CN105890804A - Method of improving airflow total temperature measurement precision of temperature sensor - Google Patents

Method of improving airflow total temperature measurement precision of temperature sensor Download PDF

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Publication number
CN105890804A
CN105890804A CN201610214774.3A CN201610214774A CN105890804A CN 105890804 A CN105890804 A CN 105890804A CN 201610214774 A CN201610214774 A CN 201610214774A CN 105890804 A CN105890804 A CN 105890804A
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temperature
flow
air
stagnation
temperature sensor
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CN105890804B (en
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马宏伟
马融
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Beihang University
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Beihang University
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
    • G01K13/024—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow of moving gases

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  • General Physics & Mathematics (AREA)
  • Measuring Temperature Or Quantity Of Heat (AREA)

Abstract

The present invention discloses a method of improving the airflow total temperature measurement precision of a temperature sensor. In the tests, such as engine, turbine, etc., the temperature sensors, such as a thermocouple, a thermal resistor, a total temperature comb, a total temperature rake, etc., are used to measure an airflow total temperature. At present, an error caused by the three dimensional airflow velocity is neglected generally, and the temperature data measured by the sensors is considered as the airflow total temperature of a measured point, thereby easily causing a larger measurement error. The present invention provides the method of improving the airflow total temperature measurement precision of the temperature sensor. The method comprises the steps of correlating a total temperature sensing coefficient with an airflow mach number, a deflection angle and a pitching angle; establishing a mapping relationship of the total temperature sensing coefficient, the airflow mach number, the deflection angle and the pitching angle via a calibration experiment; and utilizing the calibration data and the relevant flow field information to convert the temperature data measured by the sensors into the airflow total temperature. By the method, the three dimensional velocity error of the airflow total temperature measured by the temperature sensor can be reduced, and the airflow total temperature measurement precision of the temperature sensor can be improved effectively.

