航空发动机进气支板电热防冰试验

doi:10.7527/S1000-6893.2017.121066

Abstract

Abstract:

To study the performance of electrothermal anti-icing, a test on the inlet strut of the small aero-engine is carried out. According to the structural features of this type of aero-engine inlet strut, three heating arrangement modes of the electrothermal anti-icing system are designed, which adopt one to three electrical heating rods as the heat sources at different locations along the direction of the strut chord length. The three heating modes are tested in the icing wind tunnel with different icing environment and electrical heating power. The measuring points are set on the strut surface to record the transient temperature change during the anti-icing process. As a result, the characteristics of temperature change on the strut surface during the anti-icing tests can be analyzed. The effect of the electrothermal power, the heating modes, the liquid water content and the oncoming airflow temperature on the anti-icing performance of the strut are all investigated experimentally. The results show that a reasonable electrical heating mode can achieve better anti-icing performance and the runback ice can be also avoided near the strut tailing edge.

Key words: electrothermal anti-icing, icing wind tunnel test, aero-engine strut, transient temperature, flow and heat transfer

CLC Number:

V211.4

LEI Guilin, ZHENG Mei, DONG Wei, ZHOU Zhixiang, DONG Qi. Test on electrothermal anti-icing of aero-engine inlet strut[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(8): 121066-121066.

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Test on electrothermal anti-icing of aero-engine inlet strut

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