Patent ID: 6884030
Filing Date: 2005-04-26
Classification: F01D,F05B,F05D,Y10T

Abstract:
1. A method for securing a nozzle assembly within a turbine engine, the nozzle assembly including at least one nozzle, the nozzle having an airfoil including a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity is defined within the airfoil, the airfoil extending between an inner band and an outer band, said method comprising: extending at least one member through at least one of a plurality of cooling chambers defined within the cooling cavity of the airfoil, and at least one of the inner band and the outer band; and securing the nozzle assembly in position with at least one fastener such that the at least one member is coupled adjacent to at least one of the inner band and the outer band.