WO2020237828A1 - 一种自身损失小的精度高的总温探头装置 - Google Patents

一种自身损失小的精度高的总温探头装置 Download PDF

Info

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
Authority
WO
WIPO (PCT)
Prior art keywords
layer
total temperature
loss
probe
temperature
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2019/099412
Other languages
English (en)
French (fr)
Inventor
崔佳欢
刘俭
王稳
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Zhejiang University
Original Assignee
Zhejiang University
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 Zhejiang University filed Critical Zhejiang University
Publication of WO2020237828A1 publication Critical patent/WO2020237828A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Images

Classifications

    • 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.

Landscapes

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

Abstract

一种自身损失小的精度高的总温探头装置，安装在航空航天飞行器旋转机械叶片的叶片前缘，包括探头本体，探头本体上开有两层腔室，分别记为滞止层（2）和隔热层（3），隔热层（3）套设在滞止层（2）外，滞止层内含有温度传感器（1），滞止层（2）和隔热层（3）之间开有第一通孔（4），隔热层（3）底部沿叶栅距方向开有第二通孔（5）。该测量总温装置目的在于，准确测量叶片前缘滞止温度，并降低该温度测量装置带来的损失，在对原始流场影响尽可能小的情况下，获得较准确的总温测量。

Description

一种自身损失小的精度高的总温探头装置 技术领域
本发明涉及一种适用于航空航天飞行器旋转机械叶片，该结构具有较高的准确性，并且测量装置产生的损失较小，对整机的效率影响小。
背景技术
随着能源需求的增多，石油作为不可再生能源面临着资源短缺的问题，飞机制造商，发动机制造商以及相关机构都在积极开展提高燃油效率。热效率的测量准确性将直接影响对飞行器效率的计算，而热效率与测量的总温有关。因此，为了精确测量航天飞行器的性能和效率，我们必须测得发动机内的总温和总压。目前，通用的测量方法是在发动机轴向或周向位置安装温度探头，常常安装在叶片前缘。
总温探头测量总温时需要减缓流经温度传感器的流体，理想情况下，总温测量装备和外部绝热，温度传感器附近的流体滞止，实际上，测量装置无法满足绝热状态，温度换热造成测量误差，因此实际测量温度T m小于滞止温度T t，它们之间差别定义为温度恢复系数
Figure PCTCN2019099412-appb-000001
式中，T s代表静止温度，R f值范围为0-1，R f＝1时，温度为滞止温度。流场中安装温度探头会带来额外损失，因此必须考虑将装置对损失的影响降到最低，以保证通过温度探头计算得到的热效率与真实热效率相差不大。
发明内容
本发明的目的在于针对现有技术的不足，提出一种精确的总温测量装置，与现有的总温测量装置相比，其优点是，测量准确度高，自身产生的流动损失小。
为了达到上述目的，通过以下技术方案来实现的：一种自身损失小的精度高的总温探头装置，所述总温探头装置安装在航空航天飞行器旋转机械叶片的叶片前缘，所述总温探头装置包括探头本体，探头本体上开有两层腔室，分别记为滞止层和隔热层，隔热层套设在滞止层外，滞止层内含有温度传感器，滞止层和隔热层之间开有第一通孔，隔热层底部沿叶栅距方向开有第二通孔。
