微型涡喷发动机传热效应的建模分析与实验研究

 微型涡轮发动机(MTE)可作为各种新型无人机、微小型导弹的高速推进动力装置，但微型化可能给发动机各部件匹配工作带来包括传热效应在内的特殊影响。针对微型涡轮发动机MTE-110，建立了基于发动机部件特性的总体性能模型，并在此基础上分析了可能的传热效应对压气机特性及整机性能的影响。在MTE-110的地面台架运转试验中，测量数据显示传热效应使压气机的实际温升比绝热温升增加了30%，对压比影响不大，因此显著降低了压气机效率。通过在压气机静子上采用隔热技术后，MTE性能得到显著改善，设计转速下的实测推力提高了23%，达到了96 N。

Modeling Analysis and Experimental Study on Heat Transfer Effect in Micro Turbine Engine

Micro turbine engine(MTE) can be used as effective high-speed propulsion system for miniature UAVs and missiles,but some new problems such as the heat transfer will affect the performance of MTE.Based on the modeling of a MTE,MTE-110,the heat transfer from micro combustion chamber to micro compressor was analyzed and the effects of both performances of compressor and whole engine were obtained.In the MTE-110 running tests on ground-stand,the measurements data showed that the heat transfer brought more temperature-rise of compressor about 30% than adiabatic one,but almost did not affect the pressure ratio.Experimental results show that the heat-proof treatment to the stator of compressor can improve the engine performance greatly.The measured thrust of improved micro engine increased by 23% and reach 96 N.