航空发动机支板热滑油防冰性能试验

doi:10.7527/S1000-6893.2013.0466

Abstract

Abstract:

An test study on the performance of a hot lubrication oil anti-icing system of an aero-engine strut in an icing tunnel is conducted. The test model is a full-scale inlet strut of a turboshaft engine. In the test, the hot lubrication oil is heated by an electric heater. The temperature and mass flow of the lubrication oil are controlled by a programmable logic controller (PLC) system. The temperature distributions on the strut surface are measured by thermocouples. The icing environment parameters in the icing tunnel for the turboshaft engine strut are: the total temperatures of the free stream are -5℃ and -10℃, the velocity of the free stream is 40 m/s; the liquid water content is 0.5 g/m³ and 1.0 g/m³; the median volumetric diameter of the super-cooled water droplet is 20 μm. The surface temperatures of the strut and the ice shapes accreted on the strut are measured and photographed. The ice shapes are obtained when the capacity of the anti-icing system is insufficient. The characteristics of the hot lubrication oil anti-icing system are also studied under icing conditions.

Key words: hot lubrication oil, icing, anti-icing, icing tunnel, anti-icing test, engine strut

CLC Number:

V211.3

DONG Wei, ZHU Jianjun, ZHOU Zhixiang, DONG Qi. Test on Performance of an Aero-engine Strut Hot Lubrication Oil Anti-icing System[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(7): 1845-1853.

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Test on Performance of an Aero-engine Strut Hot Lubrication Oil Anti-icing System

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