进一步的，所述第一通孔位于靠近叶片位置一侧。
进一步的，所述第一通孔具有多个，多个第一通孔沿探头本体的圆周方向均匀分布。
进一步的，所述第二通孔具有多个，多个第二通孔沿探头本体的圆周方向均匀分布。
进一步的，所述探头本体呈圆柱状，中空心开有一圆柱形腔体，形成滞止层；圆柱形腔体的一平面侧敞开；该圆柱形腔体外还开有圆柱环形腔体，形成隔热层。
进一步的，所述探头本体的滞止层中向内延伸有温度传感器支座，探头本体的底部向外延伸有探头支座，温度传感器支座和探头支座上贯穿有引线孔。
进一步的，所述温度传感器为热电偶或热电阻。
相对于现有技术，本发明的有益效果是，通过设置双腔室，滞止层主要作用是测量温度，隔热层作用是降低主流流体与滞止层流体之间的热量交换导致的测量误差，精确地测量总温，并且隔热层底部开孔使流体沿着主流方向流出，破坏隔热层与支座连接位置的分离泡，降低流动损失。
附图说明
图1为本发明的立体示意图；
图2为本发明的正视图；
图3-4为本发明的剖视图；
图5为本发明的透视图。
具体实施方式
为使本发明的目的、技术方案及优点更加清楚明白，下面结合附图和具体实施例对本发明的低压涡轮叶片进行详细说明。
如图1-5所示，本发明提供一种自身损失小的精度高的总温探头装置，所述总温探头装置安装在航空航天飞行器旋转机械叶片的叶片前缘，所述总温探头装置包括探头本体，探头本体上开有两层腔室，分别记为滞止层2和隔热层3，隔热层3套设在滞止层2外，滞止层2内含有温度传感器1，滞止层2和隔热层3之间开有第一通孔4，隔热层3底部沿叶栅距方向开有第二通孔5。隔热层3的目的为隔绝主流流体与滞止层2内流体之间的热量交换。隔热层3内的流体通过第二通孔5沿主流方向流出，吹走探头尾部的分离泡，降低因安装探头导致的流动损失。
进一步的技术方案是，所述第一通孔4位于靠近叶片位置一侧；所述第一通孔4具有多个，多个第一通孔4沿探头本体的圆周方向均匀分布。所述第二通孔5具有多个，多个第二通孔5沿探头本体的圆周方向均匀分布。附图中给出了2个作为例子。
进一步的技术方案是，所述探头本体呈圆柱状，中空心开有一圆柱形腔体，形成滞止层2；圆柱形腔体的一平面侧敞开；该圆柱形腔体外还开有圆柱环形腔体，形成隔热层3。
进一步的技术方案是，所述探头本体的滞止层2中向内延伸有温度传感器支座，探头本体的底部向外延伸有探头支座7，温度传感器支座和探头支座7上贯穿有引线孔。
进一步的技术方案是，所述温度传感器可以为热电偶或热电阻。
使用时，将本发明的总温探头装置安装在叶片前缘，轴线垂直于叶片前缘，沿叶高方向安装多个总温探头，降低总温分布不均带来的测量误差。通过导线穿入引线孔中与温度传感器1相连，温度传感器1与主流来流流体接触将热信号转变成热信号，由连接的电脑测出温度值。滞止层2流体通过第一通孔4流入隔热层3。
现将本发明提供的总温测量装置的工作原理阐述如下：早期总温测量装置只有一个腔室，温度传感器安装在腔室内，腔室为封闭状态，这种方式缺点是来流流体无法对总温探头持续加热，造成较大的测量误差。逐渐发展为腔室靠近叶片附近增加排气孔，采用这种方法，来流气体可以持续的加热总温探头，但是腔室内壁和外壁由于温差存在换热，对测量的总温有影响，此外排气孔轴线方向垂直于主流流向，射流影响后面的叶片性能实验。本发明在单腔室测温装置的基础上，改进为两个腔室，外侧腔室主要作用是隔绝主流流体温度对内腔室流体温度的影响，而且排气孔设在外腔室底部，可以有效地减少由于流体在外腔室和支座连接位置产生的分离泡，排气孔流出的流体可以破坏分离泡的产生。与现有总温测量装置相比，本发明提供的测量装置优化了测量装置带来的损失，对于整机效率计算影响小。
另外，需要说明的是本实施方式中所提到的“第一”、“第二”并不代表结构或者功能上的绝对区分关系，而仅仅是为了描述的方便。本领域技术人员在考虑说明书及实践这里公开的公开后，将容易想到本申请的其它实施方案。本申请旨在涵盖本公开的任何变型、用途或者适应性变化，这些变型、用途或者适应性变化遵循本公开的一般性原理并包括本申请未公开的本技术领域中的公知常识或惯用技术手段。说明书和实施例仅被视为示例性的，本申请的真正范围和精神由下面的权利要求指出。
应当理解的是，本申请并不局限于上面已经描述并在附图中示出的精确结构，并且可以在不脱离其范围进行各种修改和改变。本申请的范围仅由所附的权利要求来限制。

Claims (7)

