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为了掌握航空发动机进口支板结冰规律和热气防冰规律,利用冰风洞对进口支板进行了热气防冰试验、融冰试验和结冰试验.试验研究结果表明:进口支板所需热气流量随来流风速增加而增大,随来流总温增加而降低;结冰主要出现在在进口支板前缘区域并且滞止点附近的结冰最厚;进口支板表面初始温度较高,下降速度较慢,容易出现透明冰;来流温度低,进口支板表面温度下降较快,容易出现霜冰.试验结果为进口支板防冰设计计算提供了依据并为航空发动机防冰系统设计提供了一定的参考和借鉴.
In order to grasp the icing rules of the aero-engine inlet branch and the rule of hot gas anti-icing, hot ice anti-icing test, ice melting test and icing test were carried out on the inlet support plate by means of ice-wind tunnel.The experimental results show that the hot gas The flow rate increased with the increase of the flow velocity and decreased with the increase of the total temperature of the flow. The icing occurred mainly in the leading edge of the inlet support and the thickest icing near the stagnation point. The initial temperature of the inlet support surface was higher, The descending speed is slow, and the transparent ice is easy to appear; the flow temperature is low, the temperature of the inlet support surface drops rapidly and the frost is easy to appear.The test results provide the basis for the anti-ice design of the inlet support and the design of anti-ice system for the aircraft engine Provide some reference and reference.