Methods and apparatus for assembling gas turbine engines

Abstract

A method is provided for operating a gas turbine engine including a core engine having a core stream duct, an inner bypass duct, an outer bypass duct, and a nozzle assembly downstream of the core engine and including a core engine nozzle and a bypass nozzle separated by a liner. The method includes channeling a first airflow discharged from the core gas turbine engine to the core engine nozzle, and channeling a second airflow through the inner bypass duct such that the second airflow bypasses the core gas turbine engine. The second airflow is channeled to a plurality of fairings that are positioned upstream from a plurality of support struts coupled to the nozzle assembly liner. The method also includes channeling a third airflow through the outer bypass duct such that the third airflow bypasses the core gas turbine engine, wherein the third airflow is channeled through the support struts to the bypass nozzle.

Dependencies are inferred from the claim text.