CN107271053B - A kind of integrated optical circuit device for aero engine turbine blades temperature monitoring - Google Patents
A kind of integrated optical circuit device for aero engine turbine blades temperature monitoring Download PDFInfo
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- CN107271053B CN107271053B CN201710524151.0A CN201710524151A CN107271053B CN 107271053 B CN107271053 B CN 107271053B CN 201710524151 A CN201710524151 A CN 201710524151A CN 107271053 B CN107271053 B CN 107271053B
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- 230000003287 optical effect Effects 0.000 title claims abstract description 73
- 238000012544 monitoring process Methods 0.000 title claims abstract description 11
- 238000012545 processing Methods 0.000 claims abstract description 13
- KPHWPUGNDIVLNH-UHFFFAOYSA-M diclofenac sodium Chemical compound [Na+].[O-]C(=O)CC1=CC=CC=C1NC1=C(Cl)C=CC=C1Cl KPHWPUGNDIVLNH-UHFFFAOYSA-M 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 12
- 230000005540 biological transmission Effects 0.000 claims description 6
- SBIBMFFZSBJNJF-UHFFFAOYSA-N selenium;zinc Chemical compound [Se]=[Zn] SBIBMFFZSBJNJF-UHFFFAOYSA-N 0.000 claims description 6
- 230000013011 mating Effects 0.000 claims description 4
- 229910000530 Gallium indium arsenide Inorganic materials 0.000 claims description 3
- 229910000661 Mercury cadmium telluride Inorganic materials 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 230000017260 vegetative to reproductive phase transition of meristem Effects 0.000 claims description 3
- 239000000567 combustion gas Substances 0.000 abstract description 14
- 230000005855 radiation Effects 0.000 abstract description 11
- 238000010183 spectrum analysis Methods 0.000 abstract description 7
- 238000005259 measurement Methods 0.000 abstract description 6
- 238000010521 absorption reaction Methods 0.000 abstract description 5
- 238000000862 absorption spectrum Methods 0.000 abstract description 2
- 239000011521 glass Substances 0.000 abstract description 2
- 238000009529 body temperature measurement Methods 0.000 description 2
- 239000013307 optical fiber Substances 0.000 description 2
- 230000005457 Black-body radiation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 210000004209 hair Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000005622 photoelectricity Effects 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/10—Radiation pyrometry, e.g. infrared or optical thermometry using electric radiation detectors
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0022—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation of moving bodies
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0088—Radiation pyrometry, e.g. infrared or optical thermometry in turbines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/02—Constructional details
- G01J5/06—Arrangements for eliminating effects of disturbing radiation; Arrangements for compensating changes in sensitivity
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/02—Constructional details
- G01J5/08—Optical arrangements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/58—Radiation pyrometry, e.g. infrared or optical thermometry using absorption; using extinction effect
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0022—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation of moving bodies
- G01J2005/0033—Wheel
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/10—Radiation pyrometry, e.g. infrared or optical thermometry using electric radiation detectors
- G01J2005/103—Absorbing heated plate or film and temperature detector
Abstract
The present invention provides a kind of integrated optical circuit device for aero engine turbine blades temperature monitoring, the integrated optical circuit system, it include three wave band thermometric optical paths, combustion gas spectrum analysis optical path, data acquisition processing system and master controller for measuring the surface temperature of turbo blade.The infra-red radiation that tested blade issues is divided into two parts after this light path system: first part is received by a photoelectric detector after entering three wave band thermometric optical paths, and is analyzed after filter circuit, amplifying circuit processing by data acquisition processing system；Second infra-red radiation enters combustion gas spectrum analysis optical path, analyzes the absorption peak of combustion gas, and by the switching of optical filter wheel in switch controller switching thermometric optical path.The invention of this collection can provide combustion gas spectrum analysis function, and according to the absorption spectrum of analysis combustion gas, wave band used in switching thermometric as needed, it can avoid the absorption peak of combustion gas, reduce measurement error, and it can switch filter glass according to use occasion, single band, two waveband, the function of three wave band thermometrics are provided.
Description
Technical field
The present invention relates to a kind of light path system, specifically a kind of light path system for temperature measurement is more specifically
A kind of aero engine turbine blades surface temperature monitoring light path system.
