Effect of airfoil probe head on transonic turbine cascade flow field
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摘要:
为探究叶型探针头部对跨声速涡轮叶栅流场的影响，采用数值模拟的方法，对叶片前缘的不同叶高位置处装有探头的跨声速涡轮叶栅流场进行了研究。分析了不同攻角下叶片负荷性能变化、流场的旋涡结构、流动损失以及探针的适用性。结果表明：叶型探针头部影响了叶片加载性能，且影响效果受气流攻角的变化明显。气流绕过探针头部后形成较长的流向涡结构。在大的正攻角下叶片吸力面出现附着涡层，该附着涡层是带有探针的叶片负荷性能下降的主要因素。叶型探针对叶栅通道各位置造成的损失占比沿流向逐渐减小，大攻角下叶型探针使栅后流场损失增加7.4%。安装在展向不同位置处的探针都能在整个可调进气攻角范围内具有较好的适用性。
Abstract:In order to investigate the effects of airfoil probe head on the transonic flow field, a numerical simulation was performed in the transonic turbine cascade with airfoil probes installed at the different heights of blade’s leading edge. The variations of blade’s load performance, vortex structure, flow loss and applicability of probes with different incidence angles were analyzed. The results indicated that the airfoil probe’s head affected the loading performance of the blade, and the effect was quite sensitive to the flow incidence angles. A long streamwise vortex induced by the probe head was formed. And an attached vortex layer appeared on the suction surface of the blade at a large positive incidence angle. This attached vortex layer was the main factor for the decline of the load performance of the blade with the airfoil probes. The proportion of flow loss contributed by probes at each slice of the cascade passage decreased gradually along the flow direction. Compared with original cascade, the flow loss behind the cascade increased by 7.4% at high incidence angle. The probes installed at different positions in the spanwise direction had good applicability in the whole range of adjustable incidence angle.
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Key words:
- airfoil probe /
- transonic turbine cascade /
- incidence angle /
- blade load performance /
- secondary flow /
- flow loss
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图 4 叶片中径位置处静压系数分布（α= 0°）
Figure 4. Static pressure coefficient distribution at midspan of the blade （α= 0°）
图 5 叶片中径位置处静压系数分布（α= −10°）
Figure 5. Static pressure coefficient distribution at midspan of the blade （α= −10°）
图 6 叶片中径位置处静压系数分布（α=10°）
Figure 6. Static pressure coefficient distribution at midspan of the blade (α=10°)
图 7 不同攻角下叶栅流场轴向压力梯度和马赫数分布云图（左：无探针；右：有探针）
Figure 7. Distributions of axial pressure gradient and Mach number in cascade flow field at different incidence angels （left: without probe; right: with probe）
图 8 叶栅端壁流场旋涡结构 （α=0°，Qnond =100）
Figure 8. Vortex structure of secondary flow in cascade endwall （α= 0°, Qnond =100）
图 9 叶栅端壁流场旋涡结构 （α=10°，Qnond =100）
Figure 9. Vortex structure of secondary flow in cascade endwall （α=10°，Qnond =100）
图 10 叶片吸力面极限流线（α=10°）
Figure 10. Limiting streamlines of blade suction surface （α=10°）
图 11 叶栅通道特征面示意图
Figure 11. Schematic diagram of characteristic plane of cascade passage
图 12 叶栅通道各特征截面马赫数与二次流总压损失分布（α=10°）
Figure 12. Distributions of Mach number and total pressure loss of secondary flow on characteristic planes of cascade passage （α =10°）
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