涡轮叶尖复合蜂窝角度参数优化研究

Qingguo Kong, Jiaxin Ning, Xiaopeng Sun, Xiande Pan, Shuang Sun, Lehan Lu, Haixu Si
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摘要

为了减少高压涡轮机因叶尖漏流造成的二次流损失,本研究对复合蜂窝叶尖的设计进行了实验和数值检验。利用径向基函数和遗传算法定义并优化了复合蜂窝的排列角度。利用 CFX 18.0 模拟了间隙为 2.128 毫米的高压涡轮叶片的叶尖流场,并优化了复合蜂窝的排列角度,以获得更低的损耗。此外,还在低速级联试验设备中测试了扁平叶尖、基本蜂窝叶尖和优化蜂窝叶尖。结果表明,蜂窝结构空腔引起的涡流和径向速度增加了泄漏流的动能损失,降低了泄漏流速。与基本蜂窝相比,优化蜂窝通过降低叶尖横向压力梯度,对叶尖泄漏流具有补充阻挡作用。优化蜂窝还改变了叶尖间隙中泄漏流的出口角,减少了泄漏涡流,总压力损失进一步降低了 2.5%。
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A study of angle parametric optimization of the composite honeycomb on turbine blade tip
To reduce the secondary flow loss of the high-pressure turbine caused by the tip leakage flow, the design of the composite honeycomb tip has been experimentally and numerically examined in this study. The arrangement angle of the composite honeycomb is defined and optimized using the radial basis function and genetic algorithm. The tip flow field of the high-pressure turbine blade with a 2.128 mm clearance is simulated by CFX 18.0, and the arrangement angle of the composite honeycomb is optimized to obtain a lower loss. Moreover, the flat tip, basic honeycomb tip, and optimized honeycomb tip are tested in a low-speed cascade test facility. The results show that the vortices and radial velocity induced by the honeycomb structure cavity increase the kinetic energy loss of the leakage flow and reduce the leakage flow rate. Compared with the basic honeycomb, the optimized honeycomb has a supplemental blocking effect on the tip leakage flow by reducing the crosswise pressure gradient in the blade tip. The optimized honeycomb also changes the outlet angle of the leakage flow in the tip clearance, reduces the leakage vortex, and the total pressure loss is further reduced by 2.5%.
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