Background technique
As aero-engine develops to high thrust ratio, high bypass ratio, high turbine inlet temperature (TIT) direction, engine is moved
Force request is increasing.The turbine inlet temperature (TIT) of engine is from 1477 DEG C of hairs of 8.0 level-one of third generation engine thrust-weight ratio
1704 DEG C for opening up 10.0 level-one of forth generation engine thrust-weight ratio.Foreign countries' Turbine Blade Temperature Field measurement product can monitor at present
Turbine Blade Temperature Field be also only capable of reaching 1400 DEG C, the engine temperature detection requirement of high thrust ratio is unable to satisfy, so that aviation
It is more prominent that engine turbine leaf temperature is difficult to the problem of measuring.
Radiation temperature measurement is at present optimal selection in aero engine turbine blades fields of measurement, and occupies important ground
Position.The technology neither jamming target surface nor interferes the surface temperature of surrounding medium at work, for some rotating objects,
High-speed moving object or the strong object of corrosivity.But the optical texture that current radiant thermometric technology uses is single, does not have
Combustion gas spectrum analysis and waveband selection function cannot be completely eliminated high-temperature fuel gas bring measurement error.
Summary of the invention
Present invention mainly solves the technical issues of, exactly propose a kind of for aero engine turbine blades temperature monitoring
Integrated optical circuit system solves light channel structure used in current radiant thermometric technology, has a single function asking of causing measurement error big
Topic.
The above technical problem is solved, one technical scheme adopted by the invention is that: one kind being used for aero-turbine leaf
The integrated optical circuit device of piece temperature monitoring, the device include: data acquisition device, data processing equipment, switch controller, master control
Device processed, the work of the main controller controls data acquisition device, data processing equipment, switch controller；The data acquisition
Device is such as flowering structure: turbo blade radius passes through window (2) first and collimates to form main optical path by collimating mirror；By dividing
A branch is separated in Shu Jingcong main optical path, branch light input light spectrometer after the first focus lamp；Then first is used
Dichronic mirror separates a branch from next main optical path, which passes through the first filter after the focusing of the second focus lamp
Optical filter on mating plate wheel inputs the first detector；Subsequently one is separated from next main optical path using the second dichronic mirror
Branch, the branch light, by the second optical filter wheel upper filter, input the second detector after tertiary focusing mirror；Finally
Main optical path after the 4th focus lamp by the optical filter on third optical filter wheel, input third detector；It is characterized in that
The spectrometer obtains data and is transferred to data processing equipment, and the switch controller controls each suitable filter of optical filter wheel selection
Mating plate.
Further, the collimating mirror and window lens material are ZnSe, and the focal length of collimating mirror is 80mm~100mm,
Diameter is 25.4mm, plates the anti-reflection film of 0.4um~5um wave band；First dichroic mirror wave band is 0.4um~1um visible close red
Outside, transmission band is 1~5um；The reflected waveband of second dichronic mirror is the short-wave infrared of 1um~3um, and transmission band is 3~5um
Medium-wave infrared；The material of second focus lamp is vitreous silica, focal length 50mm, diameter 25.4mm；The material of tertiary focusing mirror
For CaF, focal length 50mm, diameter 25.4mm；The material of 4th focus lamp is ZnSe, focal length 50mm, diameter 25.4mm.
Further, each optical filter wheel includes 5 optical filter bandwidth in 1~3um of short-wave infrared, bandwidth difference
For 1.6um ± 50nm, 1.8um ± 50nm, 2.3um ± 50nm, 2.5um ± 50nm, 3um ± 50nm.
Further, first detector is Si photodetector, and the second detector is InGaAs photodetector, the
Three detectors are HgCdTe photodetector.
The beneficial effects of the present invention are: this integrated optical circuit system provides combustion gas spectrum analysis function, and according to analysis
The absorption spectrum of combustion gas switches wave band used in thermometric as needed, can avoid the absorption peak of combustion gas, reduces measurement error.This
Integrated optical circuit device can switch filter glass, provide single band, two waveband, the function of three wave band thermometrics according to use occasion, from
And reduce the cost of measuring device.
Detailed description of the invention
Fig. 1 is integrated optical circuit system schematic；
In Fig. 1: 1. turbo blades, 2. windows, 3. collimating mirrors, 4. fiber spectrometers, 5. optical fiber, 6. first focus lamps, 7.
Beam splitter, 8. Visible-to-Near InfaRed dichronic mirrors, 9. second focus lamps, 10 first optical filter wheels, 11. second optical filter wheels 2,12.
