Volume 35 Issue 5
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SONG Jianyu, WU Jingfeng, QIU Changbo. Civil turboshaft engine induction system icing test[J]. Journal of Aerospace Power, 2020, 35(5): 1089-1098. doi: 10.13224/j.cnki.jasp.2020.05.020
Citation: SONG Jianyu, WU Jingfeng, QIU Changbo. Civil turboshaft engine induction system icing test[J]. Journal of Aerospace Power, 2020, 35(5): 1089-1098. doi: 10.13224/j.cnki.jasp.2020.05.020
shu

Civil turboshaft engine induction system icing test

doi: 10.13224/j.cnki.jasp.2020.05.020
  • 1.

    Airworthiness Certification Center,Civil Aviation Ad ministration of China,Beijing 100102,China

  • 2.

    Hunan Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China

  • Received Date: 2019-11-09
  • Publish Date: 2020-05-28
    Abstract
  • Focusing on the content of China Civil Aviation Regulations CCAR-33R2 article 33.68, a test method for turboshaft engine complying with airworthiness regulation requirement was provided, including icing critical point analysis, icing certification test points determination, engine icing certification test. In combination with the turboshaft engine operating envelope, critical point analysis was conducted to determine the icing certification test points. Several icing calculation points were selected in the icing envelope, and icing positions and amounts were calculated for each point. The calculation results show that the area where the temperature is close to 0 ℃ and the altitude is low is the zone where the turboshaft engine has a significant ice amount. During the icing test, the temperature points at which ice formation just occurred and the amount of icing was the largest were found in the temperature range of -4 ℃ to -1 ℃. The test results show that the temperature point with the largest amount of icing is the most severe icing test point.

     

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