Study on coupling mechanism between offset paired vortex distortion and fan
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摘要:
根据典型大S弯进气道出口偏置对涡畸变的速度、压力分布特征，利用涡团模型建立了一种偏置对涡边界条件定义方法，并进行数值模拟研究探索了偏置对涡畸变与风扇的耦合影响机理。研究结果表明：在风扇吸力作用下，上游畸变流掺混加强，切向速度增大。偏置对涡进气条件会使风扇性能下降，稳定裕度损失严重，其中在涡旋环量35 m2/s相斥对涡进气条件下风扇稳定裕度损失7.1%，相吸对涡进气条件下稳定裕度损失达到了7.9%。随着偏置对涡强度的增大，风扇性能下降更多，稳定裕度损失也更大。偏置对涡进气条件下风扇轴向速度损失以及切向预旋造成的风扇叶尖出现大范围大攻角区，造成风扇部分叶片通道压比较大，而风扇其余位置仍处于较低压比水平，导致近失速点附近风扇整体总压比下降，失速点提前。
Abstract:In accordance with the velocity and pressure distribution features of the offset paired vortex distortion at the exit of a typical large S-bend inlet, a method for defining the offset paired vortex boundary conditions was established by using a vortex model. The coupling effect mechanism between offset paired vortex distortion and fan was explored by carrying out numerical simulation research. From the research results, it indicated that the upstream distorted flow mixing was strengthened, and the tangential velocity increased under the suction effect of the fan. The condition of the offset paired vortex inlet caused the deterioration of fan performance, and a serious loss of stability margin. Among them, the loss of stability margin was 7.1% under the condition of mutual exclusion vortex with 35 m2/s vortex circulation, and 7.9% under the condition of mutual attraction vortex. As the strength of offset paired vortex increased, the fan performance deteriorated more, and the loss of stability margin was also greater. Under the condition of the offset paired vortex embodied in the large area of attack angle was caused by the axial speed loss and tangential pre-rotation of the fan blade tip. This caused a relatively high total pressure ratio in some blade channels of the fan, while the remaining positions of the fan were still at a relatively low total pressure ratio level, resulting in a decrease in the fan overall total pressure ratio near the stall point of the fan and an advance in the stall point.
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Key words:
- coupling mechanism /
- large S-bend inlet /
- inlet/engine matching /
- paired vortex distortion /
- vortex model /
- fan stall
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图 4 风扇总压比和总温比沿径向分布
Figure 4. Radial distribution of total pressure ratio and total temperature ratio of fan
图 10 对涡的总压云图和速度矢量场
Figure 10. Total pressure contours and velocity vectors of paired vortex
图 22 30%叶高处绝对轴向速度与切向速度周向分布曲线
Figure 22. Absolute axial and tangential velocity circumferential distribution curves at 30% span
图 23 95%叶高处绝对轴向速度与切向速度周向分布曲线
Figure 23. Absolute axial and tangential velocity circumferential distribution curves at 95% span
图 25 95%叶高处总压比周向分布曲线
Figure 25. Total pressure ratio circumferential distribution curves at 95% span
图 26 不同进气条件下风扇特性曲线
Figure 26. Fan characteristic curves under different inlet conditions
图 28 99%叶高处相对马赫数云图（相吸对涡）
Figure 28. Relative Mach number contours at 99% span （attraction）
图 29 99%叶高处相对马赫数云图（相斥对涡）
Figure 29. Relative Mach number contours at 99% span （exclusion）
图 31 85%叶高处进气攻角周向分布曲线
Figure 31. Circumferential distribution curves of inflow attack angle at 85% span
图 32 90%叶高处进气攻角周向分布曲线
Figure 32. Circumferential distribution curves of inflow attack angle at 90% span
表 1 Rotor 67设计参数
Table 1. Design parameters of rotor 67
参数 数值 参数 数值 叶片数 22 设计转速/（r/min） 16043 进口直径/mm 511.4 设计点流量/（kg/s） 33.25 出口直径/mm 485 设计压比 1.63 进口轮毂比 0.375 进口叶尖相对马赫数 1.38 出口轮毂比 0.487 设计点效率 0.92 叶尖间隙/mm 1.01 展弦比 1.56 
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表 2 涡团特征参数
Table 2. Vortex characteristic parameter
类型 涡核半径
rc/m轴向速度
损失系数
（A/z）/（m/s）涡旋环量
Γ0/（m2/s）相吸对涡 0.1 175 35 70 105 相斥对涡 0.1 175 35 70 105
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