Patent ID: 6435815
Filing Date: 2002-08-20
Classification: F01D,F04D,F05D,Y10S

Abstract:
An aerofoil for an axial flow turbo machine, the aerofoil having a span, a leading edge, a trailing edge and a cambered sectional profile comprising a pressure surface and a suction surface extending between the leading edge and trailing edge, at least one aerofoil cross bleed passage being defined in the aerofoil, the passage extending from the pressure surface through the aerofoil to the suction surface, said one passage having an end, said end of said one passage adjacent the suction surface being disposed generally at a location on the suction surface at which, in use, boundary layer separation from the suction surface would normally occur, said portion of the passage adjacent to the suction surface being at an angle of less than 20 degrees to the suction surface.