Lorenz & Kopf, LLP
Characteristic distribution for rotor blade of booster rotor
A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil having a leading edge, a trailing edge and a mean camber line. The airfoil has a delta inlet blade angle defined as a difference between a local inlet blade angle defined in a spanwise location, and a root inlet blade angle defined at the root. The delta inlet blade angle decreases in the spanwise direction from the root to a minimum value at greater than 10% span and from the minimum value, the delta inlet blade angle increases to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft or the fan.
HONEYWELL INTERNATIONAL INC.
F F F F F Y F
F01D F05D F05D F05D F05D Y02T F05D
inventional additional additional additional additional additional additional
John John Nick Bruce
Gunaraj Repp Nolcheff Reynolds