Compressor aerofoil

摘要

An aerofoil for a compressor comprising a suction surface and a pressure surface with a thickness distribution defined therebetween, the aerofoil further comprising a first local maximum in the thickness distribution and a second local maximum in the thickness distribution, the second local maximum being downstream of the first local maximum and the second local maxima being formed by a first region of concave curvature in the suction surface between the first and second local maxima, wherein the second local maximum is disposed such that in use a boundary layer upstream of the second local maximum on the suction surface is thinned by the second local maximum, and in addition the boundary layer may be sufficiently thinned so that an interaction of an upstream flow feature with the thinned boundary layer is capable of generating a turbulent spot with a calmed region downstream of the turbulent spot.

主权项

1. A turbine engine compressor aerofoil comprising a leading edge, a trailing edge, a suction surface and a pressure surface between the leading edge and the trailing edge, the aerofoil further comprising in a region of a span of the aerofoil a maximum thickness of the aerofoil between the leading edge and a midpoint of the aerofoil chord and a maximum thickness of the aerofoil between the midpoint of the aerofoil chord and the trailing edge, the maximum thickness of the aerofoil between the midpoint of the aerofoil chord and the trailing edge being downstream of the maximum thickness of the aerofoil between the leading edge and a midpoint of the aerofoil chord and a first region of concave curvature in the suction surface between the two maxima, wherein
the pressure surface has continuous concavity from the leading edge to at least 75% of the chord length, the aerofoil further comprises a second region of concave curvature in the suction surface, the second region of concave curvature being downstream of the maximum thickness of the aerofoil between the midpoint of the aerofoil chord and the trailing edge, the maximum thickness of the aerofoil between the midpoint of the aerofoil chord and the trailing edge immediately follows downstream of the maximum thickness of the aerofoil between the leading edge and a midpoint of the aerofoil chord, is disposed at a point in the rear third of the aerofoil chord, corresponds to a maximum thickness of the aerofoil, and is greater than a thickness of the maximum thickness of the aerofoil between the leading edge and the midpoint of the aerofoil chord.