Abstract: A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine. The method also comprises coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas turbine engine upstream from the core engine turbine, and channeled to the auxiliary engine for generating power.

Abstract: A method for assembling a gas turbine engine includes mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine, wherein the exhaust nozzle includes a cowl and a primary nozzle coupled radially inward from the cowl, and coupling an infrared suppression system in flow communication with the engine exhaust nozzle to facilitate suppressing an exhaust infrared signature of the core engine, wherein the infrared suppression system includes a blocking fin having a substantially U-shaped cross-sectional profile and such that a cooling air flowpath is defined between the cowl and the blocking fin.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, and coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine. In addition, the method also comprises coupling an infrared suppression system in flow communication with the engine exhaust nozzle for channeling exhaust gases discharged from said exhaust nozzle to facilitate suppressing an exhaust infrared signature of the core engine during operation, wherein the infrared suppression system includes an access door and a flow channel that is coupled to the access door such that the flow channel is movable with the access door from a closed position to an open position.

Abstract: A gas turbine engine assembly includes at least one propelling gas turbine engine and an auxiliary engine used for generating power. The propelling gas turbine engine includes a fan assembly and a core engine downstream from said fan assembly. The core engine includes a compressor, a high pressure turbine, a low pressure turbine, and a booster turbine coupled together in serial-flow arrangement such that the booster turbine is rotatably coupled between the high and low pressure turbines. The auxiliary engine includes at least one turbine and an inlet. The inlet is upstream from the high pressure turbine and is in flow communication with the propelling gas turbine engine core engine, such that a portion of airflow entering the propelling engine is extracted for use by the auxiliary engine.