Description

A kind of method improving temperature sensor measurement air-flow stagnation temperature precision
Technical field
The present invention relates to use contact temperature pick-up, as used the temperature probe of the sensor such as thermocouple, thermal resistance, Measure air-flow stagnation temperature technical field, particularly to one reduce three-dimensional velocity error, improve temperature sensor measure air-flow total The method of temperature precision.
Background technology
When air-flow is in time soaking material flows in the gas flow, just to the so-called critical point flowed on object, due to air-flow Stagnation effect, air velocity be equal to zero, the temperature in this point just reaches maximum, and this temperature is exactly stagnation temperature, cries again stagnant Only temperature.In steady flow, stagnation temperature change can be used to measure heat or merit transfer.
At present general in engineering contact temperature pick-up is used to measure air-flow stagnation temperature, including single-point stagnation temperature pick-up, many Point stagnation temperature pick-up, such as single-point thermocouple stagnation temperature probe, stagnation temperature comb, stagnation temperature rake etc..
It is true that temperature sensor has certain bulk, such as the ball head of thermocouple measurement end, only just To on the stagnation point flowed, the stagnation temperature being only air-flow of impression, the temperature of other position impression of pick-up is below stagnation temperature, i.e. Make pick-up head install stagnation cover additional, due in order to allow pick-up experience fresh flow stagnation temperature, reduce conduction error, stagnation Having discharge orifice on the wall of cover downstream, pick-up head still has certain speed, and air-flow does not has complete stagnation and gets off, So, the temperature that temperature sensor records actually, be lower than stagnation temperature, and relevant with flow-deviation angle, the angle of pitch and Mach number. Current measuring method and technology, it is considered that the temperature data that said temperature pick-up records, it is simply that the stagnation temperature of measured point, Even if being modified, the most only carrying out the correction of one-dimensional speed, have ignored the error that three-dimensional air velocity causes, easily causing relatively Big measurement error is especially high at speed of incoming flow, carry out the operating mode that flow path direction change is violent.
Invention is a kind of improves the method that temperature sensor measures air-flow stagnation temperature precision, proposes stagnation temperature and experiences coefficient Associate with between gasflow mach number, flow-deviation angle, the air-flow angle of pitch, set up its mapping relations by calibration experiments, utilize school Quasi-data and relevant information of flow, the data reduction that pick-up can be recorded goes out air-flow stagnation temperature.Make can reduce in this way The velocity error of stagnation temperature measured by pick-up, is effectively improved temperature sensor and measures the precision of air-flow stagnation temperature.
Summary of the invention
Present invention mainly solves technical problem is that: has invented a kind of temperature sensor that improves and has measured air-flow stagnation temperature precision Method, can reduce pick-up and measure the three-dimensional velocity error of air-flow stagnation temperature, can be effectively improved temperature sensor measurement air-flow total The precision of temperature.
For solving above-mentioned technical problem, the technical solution used in the present invention is: the stagnation temperature impression introducing temperature sensor is The definition of number, the stagnation temperature obtaining temperature sensor first with calibration experiments experiences coefficient gamma and gasflow mach number M, flow-deviation angle Corresponding relation between α, air-flow pitching angle beta；Again when reality is measured, according to the gasflow mach number of measured point, flow-deviation angle, The air-flow angle of pitch, is obtained the stagnation temperature of temperature sensor by calibration data and experiences coefficient, and recycling stagnation temperature is experienced the definition of coefficient and done Indentily transformation, processes the temperature data T that pick-up actual measurement flow field can be obtained by datapConverse air-flow stagnation temperature T0。
Compared with prior art, the method for the present invention is used can to reach techniques below effect:
1. the present invention points out that the stagnation temperature of temperature sensor is experienced coefficient and not only affected by Mach number, flow-deviation angle, is also subject to The air-flow angle of pitch affects, and proposes to associate with Mach number, flow-deviation angle, the air-flow angle of pitch while that stagnation temperature experiencing coefficient, it is contemplated that Temperature sensor is measured the error impact of stagnation temperature by three-dimensional velocity, and proposes modification method.
The most existing temperature sensor measures air-flow stagnation temperature, seldom carries out velocity error correction, and the velocity error carried out is repaiied Just only considered the impact of one-dimensional speed, do not recognizing that the change of flow-deviation angle, the angle of pitch also brings along temperature sensor speed The change of error, does not carry out comprising flow-deviation angle, the three-dimensional velocity error correction of angle of pitch impact.
3. the present invention can effectively reduce the three-dimensional velocity error of temperature sensor measurement air-flow stagnation temperature, is greatly improved temperature The precision of air-flow stagnation temperature measured by pick-up.
Accompanying drawing explanation
Fig. 1 is the air-flow angle of pitch, deflection angle definition, with the relativeness of temperature sensor.
Fig. 2 is the thermocouple schematic diagram of band stagnation cover.
Fig. 3 is calibration wind tunnel experimental system schematic diagram, passes through calibration experiments, it is possible to obtain the stagnation temperature impression of temperature sensor Coefficient.Calibration wind tunnel experimental system includes centrifugal blower (source of the gas), calibration wind tunnel (containing pressurizer tank, contraction section, experimental section etc.), surveys Amount flow total pressure probe, stagnation temperature probe, static probe, displacement mechanism, pressure transducer, temperature transmitter, atmospheric pressure meter, Computer data acquisition system.
Fig. 4, Fig. 5 be respectively certain temperature sensor stagnation temperature when M=0.5, M=0.8 experience coefficient and flow-deviation angle and The association of the angle of pitch, is measured by calibration wind tunnel experiment reality and obtains, it can be seen that different Mach number, different air-flow are inclined In the case of corner, the different air-flow angle of pitch flow, it is different that the stagnation temperature of this temperature sensor experiences factor v.
Detailed description of the invention
1, introduce the stagnation temperature of temperature sensor and experience the definition of coefficient:
γ = 1 - T 0 - T p T 0 [ 1 + 2 ( k - 1 ) M 2 ]
Or its indentily transformation, as
γ = 1 - T 0 - T p T 0 [ 1 - ( p s p 0 ) k - 1 k ]
K is specific heats of gases ratios, psFor air-flow static pressure, p0For air-flow stagnation pressure, TpThe temperature recorded for pick-up.
2, calibration experiments is utilized, it is thus achieved that the stagnation temperature of temperature sensor experiences coefficient gamma and gasflow mach number M, flow-deviation angle Corresponding relation between α, air-flow pitching angle beta.
Can utilize calibration wind tunnel experimental system as depicted that temperature sensor stagnation temperature is experienced coefficient to calibrate.School Quasi-wind tunnel experiment system includes centrifugal blower (source of the gas), calibration wind tunnel (containing pressurizer tank, contraction section, experimental section etc.), measures and flow Total pressure probe, stagnation temperature probe, static probe, displacement mechanism, pressure transducer, temperature transmitter, atmospheric pressure meter, computer Data collecting system.
Measure stagnation temperature and the stagnation pressure of air-flow in the outlet of wind-tunnel pressurizer tank, have baroport at experimental section wall quiet to measure Pressure.
Be positioned at wind tunnel experiment section by school temperature sensor by displacement mechanism, deflection angle between pick-up and air-flow and The angle of pitch, can be changed by displacement mechanism, measure, and can change, by adjusting source of the gas operating mode, the Mach number flowed.
At each mach number, change the angle of pitch, such as-20 °～+20 °, be spaced 10 °；In each angle of pitch position Put, change deflection angle, such as-30 °～+30 °, be spaced 10 °, respectively measurement air-flow stagnation temperature, stagnation pressure, static pressure, Mach number, by school temperature The measured temperature of degree pick-up, is calculated temperature sensor under different Mach number, the different angle of pitch, different deflection angle Stagnation temperature experiences coefficient, and is associated.
Fig. 3 is that certain temperature sensor stagnation temperature when M=0.5 experiences associating of coefficient and flow-deviation angle and the angle of pitch, Fig. 4 Associating of coefficient and flow-deviation angle and the angle of pitch is experienced for certain temperature sensor stagnation temperature when M=0.8.
3, after actual being measured, according to the gasflow mach number of measured point, flow-deviation angle, the air-flow angle of pitch, by upper Stating calibration associated data, such as, certain temperature sensor is when M=0.5, flow-deviation angle-10 °, the air-flow angle of pitch 20 °, it is known that, It is 0.845 that stagnation temperature experiences coefficient.
4, recycling stagnation temperature is experienced the definition of coefficient and is done indentily transformation, is processed pick-up actual measurement flow field can be obtained by data The temperature data T arrivedpConverse air-flow stagnation temperature T0。

