CN110231093B - Infrared radiation thermometer capable of reducing background radiation - Google Patents
Infrared radiation thermometer capable of reducing background radiation Download PDFInfo
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- CN110231093B CN110231093B CN201910588599.8A CN201910588599A CN110231093B CN 110231093 B CN110231093 B CN 110231093B CN 201910588599 A CN201910588599 A CN 201910588599A CN 110231093 B CN110231093 B CN 110231093B
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- polished rod
- radiation
- probe
- infrared radiation
- light
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- 230000005855 radiation Effects 0.000 title claims abstract description 72
- 239000000523 sample Substances 0.000 claims abstract description 46
- 238000007789 sealing Methods 0.000 claims description 11
- 230000003287 optical effect Effects 0.000 claims description 9
- 238000005096 rolling process Methods 0.000 claims description 9
- 238000004378 air conditioning Methods 0.000 claims description 7
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 6
- 229910052759 nickel Inorganic materials 0.000 claims description 3
- 238000007664 blowing Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 claims 1
- 229910000601 superalloy Inorganic materials 0.000 claims 1
- 238000009529 body temperature measurement Methods 0.000 abstract description 13
- 238000005259 measurement Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 abstract description 6
- 238000002485 combustion reaction Methods 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 14
- 239000000446 fuel Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 239000000956 alloy Substances 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 230000004907 flux Effects 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000007517 polishing process Methods 0.000 description 1
- 238000010926 purge Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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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
- G01J5/0022—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
- G01J5/0022—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation of moving bodies
- G01J2005/0033—Wheel
Abstract
The invention discloses an infrared radiation thermometer capable of reducing background radiation, belongs to the technical field of radiation thermometers, and is applied to temperature measurement of the surface of a turbine blade of an aircraft engine. The invention overcomes the influence of the radiation background radiation temperature measurement in the radiation temperature measurement process, realizes the reciprocating rotation of the probe in the thermometer by 90 degrees by utilizing the rotary cylinder, realizes the measurement of the background radiation energy in the combustion chamber by the thermometer, and reduces the influence of the radiation background radiation temperature measurement in the turbine blade temperature measurement. The radiometer has the advantages that the radiometer can well reduce the radiometric error generated by the background of the radiometer, is suitable for measuring the temperature of the turbine blade working under the high-temperature condition, and is also suitable for measuring the temperature of other irregularly moving objects under the high-temperature environment.
Description
Technical Field
The invention belongs to the technical field of radiation thermometers, and is applied to the surface temperature measurement of turbine blades of aero-engines.
Background
Patent application No. 201710464605X discloses a device for collecting light from the surface of a turbine blade, which comprises: the device comprises a probe sleeve, a coated reflecting mirror, a lens swinging control shaft and a motion control servo motor; the coated reflector comprises a lens and a mirror frame, the lens swinging control shaft comprises 3 control rods, one ends of the 3 control rods are movably connected to the mirror frame respectively, and the other ends of the 3 control rods are connected with a motion control servo motor; the coated reflector and the lens swinging control shaft are positioned in the probe sleeve, and a light through hole is formed in the position of the coated reflector corresponding to the probe sleeve; the probe sleeve comprises an inner wall and an outer wall, a gas cooling cavity is arranged between the inner wall and the outer wall, a gas inlet of the gas cooling cavity is arranged on the outer layer of the probe sleeve, and a gas outlet is arranged at a light through hole of the probe sleeve; an air inlet used for introducing cold gas into the light-passing cavity of the probe sleeve is additionally arranged on the probe sleeve, and the air outlet is a light-passing hole of the probe sleeve.
The device adopts bilayer structure, and it should not too high to add to sweep the inside temperature of cold wind maintenance probe, wherein also can reflect the infrared radiation of the inside radiation of probe on the speculum of reflection turbine blade radiation, the precision that can further reduce infrared radiation and measure.
