Methods and apparatus for assembling a gas turbine engine

Details Methods and apparatus for assembling a gas turbine engine Methods and apparatus for assembling a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

02

K

F02K 3/075 (2006.01) F02K 3/04 (2006.01)

Patent

CA 2519823

An airflow system for a gas turbine engine (12) is provided, wherein the gas turbine engine includes a core engine (20), an inner fan assembly (22), and a fladed fan assembly (24). The airflow system includes a plurality of airflow ducts for channeling airflow through the engine, wherein the airflow ducts include an inner fan duct (34) for channeling airflow through the inner fan assembly, a core engine duct (41) positioned downstream of, and in flow communication with, the inner fan duct, wherein the core engine duct facilitates channeling airflow through the core engine, a bypass fan duct (42) positioned downstream of, and in flow communication with, the inner fan duct, wherein the bypass fan duct facilitates channeling the airflow around the core engine duct, a flade duct (44) surrounding the inner fan duct and the bypass fan duct, wherein the flade duct facilitates channeling airflow through the fladed fan assembly, and a ram duct (60) surrounding an upstream portion (50) of the flade duct. The airflow system also includes a plurality of control valves (160, 162) for controlling the airflow through the engine.

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