某型航空涡轴发动机整机吞水性能试验

为进行某型航空涡轴发动机吞水试验,设计了喷水设备及专用进气整流装置,采用大小喷水环实现对发动机进行给定水流量的喷入.进行了发动机进口吞水量为空气流量2.5%和3.5%的试验,试验结果表明:试验方法及装置的设计合理可行;均匀吞水量不高于进气流量3.5%,发动机吞水时各截面温度下降量由进口至出口依次降低;吞水试验后,发动机性能下降. 

Swallowing water capability experiment of one turbine-shaft overall aviation engine

Waterworks and special air intake path were designed to conduct swallowing water experiments for one aviation turbine-shaft engine under research,while big and small rings were used to spurt certain quantity of water into the engine.The experiments were conducted at swallowing water in the quantity of 2.5% and 3.5% of engine's intake air.The results show that,the designs of the experiment method and device are feasible;when symmetrically swallowing water not higher than 3.5% of engine's intake air,the temperature drop at each engine's section decreases from the inlet to the exit;the engine's performance degrades after swallowing water experiments.