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涡轮叶片前缘附近内冷腔的几何结构通常较为复杂,建立了梯形内冷通道的放大模型进行实验模拟,考虑复杂流动条件的影响,了解通道内的流动结构与特性,为更高效的内冷通道设计提供参考。使用七孔针对通道流场进行了详细测量,研究射流、横流及气膜孔出流对通道流场的影响规律。结果表明:在射流侧壁面较低位置的射流对靶面的冲击效果良好,较高位置的射流则主要对通道内旋流起到诱导和促进作用,且后者更易受横流影响;通道内横流强度的增加会进一步促进逆时针方向旋流的发展,同时削弱射流的冲击效果;随着射流角度的增加,射流的冲击作用增强,但诱导旋流的能力减弱;气膜出流量和出流位置的改变对通道主体流动结构影响较小。
The geometry of the internal cooling chamber near the leading edge of the turbine blade is usually complicated. An enlarged model of the trapezoidal internal cooling channel is set up to simulate the simulation. Considering the influence of complex flow conditions, the flow structure and characteristics in the channel are understood. Channel design for reference. A detailed measurement of the channel flow field was carried out using seven holes. The influence of jet flow, cross flow and film hole flow on the channel flow field was studied. The results show that the impinging jet at the lower side of the jet has a good effect on the target surface, while the jet at the higher position mainly induces and accelerates the swirling in the channel, and the latter is more likely to be influenced by the cross flow The increase of the strength will further promote the development of anti-clockwise swirling flow and weaken the impact of the jet. With the increase of the jet angle, the impact of the jet will be enhanced, but the induced swirling flow will be weakened. The change has little effect on the flow structure of the main channel.