WO2020237828A1 - Dispositif de sonde de température totale très précise à faible perte propre - Google Patents

Dispositif de sonde de température totale très précise à faible perte propre Download PDF

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Publication number
WO2020237828A1
WO2020237828A1 PCT/CN2019/099412 CN2019099412W WO2020237828A1 WO 2020237828 A1 WO2020237828 A1 WO 2020237828A1 CN 2019099412 W CN2019099412 W CN 2019099412W WO 2020237828 A1 WO2020237828 A1 WO 2020237828A1
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WO
WIPO (PCT)
Prior art keywords
layer
total temperature
loss
probe
temperature
Prior art date
Application number
PCT/CN2019/099412
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English (en)
Chinese (zh)
Inventor
崔佳欢
刘俭
王稳
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浙江大学
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 浙江大学 filed Critical 浙江大学
Publication of WO2020237828A1 publication Critical patent/WO2020237828A1/fr

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
    • G01K1/20—Compensating for effects of temperature changes other than those to be measured, e.g. changes in ambient temperature
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
    • G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
    • G01K7/04—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples the object to be measured not forming one of the thermoelectric materials
    • G01K7/06—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples the object to be measured not forming one of the thermoelectric materials the thermoelectric materials being arranged one within the other with the junction at one end exposed to the object, e.g. sheathed type
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
    • G01K7/16—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements
    • G01K7/22—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements the element being a non-linear resistance, e.g. thermistor