Disclosure of Invention
The invention aims to overcome the influence of the radiation thermometer on measuring background in the radiation temperature measuring process, and provides a radiation thermometer for eliminating the influence of the measuring background based on a self-rotating mode. The reciprocating rotation of the probe in the thermometer by 90 degrees is realized by utilizing the rotary cylinder, the measurement of background radiant energy in the combustion chamber of the thermometer is realized, and the influence of radiation background radiation temperature measurement in the temperature measurement of the turbine blade is reduced.
In order to achieve the above object, the present invention firstly measures the radiation amount inside the turbine, then measures the radiation amount inside the thermometer, and finally calculates the temperature inside the turbine, so the technical scheme of the present invention is an infrared radiation thermometer for reducing background radiation, which comprises: the probe comprises a probe body, a probe shell, a rolling bearing, a rotary cylinder and a T-shaped tail pipe; the probe body comprises a reflector, a first-stage polished rod and a second-stage polished rod, the first-stage polished rod and the second-stage polished rod are of hollow tubular structures, the diameter of the first-stage polished rod is smaller than that of the second-stage polished rod, a support extends out of the tail end of the first-stage polished rod to fix the reflector, radiation reflected by the reflector sequentially passes through inner cavities of the first-stage polished rod and the second-stage polished rod, and the probe body is arranged inside a probe shell; the head section of the probe shell is provided with a cold air interface for blowing cold air into the probe shell; the tail end of the turbine is provided with a light-transmitting window for the reflector to receive the infrared radiation inside the turbine; the rolling bearing is arranged at the head end of the probe shell, the outer ring of the rolling bearing is connected with the probe shell in a sealing way, and the inner ring of the rolling bearing is connected with the second-stage polished rod in a sealing way; the tail end of the first-stage polished rod is provided with a window sheet in a sealing manner, and a condenser lens, an anti-dazzle diaphragm, a field diaphragm and a collimating lens are sequentially arranged in the second-stage polished rod from the incident end of radiation light; the slewing cylinder includes: the gas interface comprises an input port and an output port which are respectively arranged at two ends of the cylinder wall and drive the rotary mounting ring to rotate through gas flow; one end of the rotary cylinder is connected with the head end of the probe shell, the head end of the secondary polished rod is connected with the tail end of the rotary mounting tube of the rotary cylinder in a sealing mode, the other end of the rotary cylinder is connected with a T-shaped tail tube, an optical filter and a focusing mirror are contained in the T-shaped tail tube, and finally the T-shaped tail tube outputs radiation light to be input into the PD detector.
Furthermore, the infrared radiation thermometer also comprises a cold air interface device which is sleeve-shaped and directly sleeved outside the probe shell; the head end of the air conditioning interface device is provided with a bearing end cover, the middle part of the air conditioning interface device is provided with a raised air inlet, the tail section of the air conditioning interface device is provided with a flange plate, and the flange plate is provided with a positioning pin for accurately installing the infrared radiation thermometer on the wall of the turbine.
Furthermore, still be provided with circumference calibrated scale, angle adjusting screw on the revolving cylinder, the circumference calibrated scale is used for observing the rotation angle of rotatory installation pipe, and angle adjusting screw is used for adjusting the initial angle of rotatory installation pipe.
Furthermore, the reflector is made of nickel-based high-temperature alloy, and the surface of the reflector is polished.
Furthermore, the head end of the second-stage polished rod is connected with the tail end of the rotary mounting pipe of the rotary cylinder in a sealing mode through a mounting flange.
Further, the T-type tail pipe includes: the detector comprises a detector interface, a fastening plate and a light through pipe, wherein one end of the light through pipe is vertically arranged on the fastening plate, the other end of the light through pipe is connected with the detector interface, and the T-shaped tail pipe is fixedly connected with the rotary cylinder through the fastening plate; the radiation light is emitted from the second-stage polished rod, passes through the rotary mounting tube of the rotary cylinder and the light-passing tube of the T-shaped tail tube once, and is finally input into the detector through the detector interface.
