Patent ID: 7762761
Filing Date: 2010-07-27
Classification: F01D,F05D,Y02T

Abstract:
1. A method for assembling a turbine nozzle segment for a gas turbine engine, said method comprising: providing a turbine nozzle segment including a plurality of airfoil vanes extending between an inner band and an outer band, wherein the outer band includes a forward hook assembly having a rail and at least one hook that extends substantially axially outwardly from the rail; providing at least one scalloped recessed area within the forward hook assembly and the at least one hook, the at least one scalloped recessed area extending towards the inner band to facilitate reducing stresses induced to the turbine nozzle segment; and coupling a seal assembly to the forward hook assembly to at least partially overlap the at least one scalloped recessed area such that a flow of fluid through the at least one scalloped recessed area is facilitated to be restricted.