基于中等涵道比涡扇发动机结构及其气动稳定性特点,通过该类型某发动机高空压力畸变试验研究,获取了研究对象合理可行的高空压力畸变试验方案设计、畸变装置选取以及数据处理规范,结果表明：在飞行高度小于14 km范围内,飞行高度对稳态综合畸变指数有一定的影响,但影响不明显；有引气/功率分出136 kW条件下,飞行高度为11 km、飞行马赫数为0.8以及飞行高度为14 km、飞行马赫数为0.39时,该中等涵道比发动机最大巡航状态与最大爬升状态在进口综合畸变指数不大于12%时均能稳定工作。
Based on characterizations of the structure and aerodynamic stability, the experimental investigation on the inlet total pressure distortion of the middle-bypass ratio turbofan engine at high altitude was carried out. The detailed available distortion project designs, distortion installations selection, and data processing standard were introduced. The test results showed that within the range of flight height less than 14 km, the height affected the steady state comprehensive distortion index a little. When flight height was 11km, and flight Mach number was 0.8, under the comprehensive distortion index less greater than 12%, the middle-bypass ratio turbofan engine could work steadily at military cruising regime and military climbing regime with air bleeding, and power extractions was 136 kW, when the flight height was 14 km, and flight Mach number was 0.39.
彭生红,田金虎,刘冬根,田应维,邝文.中等涵道比涡扇发动机高空压力畸变试验[J].航空动力学报,2019,34(6):1273~1251. Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude[J]. Journal Of Aerospace Power,2019,34(6):1273-1251.复制