Patent ID: 8231353
Filing Date: 2012-07-31
Classification: F01D,F05D,Y02T

Abstract:
1. A flow directing assembly for use in a compressor or a turbine of a turbine engine comprising: a plurality of circumferentially spaced blades, each of the blades including a radial projecting airfoil with a concave pressure side and a convex suction side that extend from a platform; and a plurality of flow passages, each of the flow passages defined by the airfoils of a neighboring pair of blades and an inner wall formed by an abutting pair of platforms of the neighboring pair of blades, the inner wall forming an inner radial boundary of the flow passage; wherein the inner wall of one or more of the flow passages comprises means for reducing frictional losses between a flow of working fluid through the turbine engine and the inner wall; wherein the means for reducing frictional losses comprises a non-axisymmetrical trough and a leading edge ridge positioned between the neighboring pair of airfoils; wherein each of the troughs is circumferentially positioned between the airfoils of the neighboring pair of blades; wherein each of the troughs extends from an area between leading edges of the airfoils to an area between trailing edges of the airfoils, each of the troughs comprising a leading edge portion positioned between the leading edges of the airfoils; and wherein each of the leading edge ridges comprises an elongated raised area that resides approximately between a forward area of the pressure side of the airfoil and the leading edge portion of each of the troughs.