Effects of inlet distortion and non-axisymmetric endwall modeling on performance of compact compressor intermediate duct
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摘要:
为掌握畸变进气下非轴对称端壁造型对大径向落差长度比紧凑型压气机中介机匣气动特性的影响机制，采用数值模拟方法研究了畸变进气条件下中介机匣的流动特性，并进一步探索了轮毂非轴对称端壁造型对中介机匣内部流动结构和节流特性的影响。结果显示：进气畸变下中介机匣出口流场高总压损失与畸变主要来源于轮毂表面附面层分离产生的旋流和支板角区分离的共同作用。采用提出的基于三角函数的非轴对称端壁造型方法可有效消除轮毂表面的分离螺旋节点和支板角区分离，使中介机匣性能得到明显提升，总压损失系数降低约11.4%，且畸变进气下轮毂端壁造型对中介机匣节流特性的影响规律与均匀进气不同。
Abstract:To obtain the influence mechanism of non-axisymmetric endwall contouring (NAEC) on the aerodynamic characteristic of a compressor intermediate duct (CID) with large radius change to length ratio under inlet distortion, on the basis of investigating the flow characteristic under inlet distortion, the effects of hub NAEC on the internal flow structure and throttling characteristic of the CID were further explored with numerical method. The results showed that the high total pressure loss and the outlet flow distortion of the CID under inlet distortion were mainly caused by the combined action of the swirl generated by the hub boundary layer separation and the strut corner separation. The proposed NAEC method based on trigonometric function can effectively eliminate the spiral separation nodes on the hub and the strut corner separation, which improved the CID performance significantly, and the total pressure loss coefficient decreased by about 11.4%. In addition, the influence of NAEC on the throttling characteristic of the CID under inlet distortion was different from that of clear inlet condition.
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Key words:
- compressor /
- intermediate duct /
- inlet distortion /
- endwall contouring /
- throttle characteristic
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图 2 紧凑型压气机中介机匣示意图
Figure 2. Schematic diagram of the compact compressor intermediate duct
图 5 端壁造型波动函数示意图
Figure 5. Schematic diagrams of the wave functions of endwall contouring
图 7 不同进气条件下原型中介机匣出口截面总压恢复系数分布
Figure 7. Exit total pressure recovery coefficient for the datum design at different inlet flow conditions
图 8 不同进气条件下原型中介机匣轮毂表面极限流线分布
Figure 8. Limiting streamlines distribution on the hub for the datum design at different inlet flow conditions
图 9 节点s1和s2附近空间流线及3个不同截面总压恢复系数分布
Figure 9. 3D streamlines around nodes of s1, s2 and total pressure recovery coefficient distribution on three slices
图 10 不同进气条件下原型中介机匣支板表面极限流线分布
Figure 10. Limiting streamlines distribution on the strut surface at different inlet flow conditions
图 11 端壁造型后中介机匣出口的总压恢复系数分布
Figure 11. Total pressure recovery coefficient on the exit plane for the contoured design
图 12 畸变进气条件下端壁造型后支板和轮毂表面极限流线分布
Figure 12. Limiting streamlines distribution on the strut surface and hub at the inlet distortion condition
图 13 不同进气条件下端壁造型前后中介机匣总压恢复系数-相对流量特性
Figure 13. Characteristic map (total pressure recovery coefficient to relative flow rate) before and after contouring at different inlet flow conditions
图 14 不同工作点和进气条件下原型中介机匣出口截面总压恢复系数分布
Figure 14. Total pressure recovery coefficient distribution on the exit plane for the datum design at different working and inlet flow conditions
图 15 近最大流量点下通道中部子午面马赫数云图
Figure 15. Contours of Mach number on the meridional plane in the middle of the passage for the datum design at the near-maximum flow rate condition
图 16 近最大流量点原型中介机匣轮毂表面极限流线
Figure 16. Limiting streamlines on the hub for the datum design at the near-maximum flow condition
图 17 近最大流量点原型中介机匣支板表面极限流线
Figure 17. Strut surface limiting streamlines for the datum design at the near-maximum flow condition
图 18 近最大流量点下端壁造型后中介机匣轮毂表面极限流线
Figure 18. Limiting streamlines on the hub at the near-maximum flow condition after contouring
表 1 压气机中介机匣的主要特征几何参数
Table 1. Main geometric parameters of the compressor intermediate duct
参数 数值 径向落差长度比（∆R/L） 0.71 进出口面积比 （Ain/Aout） 1.0 支板最大厚度与弦长比（t/c） 0.225 支板倾角αs/（°） 25 
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