TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS

摘要

A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils (74) circumferentially spaced about the rotor hub. Each of the airfoils (74) include pressure and suction sides (P,S) between a leading edge (82) and a trailing edge (84) and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip (80). Facing pressure and suction sides (P,S) of adjacent airfoils (74) define a channel (96) in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils (74). The width at each pressure side location along the channel (96) is defined as a minimum distance to a location along the suction side. The width diverges without converging along the channel (96) for at least some of the span positions.