公开(公告)号：US20210381385A1

公开(公告)日：2021-12-09

申请号：US16892155

申请日：2020-06-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Repp ,  Bruce Reynolds ,  John Gunaraj ,  Dawn McNamee

IPC: F01D5/14

Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil extending in a spanwise direction from 0% span at a root to 100% span at a tip and having a leading edge and a trailing edge. The airfoil has a plurality of spanwise locations between the root and the tip each having a normalized local maximum thickness. A value of the normalized local maximum thickness decreases from the root to a minimum value and increases from the minimum value to the tip, and the minimum value is within 60% span to 90% span. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to a shaft or a fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and the fan.