CN206905939U - A kind of thermocouple dynamic response characteristic experimental rig based on laser - Google Patents
A kind of thermocouple dynamic response characteristic experimental rig based on laser Download PDFInfo
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- CN206905939U CN206905939U CN201720547686.5U CN201720547686U CN206905939U CN 206905939 U CN206905939 U CN 206905939U CN 201720547686 U CN201720547686 U CN 201720547686U CN 206905939 U CN206905939 U CN 206905939U
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- thermocouple
- laser
- response characteristic
- experimental rig
- dynamic response
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Abstract
The utility model discloses a kind of thermocouple dynamic response characteristic experimental rig based on laser, including thermocouple, the calibration wind tunnel being blown to thermocouple, the source of the gas for calibration wind tunnel air feed；Also include being used for the laser heating system for thermocouple heating, the displacement mechanism for adjusting thermocouple locus and whole device is controlled and the control system of data acquisition.Experimental provision with said structure realizes the method that normal temperature wind-tunnel adds laser heating technique to carry out dynamic calibration to thermocouple, and cost is low, is easy to build, and test efficiency is high；Step temperature range is big, and the step delay time is short, accurate less than 0.1ms, result of the test.
Description
Technical field
It the utility model is related to a kind of thermocouple dynamic response characteristic that is used for test and study, i.e., dynamic response characteristic characterizes
Parameter --- the device of-thermal responsive time constant measurement.
Background technology
The pilot system both at home and abroad for thermocouple dynamic response characteristic is generally all that traditional hot air wind tunnel adds cold air at present
Cooling device, positive temperature jump, such as 624 low profile thermal wind-tunnel, 304 large-scale hot air wind tunnels of institute etc. are formed, low profile thermal wind-tunnel is
Heated using electric-heating technology stream field, supplied using mini air compressor, utilize solenoid valve control nitrogen gas
Road cools down to thermo wires contact, and its wind tunnel spout is small, flowing field stability is poor, step temperature range is small, step delay time length；
The 304 large-scale hot air wind tunnels of institute are heated by wind-tunnel to thermocouple, and ladle cover mechanism controls cold air is cooled down, and equipment construction takes
With costliness, the reason such as step delay time length causes high/low temperature interface to obscure.In Scientific Research in University Laboratory, also have and utilize other heating
Method, negative temperature jump is formed, measure thermocouple time constant, its flowing field stability is poor, laboratory equipment is relatively simple and crude, knot
Fruit is less desirable, and engineer applied is difficult.
Utility model content
In view of this, the utility model provides the thermocouple dynamic response characteristic experimental rig based on laser, is applied to
Aero-engine or parts testpieces stagnation temperature inlet airflow distortion test, the thermal response spy of high speed transient temperature field test thermocouple
Property demarcation；(between compressor stage, combustion chamber hugging, between stage of turbine) dynamic temperature field test is can also be used between engine level to use
The thermal response characteristics demarcation of thermocouple, and possess certain measuring accuracy, obtain engineer applied.
To solve above technical problem, the technical solution of the utility model is：A kind of thermocouple dynamic based on laser
Response characteristic experimental rig, including thermocouple, the calibration wind tunnel being blown to thermocouple, the source of the gas for calibration wind tunnel air feed；
Also include being used for the laser heating system for thermocouple heating, the displacement mechanism for adjusting thermocouple locus and to whole
Individual device is controlled the control system with data acquisition.
As an improvement the calibration wind tunnel is small-sized normal temperature wind-tunnel, including be sequentially connected admission line, to air-flow
Carry out the straight length of rectification, air-flow is carried out the diffuser of diffusion deceleration, steady air flow pressure pressurizer tank, air-flow be depressured risen
The nozzle section of speed, draw the injection section that air-flow is exhausted；The thermocouple is between nozzle section and injection section.Wind-tunnel can pin
To thermocouple construction, so construction of wind tunnel size is unnecessary excessive, i.e., small-sized normal temperature wind-tunnel.Connected between pipeline by flange.
