Patent ID: 9709070
Date: 2017-07-18
CPC Classifications: B23K,F01D,F02K,F04D,F05D,Y10T

Claim:
1. A fan for a turbofan gas turbine engine, the fan defining a fan centerline and comprising a rotor hub and a plurality of fan blades adapted to rotate about the fan centerline, the fan blades extending radially from the rotor hub to outer tips thereof, the fan blades circumferentially spaced apart about the rotor hub in a single axial blade row, each of the fan blades having a leading edge, a hub radius (R HUB ) and a tip radius (R TIP ), wherein the hub radius (R HUB ) is the radius of the leading edge at the hub relative to the fan centerline, and the tip radius (R TIP ) is the radius of the leading edge at the outer tip relative to the fan centerline, and wherein the ratio of the hub radius to the tip radius (R HUB /R TIP ) is less than 0.29.