Patent ID: 8043063
Filing Date: 2011-10-25
Classification: F01D,F05D,Y10S

Abstract:
1. An integrally bladed rotor (IBR) for a gas turbine engine, comprises a hub and a circumferential row of blades projecting integrally from said hub, the row including an even number of blades alternating between blades having first and second airfoil definitions around the hub, each blade having a pressure side and a suction side disposed on opposed sides of a median axis and extending between a trailing edge and a leading edge, the first and second airfoil definitions being different and having respective pressure side thicknesses T 1 and T 2 defined between respective median axes and respective pressure sides of the blades, the pressure side thickness T 1 of the first airfoil definition being greater than the pressure side thickness T 2 of the second airfoil definition.