Study on evolution mechanism and performance impact of swirl distortion in intake system of TBCC engine
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摘要:
为探究涡轮组合发动机中旋流畸变的产生规律及其对轴流压气机性能的影响，构建了进气道S弯扩压段-轴流压气机转子一体化模型，针对典型工况点开展数值仿真计算，详细分析了旋流畸变的产生机制与规律，研究了旋流畸变对压气机的性能影响。结果表明：超声速S弯进气道出口背压通过影响结尾激波位置，改变扩压段入口截面气流能量分布，从而影响旋流畸变的类型与强度：低背压时形成较强的对涡旋流，中背压时旋流很弱、流动近乎均匀，高背压时产生较强的整体涡旋流。在系统级计算中，高空均匀来流条件下，压气机在80%、90%及100%转速和不同出口静压工况下，气动交界面平均静压均低于进气道临界背压，进气道处于超临界状态，S弯扩压段入口能量呈对称分布，下游形成对涡旋流。在上述系统级计算工况下，与压气机单部件工作特性相比，各转速下的工作流量范围收窄，相同工作点下的压比和效率均降低，其中最高效率降低5.49%，最高效率点流量减少8.82%，稳定裕度下降57.82%。
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关键词:
- 涡轮基组合循环（TBCC）发动机 /
- 超声速S弯进气道 /
- 旋流畸变 /
- 进发匹配 /
- 气动稳定性
Abstract:To investigate the generation law of swirl distortion in a turbine combined engine and its influence on the performance of axial flow compressors, an integrated model of a supersonic inlet S-bend diffuser section and axial flow compressor rotor was constructed to carry out numerical simulation calculations under a typical operating condition. The generation mechanism and law of swirl distortion were analyzed in detail, and the influence of swirl distortion on the performance of the compressor system was studied. The results indicated that the back pressure at the outlet of the supersonic S-bend inlet influenced the terminal shock wave position, thereby changing the energy distribution of the airflow in the diffuser section and consequently affecting the type and intensity of swirl distortion. Specifically, a strong paired swirl formed at low back pressure; the flow became nearly uniform with very weak swirl at medium back pressure; and a strong bulk swirl was generated at high back pressure. For system-level calculations under high-altitude uniform inflow conditions, the average static pressure at the aerodynamic interface plane remained below the inlet’s critical back pressure at 80%, 90%, and 100% compressor speeds across various outlet static pressures. This indicated that the inlet operated in a supercritical state, resulting in a symmetric energy distribution at the S-bend diffuser inlet and the formation of a paired swirl downstream. Under the above system-level calculation conditions, the compressor exhibited a narrowed operating flow range across all rotational speeds, along with reductions in both pressure ratio and efficiency at identical operating points, compared with its isolated component performance. Specifically, the maximum efficiency of the compressor rotor decreased by 5.49%, the flow rate at the maximum efficiency point decreased by 8.82%, and the stability margin decreased by 57.82%.
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图 3 进气道S弯扩压段-压气机一体化模型计算域
Figure 3. Calculation domain of the integrated finite element model of the inlet S-bend diffuser and compressor
图 5 完整进气道-压气机转子一级转子一体化模型计算域
Figure 5. Computation domain of the entire inlet-compressor 1st rotor model
图 6 S弯扩压段出口旋流畸变情况对比
Figure 6. Comparison of the swirl at the S-duct outlet between two different models
图 14 压气机转子入口有无旋流畸变特性对比
Figure 14. Comparison of characteristics of swirl distortion at compressor rotor inlet
图 15 不同转速下AIP面质量加权平均静压随压气机出口压力的变化
Figure 15. Change of mass flow-weighted average static pressure at AIP with compressor outlet pressure at different speeds
图 18 100%转速下最高效率点测量面速度矢量及旋流角分布
Figure 18. Velocity vectors and swirl angles at 100% speed peak efficiency on each measuring plane
图 19 最高效率点测量面不同测环上的旋流角分布
Figure 19. Swirl angle at measuring rings on each measuring plane at peak efficiency
图 21 不同叶高处相对马赫数分布
Figure 21. Relative Mach number distribution at different blade heights
表 1 来流参数
Table 1. Inflow parameters
参数 数值 飞行高度/km 18 马赫数 3.2 当地静温$ {T}_{0} $/K 216.65 当地静压$ {p}_{0} $/kPa 7.21 
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表 2 旋流指标对比
Table 2. Comparison of swirl index
参数 模型 相对误差/% 完整进气道-压气机一体化模型 进气道S弯扩压段-压气机一体化模型 正旋流扇区/（°） 10.47 10.25 2.1 负旋流扇区/（°） −10.48 −10.27 2.0 旋流强度/（°） 10.43 10.22 2.0
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