Three focus lamps, 13. short-wave infrared dichronic mirrors, 14. the 4th focus lamps, 15. switch controllers, 16. data processing systems, 17. is main
Controller；
Specific embodiment
Present invention will be further explained below with reference to the attached drawings and examples.
A kind of integrated optical circuit device for aero engine turbine blades temperature monitoring, the device include: data acquisition
Device, data processing equipment, switch controller, master controller, the main controller controls data acquisition device, data processing dress
It sets, the work of switch controller；The data acquisition device is such as flowering structure: turbo blade radius passes through window first
(2) it collimates to form main optical path by collimating mirror；A branch is separated from main optical path by beam splitter, the branch light is by the
Input light spectrometer after one focus lamp；Then a branch, the branch are separated from next main optical path using the first dichronic mirror
Light, by the optical filter on the first optical filter wheel, inputs the first detector after the focusing of the second focus lamp；Subsequently use
Second dichronic mirror separates a branch from next main optical path, which passes through the second filter after tertiary focusing mirror
Mating plate wheel upper filter inputs the second detector；Last main optical path is after the 4th focus lamp by third optical filter wheel
Optical filter, input third detector；It is characterized in that the spectrometer, which obtains data, is transferred to data processing equipment, it is described to cut
Changer controller controls each optical filter wheel and selects suitable optical filter.The collimating mirror and window lens material are ZnSe, collimation
The focal length of mirror is 80mm~100mm, diameter 25.4mm, plates the anti-reflection film of 0.4um~5um wave band；First dichroic mirror wave
Section is that 0.4um~1um is visible near-infrared, and transmission band is 1~5um；The reflected waveband of second dichronic mirror is the short of 1um~3um
Wave is infrared, and transmission band is 3~5um medium-wave infrared；The material of second focus lamp is vitreous silica, and focal length 50mm, diameter is
25.4mm；The material of tertiary focusing mirror is CaF, focal length 50mm, diameter 25.4mm；The material of 4th focus lamp is ZnSe,
Focal length is 50mm, diameter 25.4mm.First detector is Si photodetector, and the second detector is the spy of InGaAs photoelectricity
Device is surveyed, third detector is HgCdTe photodetector.Each optical filter wheel includes 5 optical filter bandwidth in short-wave infrared
In 1~3um, bandwidth is respectively 1.6um ± 50nm, 1.8um ± 50nm, 2.3um ± 50nm, 2.5um ± 50nm, 3um ± 50nm.
Aero engine turbine blades are placed in in the focus of the collimating mirror of optical path (distance is 80~100mm), optical path is hung down
Straight alignment blade surface, the temperature range of turbo blade are 400~1550 DEG C, release corresponding radiation wave band with blackbody radiation law
For 0.4~5um.The infra-red radiation that turbo blade issues, enters inside integrated optical circuit by optical window.Infra-red radiation passes through first
It crosses collimating mirror and is adjusted to directional light, parallel infra-red radiation is divided into the two parts for waiting energy by beam splitter: first part penetrates
Beam splitter enters three wave band thermometric optical paths, and second part is reflected into combustion gas spectrum analysis optical path by beam splitter.
Two parts optical path is illustrated respectively below:
In three wave band thermometric light path systems, first part's infra-red radiation passes through Visible-to-Near InfaRed dichronic mirror (back wave first
0.4~1um of section, through 1~5um of wave band), by the part infra-red radiation of Visible-to-Near InfaRed dichroic mirror after focus lamp,
It is beaten on corresponding detector photosurface through optical filter, it is seen that-near-infrared radiation is received after optical filter by photodetector,
Photodetector converts optical signals into electric signal.The embodiment of other two wave band is identical with this, and is no longer described in detail.Pass through three
The electric signal that a detector measures can extrapolate target temperature by three wave band algorithms.
In combustion gas spectrum analysis optical path, second part infra-red radiation is by being transferred to spectrometer, light by optical fiber after focus lamp
Spectrometer transfers data to master controller after analyzing the absorption peak of combustion gas, and master controller controls switching control according to combustion gas absorption peak
Device processed selects suitable optical filter.