Claims (5)

1. the present invention is a kind of method improving temperature sensor measurement air-flow stagnation temperature precision, proposes total warming of temperature sensor Being associated by between coefficient gamma with gasflow mach number M, flow-deviation angle α, air-flow pitching angle beta, being processed by calibration and data can Reduce the stagnation temperature measurement error that air velocity is brought.
A kind of temperature sensor that improves the most according to claim 1 measures air-flow stagnation temperature T0The method of precision, temperature sensor Stagnation temperature experience coefficient gamma definition be:
Or its indentily transformation, as
K is specific heats of gases ratios, psFor air-flow static pressure, p0For air-flow stagnation pressure, TpThe temperature recorded for pick-up.
A kind of method improving temperature sensor measurement air-flow stagnation temperature precision the most according to claim 1, is characterized in that: first The stagnation temperature utilizing calibration experiments to obtain temperature sensor experiences coefficient gamma and gasflow mach number M, flow-deviation angle α, air-flow pitching Corresponding relation between angle beta；Again when reality is measured, according to the gasflow mach number of measured point, flow-deviation angle, air-flow pitching Angle, is obtained the stagnation temperature of temperature sensor by calibration data and experiences coefficient, and recycling stagnation temperature is experienced the definition of coefficient and done indentily transformation, The temperature data T that pick-up actual measurement flow field can be obtained is processed by datapConverse air-flow stagnation temperature T0。
A kind of method improving temperature sensor measurement air-flow stagnation temperature precision the most according to claim 3, is characterized in that: suitable Include using thermocouple, the measurement probe of thermal resistance equitemperature sensor by scope.
A kind of method improving temperature sensor measurement air-flow stagnation temperature precision the most according to claim 3, is characterized in that: suitable Include single point temperature pick-up, multi-point temp pick-up etc. by scope, such as blade profile temperature detector probe, stagnation temperature probe, thermometric rake, survey Temperature comb etc..
CN201610214774.3A 2016-04-08 2016-04-08 A method of it improving temperature sensor and measures total airflow temperature precision Active CN105890804B (en)

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106885681A (en) * 2017-03-02 2017-06-23 北京航空航天大学 A kind of monocline hole dynamic pressure probe for measuring rotor outlet subsonics three-dimensional flow field
CN106885682A (en) * 2017-03-06 2017-06-23 北京航空航天大学 A kind of cylindrical type diplopore dynamic pressure probe for measuring rotor outlet subsonics three-dimensional flow
CN106908191A (en) * 2017-03-09 2017-06-30 北京航空航天大学 A kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field
CN107131974A (en) * 2017-05-08 2017-09-05 北京航空航天大学 A kind of temperature probe comb with air-breathing branching rod structure
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
CN111649848A (en) * 2020-05-29 2020-09-11 西安联创分布式可再生能源研究院有限公司 Temperature recovery coefficient determination method

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CN102692278A (en) * 2012-06-06 2012-09-26 中北大学 Optical fiber total temperature sensor for high-speed airflow and temperature measurement system for optical fiber total temperature sensor

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106885681A (en) * 2017-03-02 2017-06-23 北京航空航天大学 A kind of monocline hole dynamic pressure probe for measuring rotor outlet subsonics three-dimensional flow field
CN106885682A (en) * 2017-03-06 2017-06-23 北京航空航天大学 A kind of cylindrical type diplopore dynamic pressure probe for measuring rotor outlet subsonics three-dimensional flow
CN106908191A (en) * 2017-03-09 2017-06-30 北京航空航天大学 A kind of dynamic temperature force combination probe for measuring across sound Two Dimensional Unsteady flow field
CN107131974A (en) * 2017-05-08 2017-09-05 北京航空航天大学 A kind of temperature probe comb with air-breathing branching rod structure
CN107131974B (en) * 2017-05-08 2019-08-23 北京航空航天大学 A kind of temperature probe comb with air-breathing branching rod structure
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
CN111649848A (en) * 2020-05-29 2020-09-11 西安联创分布式可再生能源研究院有限公司 Temperature recovery coefficient determination method

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