| 摘要 |
A vane for a gas turbine engine has an aerofoil of unconventional shape. The stacking of sections which defines the aerofoil is arranged to produce an aerofoil whose concave flank is convex in spanwise sections and whose convex flank is concave in spanwise sections. In order to reduce the problems produced by the resulting shape of trailing edge the sections are stacked so that all their trailing edges lie in a plane substantially parallel with the plane of the throat formed between the trailing edge and the next adjacent vane in an array.
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