Abstract
Compared with a straight blade, a unique compressor blade integrated forward-swept and positive curved stacking line is studied experimentally. Aerodynamic parameters of the two cascades are measured by a five hole probe at different positions and ink trace flow visualization is conducted on blade surfaces. The result shows that the swept curved cascade has lower endw all loss and higher midspan loss as compared with the straight cascade. However, lower loss is accompanied with lower diffusion factor. Opposite' C' shape static pressure distribution is established on the suction surface of the swept curved blade, which is helpful for avoiding the accumulation of low energy fluid in the endw all corner region. Anyhow the studies support the conclusion that the swept-curved blade conduces to not only the reduction of overall loss but also the improvement of stable operation in the endw all corner region.
Published Version
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