脉冲爆震外涵加力分排涡扇发动机性能分析  

Performance Analysis of Separate-flow Turbofan Engine with Pulse Detonation Bypass Duct Afterburner

作　　者：彭辰旭 卢杰[1] 郑龙席[1] 郭欢 张佳博 PENG Chen-xu;LU Jie;ZHENG Long-xi;GUO Huan;ZHANG Jia-bo(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空发动机》2023年第2期37-44,共8页Aeroengine

摘　　要：为了研究外涵带脉冲爆震燃烧室分排涡扇发动机的性能,基于部件法建立了外涵装有脉冲爆震燃烧室(PDC)的分排涡扇发动机性能模型,分析了PDC工作参数、外涵循环参数和飞行工况对整机性能的影响。结果表明:PDC频率提高,PDC增压比和加力温度提高,发动机单位推力增大,耗油率升高;PDC当量比增大,PDC增压比和加力温度先提高后降低,发动机单位推力先增大后减小,耗油率一直升高;脉冲爆震外涵加力由于只利用外涵部分气流组织燃烧,耗油率远低于传统加力的,当PDC频率超过41 Hz时,脉冲爆震外涵加力发动机的单位推力大于传统加力涡扇发动机的;涵道比增大,参与爆震燃烧气流增多,发动机单位推力增大,耗油率升高。风扇压比提高,发动机单位推力先增大后减小,耗油率一直降低;在飞行高度一定时,飞行马赫数提高,发动机单位推力减小,耗油率升高;在飞行马赫数一定时,飞行高度增加,发动机单位推力先增大后略微减小,耗油率先降低后略微升高;在不同飞行工况下,脉冲爆震外涵加力发动机的耗油率远低于传统加力涡扇发动机的。In order to investigate the performance of a separate flow turbofan engine with Pulse Detonation Combustor(PDC)in the by⁃pass duct,the performance model was established based on performances from components.The effects of PDC operating parameters,by⁃pass cycle parameters,and flight conditions on the performance of the overall engine were analyzed.The results show that with the increase of PDC operating frequency,the pressure ratio and burner temperature of the PDC,the specific thrust and specific fuel consumption of the engine increase.With the increase of equivalence ratio,the pressure ratio and burner temperature of PDC increase first and then decrease,the specific thrust increases first and then decreases,and the specific fuel consumption increases continuously.Because only part of the by⁃pass air participates in detonation combustion,the specific fuel consumption of the turbofan engine with pulse detonation bypass duct after⁃burner is lower than that of the conventional afterburner turbofan engine.When the PDC operating frequency is greater than 41 Hz,the spe⁃cific thrust of the turbofan engine with pulse detonation bypass duct afterburner is greater than that of the conventional afterburner turbofan engine.With the increase of bypass ratio,the PDC gas flow increases,and the specific thrust and specific fuel consumption increase.With the increase of the fan pressure ratio,the specific thrust first increases and then decreases,and the specific fuel consumption decreases continuously.At a certain flight altitude,with the increase of flight Mach number,the specific thrust decreases,and the specific fuel con⁃sumption increases.At a certain flight Mach number,with the increase of flight altitude,the specific thrust increases first and then de⁃creases slightly,and the specific fuel consumption decreases first and then increases slightly.Under different flight conditions,the specif⁃ic fuel consumption of the turbofan engine with pulse detonation bypass duct afterburner is lower than that of the conve

关 键 词：脉冲爆震燃烧室 分排涡扇 外涵加力 整机性能 航空发动机 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]