机翼热气防冰流量分配模型设计及试验验证方法

Design and experimental verification method of flow distribution model of wing bleed air anti-icing

我国正在开展大型客机机翼热气防冰系统研制任务,自主知识产权的机翼热气防冰系统设计还未投入运营。首先从机翼热气防冰管路设计的原理出发,依据笛形管的流量分配计算方法,建立了管路仿真的SIMULINK模型,对不同工况下笛形管的压力、温度、管内流量分布等特性进行了分析。随后,搭建了一套机翼热气防冰地面流量分配试验台架系统,通过实际工程试验获得了笛形管压降和温降分布数据。试验结果表明当供气流量相同,入口温度越高,在笛形管段的沿程压力和温度就越高,压降变化明显,而在笛形管后段温降较小。当入口温度相同,供气流量越小,在笛形管的沿程压力和温度就越低,沿程压降变化较小,而在笛形管后段温降较大。最后,将试验结果和模型计算数据进行对比分析,进一步验证了模型计算正确性。搭建的机翼热气防冰地面流量分配试验平台可为机翼热气防冰系统优化设计提供借鉴。

China is carrying out the research and development of bleed air anti-icing system of a large civil aircraft wing,and the design of the system with independent intellectual property rights has not yet been put into operation.In this paper,based on the design principle of bleed air anti-icing system of an aircraft wing,according to the flow distribution calculation method of the piccolo,the SIMULINK model of the pipeline simulation was established,and the pressure,temperature,flow distribution in the pipe of the piccolo under different working conditions were analyzed.Subsequently,this paper established a set of test bench system for ground flow distribution,and obtained the pressure drop and temperature drop distribution data of the piccolo through actual engineering tests.The experimental results show that when the bleed air flow is the same,the higher the inlet temperature is,the higher the pressure and temperature along the piccolo section are,and the pressure drop changes significantly,while the temperature drop in the rear section of the piccolo section is small.When the inlet temperature is the same,the smaller the bleed air flow is,the lower the pressure and temperature along the piccolo section are,the pressure drop changes smaller,and the temperature drop in the rear section of the piccolo is greater.Finally,this paper compares and analyzes the test results with the model calculation data,and further verifies the correctness of the model calculation.The test platform for the flow distribution of bleed air anti-icing system of aircraft wing on the ground built in this paper can provide a reference for the optimization design of bleed air anti-icing system of aircraft wing.