Design and application of an air-cooled probe for total pressure measurement at combustor outlet

LIU Xupeng; SUN Qi; WANG Xiaoliang; XUE Xiusheng; YIN Dong

doi:10.13224/j.cnki.jasp.2019.01.005

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Design and application of an air-cooled probe for total pressure measurement at combustor outlet

燃烧、传热、传质 | 更新时间：2026-07-07

- Design and application of an air-cooled probe for total pressure measurement at combustor outlet
- Design and application of an air-cooled probe for total pressure measurement at combustor outlet
- 航空动力学报 2019年34卷第1期页码：34-44
- 作者机构：
  
  Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang,China,110015
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2019.01.005
  中图分类号：
- 纸质出版：2019
- 稿件说明：
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LIU Xupeng, SUN Qi, WANG Xiaoliang, XUE Xiusheng, YIN Dong. Design and application of an air-cooled probe for total pressure measurement at combustor outlet[J]. 航空动力学报, 2019, 34(1): 34-44.

doi: 10.13224/j.cnki.jasp.2019.01.005
LIU Xupeng, SUN Qi, WANG Xiaoliang, XUE Xiusheng, YIN Dong. Design and application of an air-cooled probe for total pressure measurement at combustor outlet[J]. 航空动力学报, 2019, 34(1): 34-44. DOI： 10.13224/j.cnki.jasp.2019.01.005.

doi: 10.13224/j.cnki.jasp.2019.01.005 DOI：

摘要

An air-cooled probe was designed for measurement of total pressure at combustor outlet; its cooling scheme combined the film cooling and convection cooling. With the aid of CFD technique

cooling effectiveness of the coolant jets at various blow ratios was compared; suitable blow ratios and configuration of film holes were chosen accordingly. The overall cooling performance of the probe was evaluated via CFD technique

the design was improved according to the simulation result

and the cooling effect of the leading edge was obviously strengthened by increasing the local coolant mass flow rate. The results of wind tunnel test indicated that

between Mach numbers 0.2 and 0.4

the probe achieved a high accuracy at various attack angles. The probe was utilized in an annular combustor rig test

the highest temperature reached 1760K and total pressure reaches 1036kPa. The result of rig test demonstrates that the coolant film distribution consistent appropriately with the CFD results.

Abstract

An air-cooled probe was designed for measurement of total pressure at combustor outlet; its cooling scheme combined the film cooling and convection cooling. With the aid of CFD technique

the design was improved according to the simulation result

and the cooling effect of the leading edge was obviously strengthened by increasing the local coolant mass flow rate. The results of wind tunnel test indicated that

between Mach numbers 0.2 and 0.4

the probe achieved a high accuracy at various attack angles. The probe was utilized in an annular combustor rig test

the highest temperature reached 1760K and total pressure reaches 1036kPa. The result of rig test demonstrates that the coolant film distribution consistent appropriately with the CFD results.

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