吸气式旋转爆震发动机进气段流动特性研究

doi:10.7527/S1000-6893.2024.30732

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吸气式旋转爆震发动机进气段流动特性研究

李冬¹,梁国柱²,凌文辉³,张义宁⁴,孟皓¹

1. 北京动力机械研究所
2. 北京航空航天大学
3. 南京航空航天大学
4. 北京机械动力研究所

收稿日期:2024-05-24 修回日期:2024-07-18 出版日期:2024-07-23 发布日期:2024-07-23
通讯作者: 梁国柱

Inlet flow characteristics analysis of air-breathing rotating detonation engine

Received:2024-05-24 Revised:2024-07-18 Online:2024-07-23 Published:2024-07-23
Contact: Guozhu LIANG

摘要/Abstract

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，分析了运动激波的构型特征、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12000rad/s和时均压力比19.1不变，峰值压力在0.5~1MPa范围时，出口平均总压损失在43%~46%范围；保持角频率12000rad/s和峰值压力比49.5不变，时均压力由0.22MPa增至0.32MPa，出口平均总压损失由52%降至40%，相比于定常反压下的总压损失大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距，进气段的流动损失更大且激波影响位置更靠近上游。

关键词: 吸气式, 非定常, 脉动反压, 进气段, 运动激波, 流动损失

Abstract: In order to analyze the influence of unsteady pulsating high pressure in the air-breathing rotating detonation engine combustor on the flow characteristics of inlet and guide the design of the inlet, the spatio-spatial characteristics of the pressure in the outlet section of inlet were considered, the propagation process and flow characteristics of moving shock wave in the inlet were simulated by adopting three-dimensional unsteady numerical simulation method. The configuration characteristics, propagation velocity, pressure and other key parameters of the moving shock wave were analyzed, the flow loss was obtained, and the influence of the angular frequency, peak and time-average values of the pulsating back pressure on the flow characteristics was obtained. The moving shock wave leads to the flow characteristics of low-pressure airflow pressurization and deceleration and high-pressure airflow decompression and acceleration in the inlet, and compared with the steady back pressure condition, the influence boundary of pulsating back pressure is more upstream; the higher the frequency, the longer the circumferential length, the more times the flow passes through the shock wave, however, the average total pressure loss of outlet at different frequencies basically remains unchanged; the time average pressure ratio are kept constant at 12000rad/s and 19.1, respectively, when the pressure peak value ranges from 0.5MPa to 1Mpa, the average total pressure loss of the outlet varies from 43% to 46%; the angular frequency and peak pressure ratio are kept constant at 12000rad/s and 49.5, respectively, when the time-average pressure increases from 0.22MPa to 0.32MPa, the average total pressure loss of the outlet decreases from 52% to 40%, compared with the steady back pressure condition, the total pressure loss is 2%~8% larger. The results show that the unsteady pulsating back pressure leads to the big differences between the flow characteristics of the air-breathing rotating detonation engine inlet and the traditional engine inlet, the flow loss is larger, and the influence boundary of shock wave is closer to the upstream.

Key words: air-breathing mode, unsteady flow, pulsating back pressure, inlet, moving shock wave, flow loss

李冬梁国柱凌文辉张义宁孟皓. 吸气式旋转爆震发动机进气段流动特性研究[J]. 航空学报, doi: 10.7527/S1000-6893.2024.30732.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

吸气式旋转爆震发动机进气段流动特性研究

Inlet flow characteristics analysis of air-breathing rotating detonation engine

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