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基于内外传热耦合原理,建立了热气防冰系统的AMESim仿真模型,研究热气防冰系统在不同引气状态下,管路流量、压力及蒙皮温度的变化规律.采用所建立的仿真方法,计算飞机机翼热气防冰系统的内部流动特性和内外耦合传热特性,将计算结果与热气防冰系统流量分配试验结果进行对比.结果表明:管路流量、压力和蒙皮温度的仿真计算结果与试验结果最大误差为9%,验证了该仿真模型的正确性.在此基础上,对飞机短舱热气防冰系统进行了仿真,分析了飞行包线下系统内外的换热、温度变化、加热效率等关键参数的瞬态特性.仿真结果为热气防冰系统的设计、分析与优化提供依据.
Based on the principle of internal and external heat transfer coupling, an AMESim simulation model of hot gas anti-icing system was established to study the variation law of flow, pressure and skin temperature of hot gas anti-icing system under different air-bleed conditions.Based on the established simulation method, The internal flow characteristics and internal and external coupling heat transfer characteristics of aircraft air-ice anti-icing system were calculated, and the results were compared with those of the hot-air anti-icing system. The results show that the simulation results of pipeline flow, pressure and skin temperature And the maximum error of the test results is 9%, which verifies the correctness of the simulation model.On the basis of this, the simulation of the anti-ice system for aircraft nacelles is carried out, and the heat exchange and temperature variation inside and outside the flight envelope are analyzed, Heating efficiency and other key parameters of the transient characteristics.The simulation results provide the basis for the design, analysis and optimization of the anti-ice system.