Abstract:

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.

Key words: micro turbine engine, compressor, heat transfer, running test, modeling