Influence of aircraft wake distortion on performance of tail-installed boundary layer ingestion fan
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摘要:
附面层吞吸式飞机将推进系统布置在靠近机身表面的位置，吸入机身边界层气流与尾流作为推进工质，以降低二氧化碳排放和燃油消耗。但由于推进器受到进气畸变影响，可能导致其偏离设计工况、性能下降，制约该构型飞机的发展。因此通过数值仿真研究了STARC-ABL构型附面层吞吸飞机的机尾推进风扇受畸变影响时，性能的恶化情况。结果表明：飞机尾流具有速度分布不均匀以及湍流黏度比高两特征。风扇吸入尾流工作，增压比、等熵效率、稳定工作裕度均有明显下降。来流径向畸变影响气流流过转子时的气流转折角，改变风扇做功能力，使风扇增压比降低；来流周向畸变使风扇内部流动恶化，叶片通道内分离、激波增强，同时增压比和等熵效率下降。来流高湍流黏度比使得风扇内部气流掺混作用加强，流动损失增加，风扇增压比和等熵效率显著下降。
Abstract:Boundary Layer Ingestion (BLI) aircraft position their propulsion systems close to the fuselage surface to ingest the boundary layer airflow and wake as the propulsive working fluid, thereby reducing carbon dioxide emissions and fuel consumption. However, due to the influence of inflow distortion, the propulsor may deviate from its design operating conditions, resulting in performance degradation, which hinders the development of this aircraft configuration. Therefore, a numerical simulation was conducted to investigate the performance deterioration of the aft-mounted propulsive fan in the STARC-ABL configured BLI aircraft under distorted inflow conditions. The results show that the aircraft wake exhibits two key characteristics: non-uniform velocity distribution and a high turbulent viscosity ratio. When the fan operates by ingesting the wake, its pressure ratio, isentropic efficiency, and stability margin decrease significantly. Radial inflow distortion affects the airflow turning angle through the rotor, altering the fan’s work capacity and reducing its pressure ratio. Circumferential inflow distortion deteriorates the internal flow within the fan, intensifying flow separation and shock waves in the blade passages, which simultaneously reduces both the pressure ratio and isentropic efficiency. The high turbulent viscosity ratio of the incoming flow enhances internal flow mixing, increases flow losses, and leads to a notable decline in both the pressure ratio and isentropic efficiency of the fan.
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图 3 飞机流场计算结果随网格量变化情况
Figure 3. Aircraft flow field calculation results obtained through grids with different numbers of grid cells
图 4 风扇流场计算结果随网格量变化情况
Figure 4. Fan flow field calculation results as a function of mesh/grid size
图 11 附面层吞吸飞机机身周围湍流黏度比云图
Figure 11. Turbulent viscosity ratio contour map around fuselage of the boundary layer ingestion aircraft
图 12 机尾推进风扇吸入不同来流时的工作特性
Figure 12. Performance of tail-installed fan when ingesting different inflow
图 13 机尾风扇以
2000 r/min转速吸入不同来流时工作特性Figure 13. Performance of tail-installed fan at
2000 r/min when ingesting different inflow conditions
图 14 机尾风扇以
2000 r/min吸入不同来流工作特性沿径向分布Figure 14. Radial distribution of performance of tail-installed fan at
2000 r/min while ingesting different inflow conditions
图 15 机尾风扇转速为
2000 r/min工作吸入不同来流时转子叶片不同叶高位置压力分布Figure 15. Pressure distribution at various spanwise locations of the rotor blade for the aft fan operating at
2000 r/min while ingesting different inflow conditions
图 16 转子前相对气流角沿径向分布
Figure 16. Radial distribution of relative swirl angle at rotor leading edge
图 17 气流流过转子的相对气流转折角沿径向分布
Figure 17. Radial distribution of relative flow turning angle when passing through rotor
图 18 机尾风扇以2 000 r/min吸入均匀来流时不同叶高处马赫数云图
Figure 18. Contours of Mach number at different spanwise positions for tail-installed fan ingesting uniform inflow at 2 000 r/min
图 19 机尾风扇以2 000 r/min吸入畸变来流时不同叶高截面马赫数云图
Figure 19. Contours of Mach number at different spanwise positions for tail-installed fan ingesting distorted inflow at 2 000 r/min
图 20 机尾风扇以2 000 r/min吸入不同湍流黏度比来流的工作特性沿径向分布
Figure 20. Radial distribution of performance of tail-installed fan at 2 000 r/min while ingesting different turbulent viscosity ratios inflow conditions
图 21 机尾风扇以2 000 r/min吸入高湍流黏度比均匀来流时50%叶高截面相对马赫数云图
Figure 21. Contour of relative Mach numbers at 50% spanwise location cross-section when tail-installed fan ingests uniform inflow with high turbulent viscosity ratio at 2 000 r/min
图 22 机尾风扇以2 000 r/min吸入低湍流黏度比均匀来流时50%叶高截面熵云图
Figure 22. Entropy contour at 50% spanwise location cross-section when tail-installed fan ingesting uniform inflow with low turbulent viscosity ratio at 2 000 r/min
图 23 风扇以2 000 r/min吸入高湍流黏度比均匀来流时50%叶高截面熵云图
Figure 23. Entropy contour at 50% spanwise location cross-section when tail-installed fan ingesting uniform inflow with high turbulent viscosity ratio at 2 000 r/min
图 25 出口导叶总压恢复系数径向分布
Figure 25. Radial distribution of total pressure recovery coefficient of outlet guide vane
图 26 转子进口相对气流转折角径向分布
Figure 26. Radial distribution of relative flow turning angle upstream of the rotor
表 1 原型机尾风扇参数
Table 1. Origin tail-installed fan parameters
参数 数值 参数 数值 转速/（r/min） 1800 进口直径/ m 2.6 流量/（kg/s） 230 动叶叶片数 28 进口轮毂比 0.4667 出口导叶片数 47 转子叶尖间隙/mm 0.6 进口导叶片数 25 
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表 2 Stage 35压气机几何参数
Table 2. Geometric parameters of Stage 35
参数 数值 参数 数值 设计转速/（r/min） 17188.7 动叶叶片数 36 设计流量/（kg/s） 20.8 静叶叶片数 46 叶尖间隙/mm 0.408 进口轮毂比 0.7
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表 3 机尾风扇受尾流畸变影响性能的下降
Table 3. Performance degradation of the tail-installed fan due to the distortion of the wake
风扇转速/
（r/min）增压比
降低/%等熵效率
降低/%稳定裕度
降低/%1000 2.11 17.45 16.70 1300 2.12 7.50 5.21 1550 2.30 5.30 3.52 1750 2.47 4.47 3.01 2000 3.02 4.41 2.63
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表 4 机尾风扇以
2000 r/min转速吸入不同来流工作时实际工作点性能Table 4. Collective operating performance of the tail-installed fan at
2000 r/min when ingesting different inflow conditions来流情况 增压比 等熵效率 稳定裕度/% 均匀来流-低湍流黏度比 1.426 0.9368 4.8148 径向畸变-低湍流黏度比 1.411 0.9398 2.8079 真实畸变-低湍流黏度比 1.398 0.9271 1.3696 均匀来流-高湍流黏度比 1.410 0.9057 10.763 真实畸变-高湍流黏度比 1.386 0.8938 2.1510
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