| 摘要 |
An airfoil array (60) for a gas turbine engine comprises a plurality of airfoils (62) spaced circumferentially apart from each other about an engine center axis. Each airfoil is associated with a platform (68a, 68b). An endwall (64) extends circumferentially about the engine center axis, and is defined by adjacent platforms (68a, 68b). Each pair of adjacent platforms (68a, 68b) are separated from each other by a gap (80). An endwall contour shape extends from a first location on one side of the gap to a second location on an opposite of the gap (80). The endwall contour shape is the same for all adjacent platforms (68a, 68b). |
