飞机发动机进气道防冰系统的设计计算

Design and calculation for the anti-icing system of an aircraft engine let

针对某型具有分流隔板的发动机进气道进行热气防冰腔和管路系统的设计,在进气道的水滴撞击特性计算的基础上,对防冰系统进行热力计算,包括防冰表面的温度分布和系统压降及系统管路的流量分配,由此验证防冰系统正常工作时能否满足对表面温度的要求.此外,还分析了供气温度、供气压力、供气流量以及限流环孔径对防冰表面温度分布的影响.分析发现表面温度随供气温度、供气流量的增加而升高,限流环孔径的变化对前缘表面温度几乎没有影响,分流隔板的表面温度随孔径的增大而升高.

A hot-air anti-icing system for an engine inlet was designed. The engine had a flow distribution plate. Based on the calculation of water droplets trajectories, thermal calculation was conducted for the anti-icing system, including the temperature profile of anti-icing surface, pipes pressure loss and flux distribution. The calculation was used to examine if the designed system would work well under the design condition. The influences of air temperature, flux and restrictor diameter on temperature distribution of anti-icing surface were analyzed. The results indicte that the surface temperature increases with the increasing of hot-air temperature and flux, and that the surface temperature of the flow distribution increases with the increasing of restrictor diameter, while the effect of it on leading edge surface temperature can be neglected.