Patent ID: 9470093
Filing Date: 2016-10-18
CPC Classification: F01D,F02C,F04D,F05D,Y02T

Claim Text:
1. A fan section for a gas turbine engine comprising: a rotor hub defining an axis; an array of airfoils circumferentially spaced about the rotor hub, each of the airfoils including pressure and suction sides between a leading edge and a trailing edge 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, facing pressure and suction sides of adjacent airfoils defining a channel in a chordwise direction and having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils; wherein the width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, the width diverging without converging along the channel for each of the span positions; and wherein each of the array of airfoils has a solidity defined by a ratio of an airfoil chord over a circumferential pitch, the solidity at the tip being less than or equal to about 1.2.