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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

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文章导航 > 航空动力学报  > 2019 >  34(1): 34-44
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
引用本文: 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
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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]. Journal of Aerospace Power, 2019, 34(1): 34-44. doi: 10.13224/j.cnki.jasp.2019.01.005
Citation: 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]. Journal of Aerospace Power, 2019, 34(1): 34-44. doi: 10.13224/j.cnki.jasp.2019.01.005
shu

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

doi: 10.13224/j.cnki.jasp.2019.01.005

  • Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang 110015,China

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

  • Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang 110015,China

    摘要
  • 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, 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.

     

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    • 参考文献(16)
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出版历程
  • 收稿日期:  2017-12-21
  • 刊出日期:  2019-01-28

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