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测量了低展弦比高负荷涡轮直叶片和正、反弯叶片叶栅端壁和叶片表面静压及流道内损失沿流向的发展，并对端壁和叶片吸力面上的流动进行了墨迹显示。实验结果表明：叶片正弯增大了叶栅进口段逆压梯度，并在叶片吸力面前部形成反“Ｃ”型静压等值线，加剧了叶片前缘的鞍点分离和吸力面分离线向叶栅中部的收敛。叶片反弯减小了叶栅进口段逆压梯度，在吸力面进口形成垂直于端壁的静压等值线，不仅削弱了鞍点分离，而且造成吸力面上的自由涡层型分离，避免了吸力面上、下分离线相交，因此二次旋涡损失大为降低。
The development of low aspect ratio high load turbine straight vane and positive and negative vane cascade endwall and blade surface static pressure and loss along the flow path was measured. The ink flow on the suction side of the end wall and the blade was measured. The experimental results show that the positive curvature of the blade increases the reverse pressure gradient at the inlet of the cascade and forms a reversed “C” hydrostatic contour in front of the blade suction surface, which aggravates the separation of the saddle point and the suction surface separation line Convergence in the middle of the cascade. The anti-bending of the blade reduces the reverse pressure gradient of the inlet section of the cascade and forms a hydrostatic contour perpendicular to the end wall at the suction surface, which not only weakens the separation of the saddle point but also causes the free vortex-type separation on the suction surface to be avoided The suction surface intersects the upper and lower separation lines, so the secondary vortex loss is greatly reduced.