吸气式旋转爆震发动机进气段流动特性  

Inlet flow characteristics analysis of air-breathing rotating detonation engine

作　　者：李冬 张义宁[2] 凌文辉[2] 梁国柱[1] 孟皓[2] LI Dong;ZHANG Yining;LING Wenhui;LIANG Guozhu;MENG Hao(School of Astronautics,Beihang University,Beijing 102206,China;Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]北京航空航天大学宇航学院,北京102206 [2]北京动力机械研究所,北京100074

出　　处：《航空学报》2025年第2期234-249,共16页Acta Aeronautica et Astronautica Sinica

基　　金：国家级项目。

摘　　要：为了分析吸气式旋转爆震发动机燃烧室内非定常高压脉动对进气段内流动特征的反向影响,指导进气段设计,考虑进气段出口压力的时空特征,采用三维非定常数值方法对进气段内的流动过程和运动激波传播过程进行了数值模拟。根据计算结果,分析了运动激波的形状特征、传播速度及压力等关键参数变化过程,得到了流动损失和进气段出口脉动反压的传播角频率、峰值以及时均值对流动特征的影响规律。运动激波作用导致进气段内呈现低压气流增压减速和高压气流减压加速的流动特征,相比于定常反压,脉动反压的影响边界更靠上游;角频率越高,则周向长度越长、振荡区域宽度越窄,气流经激波作用次数越多,但不同角频率下出口气流的平均总压损失基本维持不变;保持角频率12000 rad/s和时均压力比19.1不变,峰值压力在0.5~1 MPa时,出口平均总压损失在43%~46%;保持角频率12000 rad/s和峰值压力比49.5不变,时均压力由0.22 MPa增至0.32 MPa,出口平均总压损失由52%降至40%,相比于定常反压作用下的总压损失大2%~8%。研究表明:非定常脉动反压作用下吸气式旋转爆震发动机进气段内流动特征与传统进气段存在较大差异,进气段的流动损失更大且激波影响位置更靠近上游。The influence of unsteady pulsating high pressure in the air-breathing rotating detonation engine combustor on the flow characteristics of inlet is analyzed to guide the design of the inlet.The temporal-spatial characteristics of the pressure in the outlet section of inlet were considered,and the propagation process and flow characteristics of the moving shock wave in the inlet were simulated by adopting the three-dimensional unsteady numerical simulation method.The shape characteristics,propagation velocity,pressure and other key parameters of the moving shock wave were analyzed,and the flow loss and the influence of the angular frequency,peak and time-average values of the pulsating back pressure on the flow characteristics were obtained.It was found that the moving shock wave led to the flow characteristics of low-pressure airflow pressurization and deceleration and high-pressure airflow decompression and acceleration in the inlet.Compared with the steady back pressure condition,the influence boundary of pulsating back pressure was more upstream.The higher the angular frequency,the longer the circumferential length,the narrower the width of the oscillation region,the more times the flow passed through the shock wave;however,the average total pressure loss of the outlet at different angular frequencies basically remained unchanged.When the angular frequency and the time average pressure ratio were respectively kept constant at 12000 rad/s and 19.1 and the pressure peak value ranged from 0.5 to 1 Mpa,the average total pressure loss of the outlet varied from 43% to 46%.When the angular frequency and peak pressure ratio were respectively kept constant at 12000 rad/s and 49.5 and the time-average pressure increased from 0.22 to 0.32 MPa,the average total pressure loss of the outlet decreased from 52% to 40%.Compared with the steady back pressure condition,the total pressure loss was 2% to 8% larger.The results show that the unsteady pulsating back pressure leads to the big differences between the flow characteristi

关 键 词：吸气式 非定常 脉动反压 进气段 运动激波 流动损失 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]