| 摘要 |
A method for assembling a turbine nozzle for a gas turbine engine. The method includes providing a turbine nozzle 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, providing at least one scalloped recessed area within the forward hook assembly at least one hook to facilitate reducing stresses induced to the turbine nozzle, and coupling the turbine nozzle into the gas turbine engine using the forward hook assembly such that the turbine nozzle is at least partially supported by the forward hook assembly.
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