As an improvement the diffuser is taper, its less one end is connected with straight length, larger one end with it is steady
Press case connection.
As an improvement installation and adjustment valve regulation air flow rate on the admission line, installation is total on the pressurizer tank
Probe is pressed, the nozzle section exit installs wall static probe, air velocity is measured.
As a preferred embodiment, described source of the gas is air compressor.Source of the gas can select different work(according to tunnel airstream flow
The air compressor of rate.
As a preferred embodiment, described displacement mechanism is five degree of freedom displacement mechanism, can be achieved the angle of pitch, yaw angle, X,
Y, the movement in five directions of Z.Due to CO2The light that laser is sent does not have color, visually can't see, and living human eye is not
It can look at straight, it is serious to the extent of injury of eyes, so thermocouple clamping is adjusted on the cantilever of displacement mechanism by displacement mechanism
The position of thermocouple is saved, thermal cross is placed in light path.
As a preferred embodiment, described laser heating system is CO2Laser heating system.CO2Laser heating system master
To include laser bodies and laser controller, power continuously adjustabe, required temperature can be heated to thermocouple.Due to
CO2What what laser was sent just must not visually see, so must be protected to light path, testing crew must wear goggles, and
And a set of device for sending red light or other color of light is installed on generating laser side as guiding light, guiding light can be instead
Penetrate and reflect, laser mainly transmits, so will will guide light and laser optical path by light combination mirror piece when carrying out light path debugging
Be adjusted to it is parallel, best light path with one heart or the distance between two kinds of light are measured by the method for laser instantaneous ignition paper, to try
The position of thermocouple is adjusted when testing by displacement mechanism, thermal cross is placed in light path and heated.
As a preferred embodiment, the control system includes Dynamic Data Acquiring module and control module.Dynamic Data Acquiring
Module need to be equipped with high sampling rate, and each system is connected by control line, is integrated into control system.Control module is controlled by PLC
Gasflow mach number processed, valve opening etc..
Thermocouple dynamic response characteristic is tested, and thermocouple probe (thermo wires contact) is produced a temperature jump,
Dynamic data collection system record electric thermo-couple temperature step response characteristic simultaneously, institute is right when taking its step temperature to rise to 63.2%
The timeconstantτ of the time answered, as temperature probe under the operating mode.Therefore the dynamic characteristic key of measurement thermocouple is at it
Use under (calibration) operating mode, trying to pop one's head in thermocouple temperature sensitive produces a temperature jump, and step delay time and can is tried one's best
Shorten.
This experimental rig is heated using laser to thermocouple temperature sensitive probe, and is blown simultaneously under required operating mode
Wind, check that whether each testing equipment of wind-tunnel is intact, tune-up data acquisition software and acquisition instrument, sets data acquisition system during experiment
Sample rate of uniting will be adjusted five degree of freedom displacement mechanism, made by school to reasonable level with clamping device by school thermocouple firm grip
Thermal cross or head are placed in wind tunnel spout center, by CO2Laser operation code opens CO2Laser, pass through five degree of freedom
Displacement mechanism, which is adjusted, causes thermal cross to be placed in laser optical path, and tunnel airstream Ma is to by school Ma for regulation, and continuously supplies, tune
Save CO2Laser heats, and thermocouple measuring temperature is reached test temperature, and stably, closes CO2Laser, observed number, which is adopted, is
Unite temperature jump curvilinear motion, until stepped curve drops to straight, source of the gas continuously supplies always in the process, and completes to try
Data acquisition is tested, records thermocouple dynamic response characteristic curve.Initial temperature is found out on thermocouple dynamic response characteristic curve
T0, time t0, final temperature T and step temperature 63.2% corresponding to time t, you can try to achieve thermocouple timeconstantτ value,
Method is quick, efficiency high.