Definitions

  • the invention relates to a rotating mechanical blade suitable for aerospace aircraft.
  • the structure has high accuracy, and the loss generated by the measuring device is small, and the effect on the efficiency of the whole machine is small.
  • thermal efficiency is related to the measured total temperature. Therefore, in order to accurately measure the performance and efficiency of spacecraft, we must measure the total temperature and total pressure in the engine.
  • the general measurement method is to install a temperature probe at the axial or circumferential position of the engine, often at the leading edge of the blade.
  • the total temperature measurement equipment When the total temperature probe measures the total temperature, the fluid flowing through the temperature sensor needs to be slowed down. Ideally, the total temperature measurement equipment is insulated from the outside, and the fluid near the temperature sensor stagnates. In fact, the measurement device cannot meet the adiabatic state, which is caused by temperature heat exchange. Measurement error, so the actual measured temperature T m is less than the stagnation temperature T t , and the difference between them is defined as the temperature recovery coefficient
  • T s represents the resting temperature
  • R f the value of R f ranges from 0-1.
  • R f 1
  • the temperature is the stagnation temperature.
  • the purpose of the present invention is to provide an accurate total temperature measuring device in view of the deficiencies of the prior art. Compared with the existing total temperature measuring device, the invention has the advantages of high measurement accuracy and low flow loss.
  • a total temperature probe device with low self-loss and high precision
  • the total temperature probe device is installed on the leading edge of the blade of the rotating mechanical blade of an aerospace vehicle, and the total temperature
  • the probe device includes the probe body.
  • the heat insulation layer is sheathed outside the stagnation layer.
  • the stagnation layer contains a temperature sensor, a stagnation layer and A first through hole is opened between the heat insulation layers, and a second through hole is opened along the cascade pitch direction at the bottom of the heat insulation layer.
  • the first through hole is located on a side close to the blade position.
  • first through holes there are multiple first through holes, and the multiple first through holes are uniformly distributed along the circumferential direction of the probe body.
  • the multiple second through holes are evenly distributed along the circumferential direction of the probe body.
  • the probe body is cylindrical, with a cylindrical cavity opened in the hollow to form a stagnation layer; a flat side of the cylindrical cavity is open; a cylindrical annular cavity is also opened outside the cylindrical cavity to form a partition Thermal layer.
  • a temperature sensor support extends inward in the stagnation layer of the probe body
  • a probe support extends outward from the bottom of the probe body
  • lead holes penetrate through the temperature sensor support and the probe support.
  • the temperature sensor is a thermocouple or a thermal resistance.
  • the beneficial effect of the present invention is that by providing dual chambers, the stagnation layer mainly functions to measure temperature, and the function of the heat insulation layer is to reduce the measurement error caused by the heat exchange between the mainstream fluid and the stagnation layer fluid. , The total temperature is accurately measured, and the opening at the bottom of the insulation layer allows the fluid to flow out along the main flow direction, destroying the separation bubble at the connection position of the insulation layer and the support, and reducing the flow loss.
  • Figure 1 is a three-dimensional schematic diagram of the present invention
  • Figure 2 is a front view of the present invention
  • Figure 3-4 is a cross-sectional view of the present invention.
  • Figure 5 is a perspective view of the present invention.
  • the present invention provides a total temperature probe device with low self-loss and high accuracy.
  • the total temperature probe device is installed on the leading edge of the blade of a rotating mechanical blade of an aerospace vehicle.
  • the probe body there are two layers of chambers on the probe body, which are respectively marked as stagnation layer 2 and heat insulation layer 3.
  • the heat insulation layer 3 is set outside the stagnation layer 2, and the stagnation layer 2 contains the temperature sensor 1.
  • a first through hole 4 is opened between the stagnation layer 2 and the heat insulation layer 3, and a second through hole 5 is opened at the bottom of the heat insulation layer 3 along the cascade pitch direction.
  • the purpose of the thermal insulation layer 3 is to isolate the heat exchange between the mainstream fluid and the fluid in the stagnation layer 2.
  • the fluid in the thermal insulation layer 3 flows out in the main flow direction through the second through hole 5, blowing away the separation bubbles at the tail of the probe, and reducing the flow loss caused by the installation of the probe.
  • the first through hole 4 is located on the side close to the position of the blade; the first through hole 4 has multiple, and the multiple first through holes 4 are evenly distributed along the circumferential direction of the probe body. There are multiple second through holes 5, and the multiple second through holes 5 are evenly distributed along the circumferential direction of the probe body. Two examples are given in the drawings.
  • the probe body is cylindrical, a cylindrical cavity is opened in the hollow to form a stagnation layer 2; a plane side of the cylindrical cavity is open; and a cylindrical annular cavity is also opened outside the cylindrical cavity
  • the body, the thermal insulation layer 3 is formed.
  • a further technical solution is that the stagnation layer 2 of the probe body extends inwardly with a temperature sensor support, the bottom of the probe body extends outwards with a probe support 7, and the temperature sensor support and the probe support 7 penetrate Lead hole.
  • the temperature sensor may be a thermocouple or a thermal resistance.
  • the total temperature probe device of the present invention When in use, the total temperature probe device of the present invention is installed on the leading edge of the blade, the axis is perpendicular to the leading edge of the blade, and a plurality of total temperature probes are installed along the height direction of the blade to reduce measurement errors caused by uneven distribution of total temperature.
  • the temperature sensor 1 is connected to the temperature sensor 1 through a wire inserted into the lead hole.
  • the temperature sensor 1 contacts the main flow fluid to convert the heat signal into a heat signal, and the temperature value is measured by the connected computer.
  • the fluid in the stagnant layer 2 flows into the thermal insulation layer 3 through the first through hole 4.
  • the early total temperature measuring device has only one chamber, the temperature sensor is installed in the chamber, and the chamber is closed.
  • the disadvantage of this method is that the incoming fluid cannot affect the total temperature.
  • the temperature probe continues to heat up, causing large measurement errors.
  • Gradually developed into the chamber near the blades to increase the exhaust holes using this method, the incoming gas can continue to heat the total temperature probe, but due to the temperature difference between the inner and outer walls of the chamber, there is heat exchange, which has an impact on the measured total temperature.
  • the axial direction of the exhaust hole is perpendicular to the main flow direction, and the jet flow affects the following blade performance experiments.
  • the present invention is improved into two chambers.
  • the main function of the outer chamber is to isolate the influence of the temperature of the mainstream fluid on the temperature of the inner chamber fluid, and the exhaust hole is provided at the bottom of the outer chamber. Effectively reduce the separation bubbles generated by the fluid at the connection position of the outer chamber and the support, and the fluid flowing out of the exhaust hole can destroy the separation bubbles.
  • the measuring device provided by the present invention optimizes the loss caused by the measuring device, and has little influence on the efficiency calculation of the whole machine.