The invention has the beneficial effects that:
in the process of measuring the temperature of the surface of the turbine blade of the aeroengine, the temperature of the outer wall of a part of temperature detector in the combustion chamber can be rapidly increased under the influence of high-temperature gas, and radiation light is generated to influence the final measurement result. The radiation thermometer disclosed by the invention can well reduce radiation errors generated by the background of the radiation thermometer, is suitable for temperature measurement of turbine blades working under a high-temperature condition, and is also suitable for temperature measurement of other irregularly moving objects under a high-temperature environment.
Drawings
FIG. 1 is a schematic view of the radiation thermometer installation position of the present invention;
FIG. 2 is a schematic view of a radiation thermometer structure and cold air purging in accordance with the present invention;
fig. 3 shows the interface of the T-type tail pipe and the optical fiber detector.
In the figure: 1. the fuel injection device comprises a main shaft, 2 turbine blades, 3 radiation thermometers, 4 combustion chambers, 5 fuel nozzles, 6 high-pressure compressors, 7 detector interfaces, 8T-shaped tail pipes, 9 rotary cylinders, 10 rolling bearings, 11 cold air interfaces, 12 flange plates, 13 probe shells, 14 positioning pins, 15 secondary polished rods, 16 primary polished rods, 17 windowing, 18 reflectors, 19 cold air, 20 light through pipes and 21 fastening plates.
Detailed Description
As shown in FIG. 1, a radiation thermometer for measuring the temperature of the turbine blades is installed on the surface of a casing and is arranged between two stages of turbine blades. The gas completes the supercharging process through the guide vane at the front end of the engine and the high-pressure compressor 6, the high-pressure gas is mixed with the fuel sprayed by the fuel nozzle 5 to form high-temperature and high-pressure gas, the gas flow generates acting force when flowing through the turbine, and the turbine blade 2 is acted to rotate, so that the energy of the gas flow can be converted into mechanical energy to be output, and the working environment of the turbine blade 2 is extremely severe. The radiation thermometer 3 extends the probe part into the combustion chamber through a casing preset window, the radiation flux emitted by the turbine blade 2 enters the inside of the thermometer through the window 17, and an optical system in the radiation thermometer completes measurement, collection and transmission of optical signals and finally reaches a main control chamber to complete signal processing.
As shown in fig. 2, the radiation thermometer is a structure of three layers, the bottom layer is a polished rod structure, the first polished rod 16 is a strip, and an optical through hole is formed inside the polished rod structure, so as to ensure effective transmission of optical energy; the bottom of the polish rod is fixed with a reflecting mirror 18 made of nickel-based alloy through polishing, and the included angle between the reflecting mirror 18 and the plane is 45 degrees. Compared with the direct radiation receiving capacity, the reflector is more convenient for the temperature detector to measure the blade body part of the turbine blade, the particularity of the installation position of the radiometer is realized, the roughness of the working surface of the reflector 18 is reduced through the alloy grinding and polishing process, and the energy loss caused by the reflection of the surface of the reflector is reduced to the maximum extent. The second-stage polished rod 15 is cylindrical with a through hole, and a condenser lens, an anti-dazzle diaphragm, a field diaphragm and a collimating lens are sequentially arranged inside the second-stage polished rod; the condenser lens can effectively condense infrared light; the anti-dazzle diaphragm can effectively prevent stray light from entering the optical system; the field diaphragm directly determines the field size of the object to be measured and improves the uniformity of the obtained infrared light; the collimating lens performs divergence angle compression on the diverged infrared light to enable the diverged infrared light to achieve parallel light transmission. The top end of the second-stage polished rod 15 is provided with a flange plate with a hole, and the flange plate is connected with the rotary cylinder 9 through a bolt. In view of the three considerations of polish rod rigidity, sealing performance and cost, the secondary polish rod 15 is connected with the primary polish rod 16 by welding. The second layer structure is probe shell 13, wholly is the drum cascaded, and there is oval windowing 17 just opposite bottom reflector 18, windowing 17 length 4mm, and too big window can lead to the gas volume that gets into the probe to increase, and the indirect increase is used for refrigerated air conditioning volume, raise the cost. The radiation flux of the turbine blade enters the interior of the temperature detector through the window 17, the temperature of the probe shell 13 and the reflector 18 can be rapidly raised under the influence of fuel gas, and if