Flow passage with elongated ridge for a gas turbine engine

摘要

Inefficiencies associated with the formation of horseshoe vortices in a gas turbine engine having a row of radially extending airfoils, are mitigated with an improved flow passage (85) defined by the suction and pressure surface (64,62) of two adjacent airfoils (60) and endwalls (75,80) disposed proximal to the radially inner and outer ends of the airfoils (60). The flow passage (85) includes a ridge (87) disposed in one of the endwalls (75,80) adjacent a suction surface (64) of one of the airfoils (60), the ridge (87) extending longitudinally from a location at or near the maximum circumferential extent of the airfoil suction side (64) to a downstream location proximal to the trailing edge of the suction surface (64).