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

Abstract

L'invention concerne un dispositif de sonde de température totale très précise à faible perte propre. Le dispositif est monté sur un bord d'attaque d'une pale mécanique rotative d'un véhicule aérospatial, et comprend un corps de sonde, le corps de sonde étant pourvu de deux couches de chambres qui sont respectivement marquées en tant que couche stagnante (2) et couche d'isolation thermique (3) ; la couche d'isolation thermique (3) se situe à l'extérieur de la couche stagnante (2) de manière gainée ; la couche stagnante contient un capteur de température (1) ; un premier trou traversant (4) est ménagé entre la couche stagnante (2) et la couche d'isolation thermique (3) ; et le fond de la couche d'isolation thermique (3) est pourvu de seconds trous traversants (5) dans la direction de pas d'une aube. Le dispositif de mesure de température totale vise à mesurer précisément la température de stagnation d'un bord d'attaque de pale et à réduire la perte provoquée par le dispositif de mesure de température, afin d'obtenir une mesure de température totale plus précise dans la mesure où l'impact d'un champ d'écoulement original est le plus faible possible.
PCT/CN2019/099412 2019-05-28 2019-08-06 Dispositif de sonde de température totale très précise à faible perte propre WO2020237828A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201910448308.5A CN110160667A (zh) 2019-05-28 2019-05-28 一种自身损失小的精度高的总温探头装置
CN201910448308.5 2019-05-28

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WO2020237828A1 true WO2020237828A1 (fr) 2020-12-03

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Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113804449B (zh) * 2020-06-17 2024-03-26 中国航发商用航空发动机有限责任公司 总温检测装置及航空发动机
CN113588105A (zh) * 2021-08-31 2021-11-02 中国航发贵阳发动机设计研究所 高导叶型总温探针结构

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1330766A (zh) * 1998-10-20 2002-01-09 航空电子特制品有限公司 具有内装空气温度传感器的飞机探头
CN103674304A (zh) * 2013-12-03 2014-03-26 天津航空机电有限公司 一种热电偶的滞止室
CN106840459A (zh) * 2017-03-24 2017-06-13 北京航空航天大学 一种十孔总温测量探针
CN106940230A (zh) * 2017-03-28 2017-07-11 北京航空航天大学 一种九孔总温测量探针
CN108088588A (zh) * 2016-11-22 2018-05-29 霍尼韦尔国际公司 用于抗结冰总气温探头的系统和方法
CN108279080A (zh) * 2017-01-05 2018-07-13 霍尼韦尔国际公司 用于具有空气射流的抗结冰总气温探头的系统和方法

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201213576D0 (en) * 2012-07-31 2012-09-12 Rolls Royce Plc Total temperature probe
CN210322067U (zh) * 2019-05-28 2020-04-14 浙江大学 自身损失小的精度高的总温探头装置

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1330766A (zh) * 1998-10-20 2002-01-09 航空电子特制品有限公司 具有内装空气温度传感器的飞机探头
CN103674304A (zh) * 2013-12-03 2014-03-26 天津航空机电有限公司 一种热电偶的滞止室
CN108088588A (zh) * 2016-11-22 2018-05-29 霍尼韦尔国际公司 用于抗结冰总气温探头的系统和方法
CN108279080A (zh) * 2017-01-05 2018-07-13 霍尼韦尔国际公司 用于具有空气射流的抗结冰总气温探头的系统和方法
CN106840459A (zh) * 2017-03-24 2017-06-13 北京航空航天大学 一种十孔总温测量探针
CN106940230A (zh) * 2017-03-28 2017-07-11 北京航空航天大学 一种九孔总温测量探针

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