corresponding cooling measures are not taken, a large amount of radiation energy can be generated, and the temperature measurement precision is seriously influenced. The outmost layer is a cold air interface device, and the bottom is a mounting flange 12 used for mounting the temperature detector and the surface of the casing. The middle of the probe is provided with a cold air interface 11, the cold air interface is a through hole corresponding to the round surface of the probe shell, so that cold air can conveniently enter the interior of the temperature detector, as shown in figure 2, the cold air enters the interior of the probe through the interface and reaches the reflector 18 and the probe window 17 to form forced convection with fuel gas, and in the temperature measurement process, the reflector 18 can be completely wrapped by appropriate cold air flow, the surface temperature of the reflector 18 is reduced, the optical lens can be swept through the through hole, and the pollution of the fuel gas to the lens is effectively prevented. The rotary cylinder 9 is divided into a stator part and a rotor part, the rotor part is connected with a flange plate of the secondary light pipe to realize the rotation of the polish rod, and a through hole is still arranged at the center of the rotary cylinder to be used as an optical channel. The T-shaped tail pipe 8 is internally provided with a condenser lens, a field diaphragm and a collimating lens, and further collimates infrared light entering the center of the cylinder. And finally, the PD detector 7 completes the standard conversion of the photoelectric signals and establishes the relation between the voltage and the temperature. After the signals of the turbine blades are rapidly collected, the second-stage polished rod 15 and the first-stage polished rod 16 are rotated by 90 degrees under the action of the rotary cylinder 9, the bottom side face of the first-stage polished rod faces the windowing, the windowing is shielded, the measurement of the background radiation flux of the temperature detector is completed, and the radiation measurement error caused by the background of the temperature detector in the temperature measurement process is eliminated through the measurement of radiation energy twice.
Claims (6)
1. An infrared radiation thermometer that reduces background radiation, the infrared radiation thermometer comprising: the probe comprises a probe body, a probe shell, a rolling bearing, a rotary cylinder and a T-shaped tail pipe; the probe body comprises a reflector, a first-stage polished rod and a second-stage polished rod, the first-stage polished rod and the second-stage polished rod are of hollow tubular structures, the diameter of the first-stage polished rod is smaller than that of the second-stage polished rod, a support extends out of the tail end of the first-stage polished rod to fix the reflector, radiation reflected by the reflector sequentially passes through inner cavities of the first-stage polished rod and the second-stage polished rod, and the probe body is arranged inside a probe shell; the head end of the probe shell is provided with a cold air interface for blowing cold air into the probe shell; the tail end of the turbine is provided with a light-transmitting window for the reflector to receive the infrared radiation inside the turbine; the rolling bearing is arranged at the head end of the probe shell, the outer ring of the rolling bearing is connected with the probe shell in a sealing way, and the inner ring of the rolling bearing is connected with the second-stage polished rod in a sealing way; the tail end of the first-stage polished rod is provided with a window sheet in a sealing manner, and a condenser lens, an anti-dazzle diaphragm, a field diaphragm and a collimating lens are sequentially arranged in the second-stage polished rod from the incident end of radiation light; the slewing cylinder includes: the gas interface comprises an input port and an output port which are respectively arranged at two ends of the cylinder wall and drive the rotary mounting ring to rotate through gas flow; one end of the rotary cylinder is connected with the head end of the probe shell, the head end of the secondary polished rod is connected with the tail end of the rotary mounting tube of the rotary cylinder in a sealing mode, the other end of the rotary cylinder is connected with a T-shaped tail tube, an optical filter and a focusing mirror are contained in the T-shaped tail tube, and finally the T-shaped tail tube outputs radiation light to be input into the PD detector.
2. The reduced background radiation infrared radiation thermometer of claim 1 wherein said infrared radiation thermometer further comprises a cold air interface means, said cold air interface means being sleeve-like and directly received by said probe housing; the head end of the air conditioning interface device is provided with a bearing end cover, the middle part of the air conditioning interface device is provided with a raised air inlet, the tail end of the air conditioning interface device is provided with a flange plate, and the flange plate is provided with a positioning pin for accurately installing the infrared radiation thermometer on the wall of the turbine.
