Patent ID: 7758306
Filing Date: 2010-07-20
Classification: F01D,Y02T,Y10T

Abstract:
1. A method for assembling a gas turbine engine, said method comprising: coupling at least one stator assembly within the turbine engine, wherein the at least one stator assembly includes at least one stator vane extending from an inner band within the gas turbine engine, wherein the stator vane extends in a first plane from a root portion radially outward to a tip portion and extends in a second plane between a leading edge and a trailing edge, and wherein the stator vane includes at least two lean directional changes defined between the root portion and the tip portion; and coupling at least one turbine blade assembly within the turbine engine, wherein the turbine blade assembly includes at least one rotor blade in flow communication with the stator assembly such that an axial spacing is defined between the rotor blade and at least one of the leading edge of the stator vane and the trailing edge of the stator vane, wherein the axial spacing defined at one of the lean directional changes is wider than the axial spacing defined at the root portion.