Claims (4)
1. a kind of integrated optical circuit device for aero engine turbine blades temperature monitoring, which includes: data acquisition dress
It sets, data processing equipment, switch controller, master controller, the main controller controls data acquisition device, data processing dress
It sets, the work of switch controller；The data acquisition device is such as flowering structure: turbo blade radius passes through window first
(2) it collimates to form main optical path by collimating mirror；A branch is separated from main optical path by beam splitter, the branch light is by the
Input light spectrometer after one focus lamp；Then a branch, the branch are separated from next main optical path using the first dichronic mirror
Light, by the optical filter on the first optical filter wheel, inputs the first detector after the focusing of the second focus lamp；Subsequently use
Second dichronic mirror separates a branch from next main optical path, which passes through the second filter after tertiary focusing mirror
Mating plate wheel upper filter inputs the second detector；Last main optical path is after the 4th focus lamp by third optical filter wheel
Optical filter, input third detector；It is characterized in that the spectrometer, which obtains data, is transferred to data processing equipment, it is described to cut
Changer controller controls each optical filter wheel and selects suitable optical filter.
2. a kind of integrated optical circuit device for aero engine turbine blades temperature monitoring as described in claim 1, special
Sign is the collimating mirror and window lens material is ZnSe, and the focal length of collimating mirror is 80mm~100mm, and diameter is
25.4mm plates the anti-reflection film of 0.4um~5um wave band；First dichroic mirror wave band is that 0.4um~1um is visible near-infrared, transmission
Wave band is 1~5um；The reflected waveband of second dichronic mirror is the short-wave infrared of 1um~3um, and transmission band is that 3~5um medium wave is red
Outside；The material of second focus lamp is vitreous silica, focal length 50mm, diameter 25.4mm；The material of tertiary focusing mirror is CaF,
Focal length is 50mm, diameter 25.4mm；The material of 4th focus lamp is ZnSe, focal length 50mm, diameter 25.4mm.
3. a kind of integrated optical circuit device for aero engine turbine blades temperature monitoring as claimed in claim 1 or 2,
Be characterized in that each optical filter wheel includes 5 optical filter bandwidth in 1~3um of short-wave infrared, bandwidth be respectively 1.6um ±
50nm、1.8um±50nm、2.3um±50nm、2.5um±50nm、3um±50nm。
4. a kind of integrated optical circuit device for aero engine turbine blades temperature monitoring as claimed in claim 3, special
Sign is that first detector is Si photodetector, and the second detector is InGaAs photodetector, and third detector is
HgCdTe photodetector.
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| CN201710524151.0A CN107271053B (en) | 2017-06-30 | 2017-06-30 | A kind of integrated optical circuit device for aero engine turbine blades temperature monitoring |
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| CN201710524151.0A CN107271053B (en) | 2017-06-30 | 2017-06-30 | A kind of integrated optical circuit device for aero engine turbine blades temperature monitoring |
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| CN107271053B true CN107271053B (en) | 2019-07-19 |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107271053B (en) * | 2017-06-30 | 2019-07-19 | 电子科技大学 | A kind of integrated optical circuit device for aero engine turbine blades temperature monitoring |
| CN107741275A (en) * | 2017-10-26 | 2018-02-27 | 中国科学院地理科学与资源研究所 | A kind of multi-optical spectrum imaging system |
| CN109060135A (en) * | 2018-06-05 | 2018-12-21 | 哈尔滨工程大学 | A kind of radiation temperature measurement system of turbo blade and turbo blade radiative thermometric method based on reflection compensation |
| CN112212977B (en) * | 2020-09-22 | 2022-02-08 | 北京理工大学 | High-speed high-resolution high-precision ultrahigh-temperature molten pool temperature field online monitoring device and method |
| CN112611566A (en) * | 2020-11-27 | 2021-04-06 | 中国航发四川燃气涡轮研究院 | Online particle detection method and device in high-temperature and high-speed airflow based on spectrum identification |
| CN112964367B (en) * | 2021-02-07 | 2022-02-11 | 中国科学院长春光学精密机械与物理研究所 | Radiation temperature measurement method for turbine blade of aircraft engine |
| CN113310578A (en) * | 2021-05-11 | 2021-08-27 | 电子科技大学 | Six-channel optical device for temperature measurement of turbine blade of aircraft engine |
| CN113358365B (en) * | 2021-05-26 | 2022-11-08 | 电子科技大学 | Aero-engine turbine disk radiation information acquisition probe |
| CN113401360B (en) * | 2021-06-16 | 2023-03-10 | 电子科技大学 | Aero-engine turbine disk temperature measuring device based on multiband optical radiation temperature measurement |
| CN113551779A (en) * | 2021-08-11 | 2021-10-26 | 电子科技大学 | Prism six-channel system for temperature measurement of turbine blade of aircraft engine |
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