  1. 一种自身损失小的精度高的总温探头装置，所述总温探头装置安装在航空航天飞行器旋转机械叶片的叶片前缘，其特征是：所述总温探头装置包括探头本体等，探头本体上开有两层腔室，分别记为滞止层和隔热层，隔热层套设在滞止层外，滞止层内含有温度传感器，滞止层和隔热层之间开有第一通孔，隔热层底部沿叶栅距方向开有第二通孔。
  2. 根据权利要求1所述的一种自身损失小的精度高的总温探头装置，其特征在于，所述第一通孔位于靠近叶片位置一侧。
  3. 根据权利要求2所述的一种自身损失小的精度高的总温探头装置，其特征在于，所述第一通孔具有多个，多个第一通孔沿探头本体的圆周方向均匀分布。
  4. 根据权利要求3所述的一种自身损失小的精度高的总温探头装置，其特征在于，所述第二通孔具有多个，多个第二通孔沿探头本体的圆周方向均匀分布。
  5. 根据权利要求4所述的一种自身损失小的精度高的总温探头装置，其特征在于，所述探头本体呈圆柱状，中空心开有一圆柱形腔体，形成滞止层；圆柱形腔体的一平面侧敞开；该圆柱形腔体外还开有圆柱环形腔体，形成隔热层。
  6. 根据权利要求5所述的一种自身损失小的精度高的总温探头装置，其特征在于，所述探头本体的滞止层中向内延伸有温度传感器支座，探头本体的底部向外延伸有探头支座，温度传感器支座和探头支座上贯穿有引线孔。
  7. 根据权利要求6所述的测温装置，其特征是在于，所述温度传感器为热电偶或热电阻。
PCT/CN2019/099412 2019-05-28 2019-08-06 一种自身损失小的精度高的总温探头装置 Ceased WO2020237828A1 (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201910448308.5 2019-05-28
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

Publications (1)

Publication Number Publication Date
WO2020237828A1 true WO2020237828A1 (zh) 2020-12-03

Family

ID=67629195

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2019/099412 Ceased WO2020237828A1 (zh) 2019-05-28 2019-08-06 一种自身损失小的精度高的总温探头装置

Country Status (2)

Country Link
CN (1) CN110160667A (zh)
WO (1) WO2020237828A1 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN120992043A (zh) * 2024-05-21 2025-11-21 中国航发商用航空发动机有限责任公司 一种总温测试受感部

Families Citing this family (3)

* 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
CN113588105B (zh) * 2021-08-31 2024-11-12 中国航发贵阳发动机设计研究所 高导叶型总温探针结构
CN114485977B (zh) * 2021-12-29 2026-05-26 中车永济电机有限公司 一种测定电机轴承温度分布的模拟装置及方法

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN120992043A (zh) * 2024-05-21 2025-11-21 中国航发商用航空发动机有限责任公司 一种总温测试受感部

Also Published As

Publication number Publication date
CN110160667A (zh) 2019-08-23

Similar Documents

Publication Publication Date Title
US10018648B2 (en) Systems, methods, and devices for fluid data sensing
CN111089702A (zh) 一种测量亚音三维稳态流场全参数的探针
CN110160667A (zh) 一种自身损失小的精度高的总温探头装置
US9631985B2 (en) Total air temperature sensors
CN106918410B (zh) 一种总温叶型探针
Englar Experimental investigation of the high velocity coanda wall jet applied to bluff trailing edge circulation control airfoils
BR102014021913A2 (pt) sensor de temperatura total do ar
CN103674304B (zh) 一种热电偶的滞止室
CN106840459A (zh) 一种十孔总温测量探针
BR102015002343A2 (pt) sonda de temperatura total do ar
CN106940230B (zh) 一种九孔总温测量探针
CN108917965B (zh) 一种基于热电阻的具有宽不敏感角的总温探针头部
US10585109B2 (en) Systems, methods, and devices for fluid data sensing
CN211668740U (zh) 一种用于亚音速二维流场的多点动态全参数测量装置
CN111076832A (zh) 一种防辐射的总温测量探针
CN212082825U (zh) 一种测量高亚音三维稳态流场的全参数探针
CN212082824U (zh) 一种测量跨音三维稳态流场全参数的探针
CN111089700B (zh) 一种用于亚音速二维流场的多点动态全参数测量装置
CN210322067U (zh) 自身损失小的精度高的总温探头装置
CN111060321A (zh) 一种测量机匣内壁附面层内二维稳态流场全参数的探针
CN211696708U (zh) 一种侧面开槽的双套管半球头总温探针
CN102937458A (zh) 稳态熵探针
US20150226082A1 (en) Instrumented vane
CN211696880U (zh) 一种测量亚音三维稳态流场全参数的探针
CN109799030B (zh) 一种适用于高焓气流的水冷式压力测量探头

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 19931216

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 19931216

Country of ref document: EP

Kind code of ref document: A1