学 | Mid-infrared laser measuring system and method for engine combustion process monitoring |
| CN109357763B (en) * | 2018-09-27 | 2020-08-07 | 中国科学院上海技术物理研究所 | Atmospheric absorption spectrum measurement system and method based on time-resolved optical frequency comb |
-
2019
- 2019-10-17 CN CN201910988885.3A patent/CN110657993B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6741629B1 (en) * | 2000-09-22 | 2004-05-25 | Blueleaf, Inc. | Optical transmitter having optically pumped vertical external cavity surface emitting laser |
| CN101331391A (en) * | 2005-12-16 | 2008-12-24 | 丰田自动车株式会社 | Method for analyzing exhaust gas and apparatus for analyzing exhaust gas |
| CN103411923A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Normalized noise reduction method adopting two-path tunable laser absorption spectrum technology |
| CN106802288B (en) * | 2017-03-22 | 2019-06-04 | 河北大学 | Gas-detecting device and method based on tunable laser and super continuous spectrums laser |
| CN108645623A (en) * | 2018-05-11 | 2018-10-12 | 中国人民解放军战略支援部队航天工程大学 | Engine chamber efficiency of combustion measuring device and its measurement method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110657993A (en) | 2020-01-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11644415B2 (en) | System for measuring gas temperature and component concentrations in combustion field based on optical comb | |
| US4081215A (en) | Stable two-channel, single-filter spectrometer | |
| CN110657992B (en) | Method for monitoring combustion field of aero-engine by space access type double-optical comb system | |
| CN100395538C (en) | Novel quick-speed elliptical polarized light measurement system | |
| US4818705A (en) | Method and apparatus for analyzing the composition of the exhaust gas of any internal combustion engine | |
| CN110657993B (en) | Method for monitoring combustion field of aero-engine based on all-fiber optical frequency comb system | |
| WO2010002326A1 (en) | Arrangement adapted for spectral analysis | |
| CN101819140A (en) | Continuous monitoring device and method of gaseous elemental mercury concentration | |
| CN110736623B (en) | Method for monitoring combustion field of aircraft engine based on double-optical-comb all-fiber system | |
| CN104833816A (en) | Laser doppler velocity measurement device based on rotating grating and velocity measurement method of laser doppler velocity measurement device | |
| CN113376111A (en) | Method for detecting concentration of marker respiratory gas by cavity ring-down double-comb spectrum | |
| CN106841065A (en) | Ultraviolet-visible near-infrared transflector spectral measurement device and measuring method | |
| CN110657994B (en) | Method for monitoring combustion field of aero-engine by spatial access type optical frequency comb system | |
| Gang et al. | Integrated differential area method for variable sensitivity interrogation of tilted fiber Bragg grating sensors | |
| US6353476B1 (en) | Apparatus and method for substantially simultaneous measurement of emissions | |
| CN110031426A (en) | A kind of the escaping of ammonia analyzer and analysis method based on multi beam light source off-axis integrated chamber output spectrum technology | |
| CN109087719A (en) | Main steam line leakage monitoring system in a kind of containment | |
| CN202421062U (en) | Ultraviolet analyzer for measuring sulfur dioxide and nitrogen oxides | |
| US3994592A (en) | Method of determining the concentration ratio of two substances | |
| CN204575674U (en) | Based on the laser Doppler speed measuring device of rotating grating | |
| Tedder et al. | Characterization of a combined CARS and interferometric Rayleigh scattering system | |
| CN111956233B (en) | Blood glucose measuring device and blood glucose measuring method | |
| RU10462U1 (en) | LASER GAS ANALYZER | |
| RU84986U1 (en) | DEVICE FOR SIMULTANEOUS DETERMINATION OF THE CONCENTRATION OF CO AND CO2 MOLECULES IN A GAS-MEDIUM | |
| JPS6367521A (en) | Device and method of measuring displacement |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |