高负荷压气机叶栅采用附面层抽吸的实验研究
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摘要
现代高性能叶轮机械的发展对压气机的负荷提出了越来越高的要求,而负荷的增大将导致附面层增厚、气流阻塞、高损失范围增大等不利影响,因此在提高叶片负荷的同时,抑制或消除附面层分离,降低叶栅的损失,对提高压气机的负荷、减小端部损失、提高压气机效率、增加稳定工作范围意义重大。而附面层吸除技术是一种非常有效的解决手段。
本文实验以低速平面叶栅风洞为平台,设计并加工了叶片吸力面上不同弦向位置的吸气槽,以及进行吸气和调节吸气量的设备,同时构建了实验台测量和数据采集系统。在不同吸气量(进口流量的0.5%、1.0%和1.5%)和吸气位置(轴向弦长的25%、35%、48%和60%)等条件下,测试了高负荷压气机叶栅在设计冲角下的气动性能。对实验结果进行后处理,得到了测量面上的总压损失系数、二次流矢量、节距平均总压损失系数、叶栅出口节距平均气流角、型面静压系数等重要参数的分布规律。同时还采用墨迹显示方法研究了叶栅端壁和叶片表面的气流流动状况。
研究结果表明,附面层吸除技术能够有效减弱吸力面的附面层分离、减小角区分离的强度和范围,减小损失,增加叶片负荷并提高气流折转能力,显著改善大转角压气机叶栅气动性能,随吸气量增加,吸力面角区低能流体积聚减弱,阻塞作用减轻,负荷增加,气流落后角减小,且在附面层分离充分发展的位置,采用大吸气量可以得到更明显的改善效果;附面层抽吸对通道涡核心的位置影响较小,却能降低其强度和尺寸,吸气位置位于分离点附近时,吸气对通道涡的抑制效果明显增强;叶片吸力面开全叶高槽进行附面层抽吸对端部气动性能影响较小,叶展中部流动的改善是导致整个叶栅损失下降的主要原因,在分离线后、通道涡尚未充分发展而远离壁面的位置进行抽吸,可明显减小端区的损失;最佳吸气量与吸气位置的布置有关,当吸气位置在原型分离起始位置及其上游位置时,流动并未发生分离或分离程度很小,低能流体相对较少,采用吸力面吸气只能延缓通道涡的发展,在较小的吸气量下即得到了该吸气位置的最佳效果,继续增加吸气量还会对主流区流动产生干扰,导致叶栅气动性能不随吸气量增大而得到更大改善,当吸气位置位于分离刚刚发生的区域时,虽然吸除部分附面层流体减轻了吸气位置后的分离流动,但是由于此时端壁附面层和通道涡已得到较充分的发展,积聚了大量的低能流体,且距离吸力面的横向位置逐渐拉大,必须采用较大的吸气量才能实现较好的抽吸效果,因此对应的最佳吸气量较大,对流场的改善也更为显著。可见,吸气位置的选取对于附面层在压气机中的影响尤为重要。
The development of turbomachine with high performance requires highly-loaded compressor system. However, this leads to boundary layer thickening in compressor cascade, resulting in flow blockage and increase in energy loss. So finding an effective way to reduce or even eliminate the boundary layer separation and thus reduce the energy loss will benefit the increase in blade loading, and the improvment of the compressor performance. Boundary layer suction technology was adopted in this paper to reduce the flow separation in the highly-loaded compressor cascade.
First, the compressor blades with suction slot as well as the instrument used to control the suction flow rate were designed. Then the data acquisition system was set up. At last, the effects of boundary layer suction on the performance of the compressor cascade under different suction slot locations (25%, 35%, 48% and 60% of the axial chord) and suction flow rates (0.5%, 1.0% and 1.5% of the inlet mass flow rate) were studied. The total loss coefficient, secondary flow vectors, pitch-average total loss coefficient and spanwise outlet flow angle were calculated.
The results show that investigation presents, compared to conventional cascade, the boundary layer suction can restrain the separated flow, improve the condition of flow on the endwall corner, reduce the loss, increase blade loading and the capability of diffusion. With the appropriate suction and suction flow rate, the compressor performance should be further improved. The boundary layer suction can decrease the strength and size of passage vortex rather than its position. The more downstream suction location is, the effect is more obvious; Boundary layer suction at the suction surface controls the wake effectively and reduces the loss at the midspan of the flow passage remarkably in all the cases studied in this paper. And the endwall loss reduction is visually only when the suction location is placed at where the boundary layer deviates but is not too far from the blade surface; the optimal suction flow rate relates to suction location. When the slot is before the initial separation location, flow separation degree is very small and there is little of low energy fluid. The boundary layer suction can delay the development of passage vortex. It can make best effect with small suction flow rate in this slot. As the suction flow rate rises, more low-energy fluid is removed from the flow passage, so the aerodynamic performance of cascade doesn’t improve with the increment of suction flow rate. When the slot is located into the separation region where the endwall boundary layer and passage vortex have developed fully, a lot of low energy fluid accumulating in the suction corner and the slot is far from the leading edge of blades, so only larger suction flow rate can make a good result. It can be seen that, the suction slot is very important and must be cautious to select.
本文实验以低速平面叶栅风洞为平台,设计并加工了叶片吸力面上不同弦向位置的吸气槽,以及进行吸气和调节吸气量的设备,同时构建了实验台测量和数据采集系统。在不同吸气量(进口流量的0.5%、1.0%和1.5%)和吸气位置(轴向弦长的25%、35%、48%和60%)等条件下,测试了高负荷压气机叶栅在设计冲角下的气动性能。对实验结果进行后处理,得到了测量面上的总压损失系数、二次流矢量、节距平均总压损失系数、叶栅出口节距平均气流角、型面静压系数等重要参数的分布规律。同时还采用墨迹显示方法研究了叶栅端壁和叶片表面的气流流动状况。
研究结果表明,附面层吸除技术能够有效减弱吸力面的附面层分离、减小角区分离的强度和范围,减小损失,增加叶片负荷并提高气流折转能力,显著改善大转角压气机叶栅气动性能,随吸气量增加,吸力面角区低能流体积聚减弱,阻塞作用减轻,负荷增加,气流落后角减小,且在附面层分离充分发展的位置,采用大吸气量可以得到更明显的改善效果;附面层抽吸对通道涡核心的位置影响较小,却能降低其强度和尺寸,吸气位置位于分离点附近时,吸气对通道涡的抑制效果明显增强;叶片吸力面开全叶高槽进行附面层抽吸对端部气动性能影响较小,叶展中部流动的改善是导致整个叶栅损失下降的主要原因,在分离线后、通道涡尚未充分发展而远离壁面的位置进行抽吸,可明显减小端区的损失;最佳吸气量与吸气位置的布置有关,当吸气位置在原型分离起始位置及其上游位置时,流动并未发生分离或分离程度很小,低能流体相对较少,采用吸力面吸气只能延缓通道涡的发展,在较小的吸气量下即得到了该吸气位置的最佳效果,继续增加吸气量还会对主流区流动产生干扰,导致叶栅气动性能不随吸气量增大而得到更大改善,当吸气位置位于分离刚刚发生的区域时,虽然吸除部分附面层流体减轻了吸气位置后的分离流动,但是由于此时端壁附面层和通道涡已得到较充分的发展,积聚了大量的低能流体,且距离吸力面的横向位置逐渐拉大,必须采用较大的吸气量才能实现较好的抽吸效果,因此对应的最佳吸气量较大,对流场的改善也更为显著。可见,吸气位置的选取对于附面层在压气机中的影响尤为重要。
The development of turbomachine with high performance requires highly-loaded compressor system. However, this leads to boundary layer thickening in compressor cascade, resulting in flow blockage and increase in energy loss. So finding an effective way to reduce or even eliminate the boundary layer separation and thus reduce the energy loss will benefit the increase in blade loading, and the improvment of the compressor performance. Boundary layer suction technology was adopted in this paper to reduce the flow separation in the highly-loaded compressor cascade.
First, the compressor blades with suction slot as well as the instrument used to control the suction flow rate were designed. Then the data acquisition system was set up. At last, the effects of boundary layer suction on the performance of the compressor cascade under different suction slot locations (25%, 35%, 48% and 60% of the axial chord) and suction flow rates (0.5%, 1.0% and 1.5% of the inlet mass flow rate) were studied. The total loss coefficient, secondary flow vectors, pitch-average total loss coefficient and spanwise outlet flow angle were calculated.
The results show that investigation presents, compared to conventional cascade, the boundary layer suction can restrain the separated flow, improve the condition of flow on the endwall corner, reduce the loss, increase blade loading and the capability of diffusion. With the appropriate suction and suction flow rate, the compressor performance should be further improved. The boundary layer suction can decrease the strength and size of passage vortex rather than its position. The more downstream suction location is, the effect is more obvious; Boundary layer suction at the suction surface controls the wake effectively and reduces the loss at the midspan of the flow passage remarkably in all the cases studied in this paper. And the endwall loss reduction is visually only when the suction location is placed at where the boundary layer deviates but is not too far from the blade surface; the optimal suction flow rate relates to suction location. When the slot is before the initial separation location, flow separation degree is very small and there is little of low energy fluid. The boundary layer suction can delay the development of passage vortex. It can make best effect with small suction flow rate in this slot. As the suction flow rate rises, more low-energy fluid is removed from the flow passage, so the aerodynamic performance of cascade doesn’t improve with the increment of suction flow rate. When the slot is located into the separation region where the endwall boundary layer and passage vortex have developed fully, a lot of low energy fluid accumulating in the suction corner and the slot is far from the leading edge of blades, so only larger suction flow rate can make a good result. It can be seen that, the suction slot is very important and must be cautious to select.
引文
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