Methods and apparatus for securing multi-piece nozzle assemblies

A nozzle assembly for a turbine engine, said nozzle assembly comprising:

• an outer band;
• an inner band;
• an airfoil having 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, said leading and trailing edge of said airfoil extending between said inner band and said outer band, said airfoil further comprising at least one spar extending between said pressure and suction sides for dividing said cooling cavity into at least two cooling chambers;
• and
• a member extending through said cooling cavity of said airfoil, and at least one of said inner band and said outer band, said member secured within said nozzle assembly with at least one fastener such that said member is coupled adjacent to at least one of said inner and outer band.

A turbine comprising:

• a nozzle assembly having a plurality of nozzles, each nozzle comprising:
• an outer band;
• an inner band;
• and
• an airfoil having 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, said leading and trailing edge of said airfoil extending between said inner band and said outer band, said airfoil further comprising at least one spar extending between said pressure and suction sides for dividing said cooling cavity into at least two cooling chambers;
• and
• a member extending through said cooling cavity of said airfoil, and at least one of said inner band and said outer band, said member secured within said nozzle assembly with at least one fastener such that said member is coupled adjacent to at least one of said inner and outer band.