Patent ID: 7144221
Filing Date: 2006-12-05
Classification: F01D,F02C,Y02T

Abstract:
1. A method for assembling a gas turbine engine, said method comprises: coupling a plurality of rows of fan blades in a row to a rotor disk, wherein each fan blade includes an airfoil having a first sidewall and a second sidewall connected together at a leading edge and a trailing edge, and wherein each airfoil extends radially between a root and a tip; coupling at least one shroud to at least one of the plurality of rows of fan blades, such that the shroud is coupled to at least one fan blade tip extending within the same row of fan blades; coupling at least a first row of rotor blades and a second row of rotor blades to the shroud, such that the rotor blades extend radially outward from the shroud, and wherein each rotor blade includes an airfoil having a first sidewall and a second sidewall connected together at a leading edge and a trailing edge; and positioning the first row of rotor blades upstream of the second row of rotor blades.