某种热气射流式飞机防冰腔试验

Experimental Study on the Hot Air Jet Anti-Icer of Aircraft

某型飞机发动机进气道前缘利用引自发动机的热气进行防冰,防冰腔采用冲击射流加双蒙皮通道的结构。为验证该结构防冰腔是否满足要求,利用试验室现有条件,搭建小型直流式冰风洞,选取局部典型全尺寸防冰腔试验件进行冰风洞试验,在不同外部气流条件下和不同内部热气参数条件下,对防冰腔外蒙皮表面的温度分布进行测量,并根据试验结果对防冰腔的性能及影响因素进行分析和研究。研究结果表明,该结构防冰腔在现有发动机引气温度和压力条件下,满足防冰要求。

The hot air bleeding from engine was used for the certain engine inlet duct leading edge anti-icing system,the anti-icer made up of double skin with jet hole.The main research in this thesis are as following:According to the test requirement and equipment,an open-circuit icing wind tunnel was designed and constructed.The partial true size test models were manufactured,and then the performance test was carried up under different conditions of inside and outside.The test result indicated that this anti-icer could satisfy requirement of anti-icing.