为分析微型涡喷发动机核心机部件工作特性和整机热力性能，在发动机主要站位布置了温度和压强传感器，通过稳态试车试验测量工质热力状态参数，结合转速、流量等工作性能参数分别开展部件及整机热力性能计算。研究表明，燃烧室传热造成压气机效率下降，而散热损失和排气离速损失是影响微型涡喷发动机整机热效率的主要因素。在紧凑型涡喷发动机中，直流式燃烧室对涡轮工作有不利影响，进行优化设计时应予以重点考虑。

In order to analyze the working characteristics of the core components and the thermal performance of the microturbojet engine in centimeter size,the steady state run test was carried out.Temperature and pressure sensors were arranged at the main stations of the engine to measure the thermodynamic parameters,combined with the working performance parameters such as rotational speed and mass flow rate to carry out the thermal performance analysis of the components and the whole machine.It shows that,heat transferred from the combustor leads to the decrease of compressor efficiency,and the losses of heat dissipation and exhaust velocity are the main factors affecting the overall thermal efficiency of the engine.For a compact turbojet engine,the directflow combustor has adverse effect on the turbine operation,which should be taken into consideration during optimization.

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国家自然科学基金委员会与中国民用航空局联合基金（U163313）；中央高校基本科研业务费资助项目（3122019187）