END WALL CONFIGURATION FOR GAS TURBINE ENGINE

摘要

A contoured turbine airfoil assembly including an end wall (30a) formed by platforms (30) located circumferentially adjacent to each other, and a row of airfoils (34a, 34b) integrally joined to the end wall (30a) and spaced laterally apart to define flow passages (46) therebetween for channeling gases in an axial direction. A trough (62) is defined between a pressure side ridge (48) and a suction side ridge (58) located forward of each pair of airfoils (34a, 34b). Each trough (62) has a direction of elongation aligned to direct flow into the flow passage (46) centrally between each pair of airfoils (34a, 34b).

主权项

1. A contoured turbine airfoil assembly including:
an end wall formed by platforms located circumferentially adjacent to each other; a row of airfoils integrally joined to the end wall and spaced laterally apart to define flow passages therebetween for channeling gases in an axial direction; each of the airfoils including a concave pressure side and a laterally opposite convex suction side extending in a chordwise direction between opposite leading and trailing edges, the chordwise direction extending generally in the axial direction; and a pressure side ridge associated with each airfoil and defined by an elongated crest extending from a location forward of the mid-chord on the pressure side of an associated airfoil and extending to a location axially forward of the leading edges of the airfoils.