Methods and apparatus for assembling turbine engines

A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane a...

Full description

Saved in:
Bibliographic Details
Main Authors Lee, Ching-Pang, Guentert, Joseph M, Lu, Wenfeng, Iles, Mitchell E
Format Patent
LanguageEnglish
Published 12.07.2011
Online AccessGet full text

Cover

More Information
Summary:A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.