Thermocouple can heat the power that maximum temperature depends on laser, and ordinary circumstance is existed using 40W CO2 lasers
Under continuous blowing state to thermocouple can 1200 DEG C of heat value, the dynamic temperature test of aero-engine flow field can be met completely, can
According to circumstances choose the laser of different capacity, laser power continuously adjustabe.
Experimental rig the key technical indexes：Flow Field in Wind Tunnel quality meets GJB1197-11；Step delay time ＜ 0.1ms；
Dynamical system sample rate：≮200kHz.
It is of the present utility model to be beneficial in that：Experimental provision with said structure realizes normal temperature wind-tunnel and adds laser to add
The method that thermal technology carries out dynamic calibration to thermocouple, cost is low, is easy to build, and test efficiency is high；Step temperature range is big, rank
Jump time delay is short, accurate less than 0.1ms, result of the test.
The foundation of the present apparatus has very important significance for the accuracy of dynamic temperature measurement.It is successfully applied in aviation
Engine or parts testpieces stagnation temperature, stagnation pressure inlet airflow distortion test, high speed transient temperature field test temperature probe and thermoelectricity
Even thermal response characteristics demarcation；It is dynamic that (between compressor stage, combustion chamber hugging, between stage of turbine) is can also be used between engine level
The thermal response characteristics of state temperature field test temperature probe and thermocouple is demarcated, and possesses certain measuring accuracy, can be with excellent
Change the structure design of aeroengine test temperature probe, the measurement accuracy of temperature probe is improved, to aero-engine temperature
The smooth development of field dynamic test provides important technical support.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model.
Marked in figure：1 source of the gas, 2 regulating valves, 3 straight lengths, 4 diffusers, 5 pressurizer tanks, 6 nozzle sections, 7 thermocouples, 8 injections
Section, 9 displacement mechanisms, 10 laser heating systems, 11 control systems.
Embodiment
In order that those skilled in the art more fully understands the technical solution of the utility model, with reference to specific implementation
The utility model is described in further detail for mode.
As shown in figure 1, the utility model include thermocouple 7, thermocouple 7 is blown calibration wind tunnel, for calibration wind
The source of the gas 1 of hole air feed；Also include for the laser heating system 10 for the heating of thermocouple 7, for adjusting the locus of thermocouple 7
Displacement mechanism 9 and whole device is controlled and the control system of data acquisition 11.
The calibration wind tunnel is small-sized normal temperature wind-tunnel, including be sequentially connected admission line, to air-flow carry out rectification it is straight
Pipeline section 3, the diffuser 4 that diffusion deceleration is carried out to air-flow, the pressurizer tank 5 of steady air flow pressure, the jet pipe that raising speed is depressured to air-flow
Section 6, draw the injection section 8 that air-flow is exhausted；The thermocouple 7 is between nozzle section 6 and injection section 8.Diffuser 4 is cone
Shape, its less one end are connected with straight length 3, and larger one end is connected with pressurizer tank 5.Installation and adjustment valve 2 is adjusted on admission line
Air flow rate is saved, total pressure probe is installed, wall static probe is installed in the exit of nozzle section 6, to air-flow on the pressurizer tank 5
Speed measures.
Source of the gas 1 is air compressor, can select different capacity according to tunnel airstream flow.
Displacement mechanism 9 is five degree of freedom displacement mechanism, and the movement of the angle of pitch, five yaw angle, X, Y, Z directions can be achieved.
Make to be placed in wind tunnel spout center by the contact of school thermocouple 7 or head.
Laser heating system 10 is CO2Laser heating system.
Control system 11 includes Dynamic Data Acquiring module and control module.Dynamic Data Acquiring module need to be equipped with high sampling
Rate, each system is connected by control line, is integrated into control system.Control module controls gasflow mach number, regulation by PLC
Valve opening of valve 2 etc..
The experimental rig needs to demarcate Flow Field in Wind Tunnel after building up, and Flow Field in Wind Tunnel quality need to meet GJB1197-11
Requirement, to each instrument and meter carry out gauging calibration, meet its required precision.