3. The infrared radiation thermometer for reducing background radiation as set forth in claim 1, wherein said rotary cylinder is further provided with a circumferential scale for observing a rotation angle of said rotary mounting tube, and an angle adjusting screw for adjusting an initial angle of said rotary mounting tube.
4. The infrared radiation thermometer with reduced background radiation as recited in claim 1, wherein said reflector material is a nickel-based superalloy with a polished surface.
5. The infrared radiation thermometer with reduced background radiation of claim 1 wherein the head end of said secondary polish rod is sealingly connected to the tail end of the rotating mounting tube of the rotary cylinder by a mounting flange.
6. The infrared radiation thermometer with reduced background radiation of claim 1 wherein said T-shaped tailpipe includes: the detector comprises a detector interface, a fastening plate and a light through pipe, wherein one end of the light through pipe is vertically arranged on the fastening plate and is in sealing connection with the fastening plate, the other end of the light through pipe is connected with the detector interface, and the T-shaped tail pipe is fixedly connected with the rotary cylinder through the fastening plate; the radiation light is emitted from the second-stage polished rod, passes through the rotary mounting tube of the rotary cylinder and the light-passing tube of the T-shaped tail tube once, and is finally input into the detector through the detector interface.
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| CN201910588599.8A CN110231093B (en) | 2019-07-02 | 2019-07-02 | Infrared radiation thermometer capable of reducing background radiation |
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| CN201910588599.8A CN110231093B (en) | 2019-07-02 | 2019-07-02 | Infrared radiation thermometer capable of reducing background radiation |
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| CN111486966B (en) * | 2020-05-07 | 2022-12-09 | 江苏日颖慧眼智能设备有限公司 | Diaphragm assembly and infrared sensor temperature measuring device |
| CN112113666B (en) * | 2020-08-31 | 2022-06-03 | 哈尔滨工程大学 | Multispectral temperature measuring device based on self-adaptive emissivity model and temperature measuring method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2109472A (en) * | 1981-11-04 | 1983-06-02 | Rolls Royce | Pyrometer for gas turbine |
| GB2358059A (en) * | 2000-01-07 | 2001-07-11 | Rotadata Ltd | Pyrometric determination of radiance and/ or temperature |
| CN104964748A (en) * | 2015-06-15 | 2015-10-07 | 中国航空工业集团公司上海航空测控技术研究所 | Infrared wavelength acquisition apparatus |
| CN105452932A (en) * | 2013-08-15 | 2016-03-30 | 西门子能源公司 | Methods regarding optical probe having an inner tube with separable tube sections to house optical elements |
| CN106644093A (en) * | 2017-01-09 | 2017-05-10 | 电子科技大学 | Method for measuring surface temperature of turbine blades based on biaxial adjustment |
-
2019
- 2019-07-02 CN CN201910588599.8A patent/CN110231093B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2109472A (en) * | 1981-11-04 | 1983-06-02 | Rolls Royce | Pyrometer for gas turbine |
| GB2358059A (en) * | 2000-01-07 | 2001-07-11 | Rotadata Ltd | Pyrometric determination of radiance and/ or temperature |
| CN105452932A (en) * | 2013-08-15 | 2016-03-30 | 西门子能源公司 | Methods regarding optical probe having an inner tube with separable tube sections to house optical elements |
| CN104964748A (en) * | 2015-06-15 | 2015-10-07 | 中国航空工业集团公司上海航空测控技术研究所 | Infrared wavelength acquisition apparatus |
| CN106644093A (en) * | 2017-01-09 | 2017-05-10 | 电子科技大学 | Method for measuring surface temperature of turbine blades based on biaxial adjustment |
Non-Patent Citations (1)
| Title |
|---|
| 航空发动机内壁高温测试技术;邓进军等;《微纳电子技术》;20150331;第52卷(第3期);第178-183页 * |
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