Effect of end-slot based on the incoming flow momentum on the corner separation of compressor cascade
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摘要:
为控制压气机叶栅中的角区分离现象，以某高亚声速压气机叶栅为对象，通过参数化研究设计了一种基于来流动量的叶根开槽叶栅，并探究了其流动控制机理与低叶栅稠度下的自适应能力。结果表明：开槽叶栅能有效抑制角区分离，尤其对正攻角下的角区失速流动控制效果显著，降低总压损失的同时也提高了叶片整体的负荷和扩压能力。然而，对于不同的分离形态其控制机理不同，在弱角区分离形态下，主要通过消除集中脱落涡从而减少了0%～25%叶高的总压损失，而对于角区失速形态，由于吸力面分离涡的削弱，显著降低了0%～40%叶高的总压损失。此外，与设计稠度（1.82）相比，更低的稠度下开槽叶栅的性能收益进一步提升。对于稠度为1.33时的开槽叶栅，全攻角范围内的总压损失平均降低29.53%，静压系数平均提高26.06%。因此，在不降低叶栅性能前提下，叶根开槽叶栅可进一步减小叶栅设计稠度，对提高航空发动机的推质比具有极大潜力。
Abstract:To control the corner separation in subsonic compressor cascade, an incoming flow momentum-based slotted cascade was designed through parametric study, and its flow control mechanism and adaptive capabilities under low cascade solidity were investigated. The results showed that the slotted cascade can effectively inhibit the corner separation. Especially the control effect was remarkable on the corner stall at the positive incidence angles. In addition to reducing the total pressure loss, the overall blade load and diffusion capacity were also improved. However, the control mechanisms of the slotted cascade varied for different separation forms. For the weak corner separation form, the total pressure loss within 0%—25% blade span was reduced mainly by eliminating the concentrated shedding vortex, while for the corner stall form the total pressure loss within 0%—40% blade span was greatly reduced due to the weakening of the separation vortex near the blade suction surface. Moreover, compared with the slotted cascade at the design solidity (1.82), the performance gain of the slotted cascade with a lower solidity was further enhanced. For a slotted cascade with the solidity of 1.33, its total pressure loss was reduced by an average of 29.53% and the static pressure rise coefficient was increased by an average of 26.06% within the range of full incidence angles. Therefore, the design solidity can be further reduced for an end-slotted cascade without reducing the cascade performance, indicating that the end-slotted cascade had a significant potential to improve the thrust-to-weight ratio of aero-engines.
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Key words:
- compressor cascade /
- corner separation /
- corner stall /
- cascade solidity /
- vortex structure
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图 10 0°与6°攻角下不同叶栅编号的总压损失系数
Figure 10. Total pressure loss coefficient of different cascade schemes under the incidence angles of 0° and 6°
图 11 6°攻角下原型叶栅和不同槽道宽度的开槽叶栅在7.5%叶高处的马赫数云图
Figure 11. Mach number contours at 7.5% blade span for the original and slotted cascades with different slot widths under the incidence angle of 6°
图 13 原型叶栅与开槽叶栅的总压损失系数和静压系数攻角特性图
Figure 13. Coefficients of total pressure loss and static pressure for the original cascade and slotted cascade at different incidence angles
图 14 $ {0}{\text{°} } $和$ {6}{\text{°} } $攻角下原型叶栅和开槽叶栅的端壁流线图
Figure 14. Endwall limiting streamlines for the original and slotted cascades under the incidence angles of 0° and 6°
图 15 0°和6°攻角下原型叶栅和开槽叶栅的吸力面流线图
Figure 15. Limiting streamlines of suction surface for the original and slotted cascades under the incidence angles of 0° and 6°
图 16 0°攻角下原型叶栅与开槽叶栅三维流线和涡结构图
Figure 16. 3D streamline and vortex structures of the original and slotted cascades under the incidence angle of 0°
图 17 6°攻角下原型叶栅与开槽叶栅三维流线和涡结构图
Figure 17. 3D streamline and vortex structures of the original and slotted cascades under the incidence angle of 6°
图 18 0°和6°攻角下原型叶栅与开槽叶栅在分析平面处的总压损失云图与涡量图
Figure 18. ω and vorticity contours of the original and slotted cascades under the incidence angles of 0° and 6° on the analysis plane
图 19 原型叶栅与开槽叶栅的周向平均总压损失系数沿展向的分布图
Figure 19. Spanwise distribution of pitch-averaged ω for original cascade and slotted cascade
图 20 0°和 6°攻角下7.5%叶高位置处叶片表面静压系数与负荷沿相对弦长的分布图
Figure 20. Distribution of $ {C}_{{\mathrm{p}}} $ and $ \Delta {C}_{{\mathrm{p}}} $ on blade surface along relative chord length at 7.5% h under the incidence angles of 0° and 6°
图 21 0°和 6°攻角下50%叶展位置处叶片表面静压系数沿相对弦长的分布图
Figure 21. Distribution of static pressure coefficient on blade surface along relative chord length at 50% blade span under the incidence angles of 0° and 6°
图 22 不同叶栅稠度下原型叶栅和开槽叶栅的总压损失系数与静压系数攻角特性图
Figure 22. Coefficients of total pressure loss and static pressure rise of the original cascade and slotted cascade at different incidence angles and cascade solidities
图 23 4°攻角下不同叶栅稠度叶片吸力面和端壁的极限流线与总压损失系数云图
Figure 23. Limiting streamlines on the blade surface and endwall together with the contours of total pressure loss coefficient at different solidities under the incidence angle of 4°
图 24 4°攻角下在7.5%叶高叶片表面的静压系数分布和负荷分布
Figure 24. Distributions of static pressure coefficient and load on the blade surfaces with different solidities at 7.5% blade span under the incidence angle of 4°
表 1 原型叶栅设计参数
Table 1. Design parameters of the original cascade
参数 数值 弦长 $ C $/mm 40 展向高度 $ H $/mm 52 周向长度 $ S $/mm 22 展弦比 $ h/S $ 1.3 叶栅稠度 $ \sigma $ 1.82 安装角 $ {\beta }_{s} $/（°） 22.5 弯角 $ \theta $/（°） 48 进口气流角$ {\beta }_{1} $/（°） 42 进口马赫数 $ M{a}_{1} $ 0.67 
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表 2 槽关键几何参数及其取值
Table 2. Key geometric parameters of the slot and their values
参数 参数值1 参数值2 参数值3 槽出口位置 55%Ca 65%Ca 75%Ca 槽高度 7.5%h 15%h 22.5%h 槽宽度 1.1%Ca 1.4%Ca 1.7%Ca
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表 3 控制变量表
Table 3. Table of controlled variable experiments
叶栅
编号影响因素与参数值 槽出口位置 槽高度 槽宽度 0（对照） 2（65%Ca） 2（15%h） 2（1.4%Ca） 1 1（55%Ca） 2（15% h） 2（1.4%Ca） 2 3（75%Ca） 2（15% h） 2（1.4%Ca） 3 2（65%Ca） 1（7.5% h） 2（1.4%Ca） 4 2（65%Ca） 3（22.5% h） 2（1.4%Ca） 5 2（65%Ca） 2（15% h） 1（1.1%Ca） 6 2（65%Ca） 2（15% h） 3（1.7%Ca）
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