Check that whether each testing equipment of wind-tunnel is intact, tune-up data acquisition software and acquisition instrument, sets data during experiment
Acquisition system sample rate will adjust five degree of freedom displacement mechanism to reasonable level, with clamping device by school thermocouple firm grip,
Make to be placed in wind tunnel spout by school thermal cross or head.
Claims (8)
- A kind of 1. thermocouple dynamic response characteristic experimental rig based on laser, it is characterised in that：Including thermocouple, to thermoelectricity Calibration wind tunnel, the source of the gas for calibration wind tunnel air feed being occasionally blown；Also include being used for the laser heating system for thermocouple heating System, the displacement mechanism for adjusting thermocouple locus and whole device is controlled and the control system of data acquisition System.
- 2. a kind of thermocouple dynamic response characteristic experimental rig based on laser according to claim 1, its feature exist In：The calibration wind tunnel is small-sized normal temperature wind-tunnel, including be sequentially connected admission line, to air-flow carry out rectification straight length, Diffuser, the pressurizer tank of steady air flow pressure, the nozzle section that raising speed is depressured to air-flow, the extraction gas of diffusion deceleration are carried out to air-flow The injection section that stream is exhausted；The thermocouple is between nozzle section and injection section.
- 3. a kind of thermocouple dynamic response characteristic experimental rig based on laser according to claim 2, its feature exist In：The diffuser is taper, and its less one end is connected with straight length, and larger one end is connected with pressurizer tank.
- 4. a kind of thermocouple dynamic response characteristic experimental rig based on laser according to claim 2, its feature exist In：Installation and adjustment valve regulation air flow rate on the admission line, total pressure probe is installed on the pressurizer tank, the nozzle section goes out Wall static probe is installed at mouthful.
- 5. a kind of thermocouple dynamic response characteristic experimental rig based on laser according to claim 1, its feature exist In：Described source of the gas is air compressor.
- 6. a kind of thermocouple dynamic response characteristic experimental rig based on laser according to claim 1, its feature exist In：Described displacement mechanism is five degree of freedom displacement mechanism, and the movement of the angle of pitch, five yaw angle, X, Y, Z directions can be achieved.
- 7. a kind of thermocouple dynamic response characteristic experimental rig based on laser according to claim 1, its feature exist In：Described laser heating system is CO2 laser heating systems.
- 8. a kind of thermocouple dynamic response characteristic experimental rig based on laser according to claim 1, its feature exist In：The control system includes Dynamic Data Acquiring module and control module.
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| CN201720547686.5U CN206905939U (en) | 2017-05-17 | 2017-05-17 | A kind of thermocouple dynamic response characteristic experimental rig based on laser |
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| CN201720547686.5U CN206905939U (en) | 2017-05-17 | 2017-05-17 | A kind of thermocouple dynamic response characteristic experimental rig based on laser |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186815A (en) * | 2018-10-31 | 2019-01-11 | 北京航空航天大学 | A kind of low temperature High Mach number detecting probe temperature calibration device |
| CN111006793A (en) * | 2019-12-18 | 2020-04-14 | 北京航空航天大学 | K-type armored thermocouple response time measuring method based on heat pipe method |
| CN112161728A (en) * | 2020-09-04 | 2021-01-01 | 南京理工大学 | Double-functional type calibration device and method for transient heat flow meter |
-
2017
- 2017-05-17 CN CN201720547686.5U patent/CN206905939U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186815A (en) * | 2018-10-31 | 2019-01-11 | 北京航空航天大学 | A kind of low temperature High Mach number detecting probe temperature calibration device |
| CN111006793A (en) * | 2019-12-18 | 2020-04-14 | 北京航空航天大学 | K-type armored thermocouple response time measuring method based on heat pipe method |
| CN112161728A (en) * | 2020-09-04 | 2021-01-01 | 南京理工大学 | Double-functional type calibration device and method for transient heat flow meter |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180119 Termination date: 20180517 |
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| CF01 | Termination of patent right due to non-payment of annual fee |