微型涡轮喷气发动机风车起动特性研究  

Study on Micro Turboengine Windmill Starting Characteristics

作　　者：万照云 

机构地区：[1]中国航发控制系统研究所,江苏无锡214063

出　　处：《航空发动机》2016年第6期30-35,共6页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：为研究微小型涡轮喷气发动机风车起动的特性,以某微型涡轮喷气发动机为原型,通过数值模拟和试验研究相结合的方法,研究了其风车起动过程的各种特性。通过试验研究了丙烷气点火时间和丙烷气压对微型涡喷发动机转速以及燃烧室温度的影响规律,以在最短时间内使得微型涡喷发动机转速和燃烧室温度满足可供油燃烧的条件,并确定所需要的丙烷气最小气量。结果表明:在本试验条件下发动机从起动到慢车状态过程中,以先快后慢的供油规律起动加速时间最短约为82 s;发动机从慢车到80%全转速状态过程中,实现相对最短加速时间的供油规律可分为2段,前段供油斜率较大为0.79,后段供油斜率较小为0.14。对其它结构形式和起动过程类似的微小型涡轮喷气发动机有一定借鉴作用。Based on a micro turbojet engine prototype and by the method of numerical simulation and experiment, the starting characteristics of micro turbojet engine windmilling were studied in this paper. Based on experiment, the influences of propane ignition time and propane pressure upon engine rotation speed and combustion chamber temperature were studied to meet the demand of combustion in the shortest possible time, as well as confirmed the minimum required propane. Further experiments show that in the experimental conditions of the engine from the start state to the idle state, the process to slow down after the oil law shortest start acceleration time can be about 82 s. Eighty percent of the engine from idle to full speed during the state to achieve the shortest relative acceleration time for oil law can be divided into two sections, the front slope of the larger oil supply is 0.79, while the final part slope of the smaller oil supply is 0.14. It can be well referenced by other micro turbojet engines which have similar structure and starting process.

关 键 词：微型发动机 风车起动 低速特性 点火特性 航空发动机 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]