초록 ▼

A method for assembling a gas turbine engine includes providing a core engine, an inner fan assembly, and a fladed fan assembly, coupling a plurality of airflow ducts to the engine including an inner fan duct for channeling airflow through the inner fan assembly, a core engine duct for channeling ai

A method for assembling a gas turbine engine includes providing a core engine, an inner fan assembly, and a fladed fan assembly, coupling a plurality of airflow ducts to the engine including an inner fan duct for channeling airflow through the inner fan assembly, a core engine duct for channeling airflow through the core engine, a bypass fan duct for channeling the airflow around the core engine duct, a flade duct for channeling airflow through the fladed fan assembly, and a ram duct surrounding an upstream portion of the flade duct, and coupling a plurality of control valves to the engine to control an amount of airflow channeled through each of the ducts using the plurality of control valves.

대표청구항 ▼

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: providing a core engine, an inner fan assembly, and a fladed fan assembly; coupling a plurality of airflow ducts to the engine including an inner fan duct for channeling airflow through the inner fan assemb

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: providing a core engine, an inner fan assembly, and a fladed fan assembly; coupling a plurality of airflow ducts to the engine including an inner fan duct for channeling airflow through the inner fan assembly, a core engine duct for channeling airflow through the core engine, a bypass fan duct for channeling the airflow around the core engine duct, a flade duct for channeling airflow through the fladed fan assembly, and a ram duct surrounding an upstream portion of the flade duct; and coupling a plurality of control valves to the engine to control an amount of airflow channeled through each of the ducts using the plurality of control valves. 2. A method in accordance with claim 1 wherein coupling a plurality of control valves comprises coupling a plurality of mode selector valves to the engine that are selectively positionable in one of an open position, an intermediate position, and a closed position. 3. A method in accordance with claim 1 wherein coupling a plurality of control valves comprises coupling an inner mode selector valve and an outer mode selector valve to the engine such that: when positioned in an open position, the inner mode selector valve controls airflow between the inner fan duct and the bypass duct; and the outer mode selector valve controls airflow between an upstream portion and a downstream portion of the flade duct; when positioned in an intermediate position, the inner and outer mode selector valves control the airflow entering the ram duct to be channeled into at least one of the flade duct and the bypass duct; and when positioned in a closed position, the inner and outer mode selector valves control the airflow between the ram duct and at least one of the flade duct and the bypass duct. 4. A method in accordance with claim 1 wherein coupling a plurality of control valves comprises coupling a front closure system to the engine including a plurality of closing flaps positioned upstream of the inner fan duct and the flade stream, wherein the closing flaps are positionable in one of an open position, an intermediate position, and a closed position to control an amount of airflow channeled into each of the ducts. 5. A method in accordance with claim 1 wherein coupling a plurality of airflow ducts further comprises: coupling an auxiliary duct in flow communication with the ram duct; and coupling a thermal management system valve in the auxiliary duct, wherein the thermal management system includes a heat exchanger that is coupled in flow communication between the ram duct and the auxiliary duct, and is coupled in flow communication to at least one of the inner fan duct and the flade duct. 6. An airflow system for a gas turbine engine, wherein the gas turbine engine includes a core engine, an inner fan assembly, and a fladed fan assembly, said airflow system comprising: a plurality of airflow ducts for channeling airflow through the engine, said airflow ducts comprise: an inner fan duct for channeling airflow through the inner fan assembly; a core engine duct positioned downstream of, and in flow communication with, the inner fan duct, said core engine duct for channeling airflow through the core engine; a bypass fan duct positioned downstream of, and in flow communication with, the inner fan duct, said bypass fan duct for channeling the airflow around said core engine duct; a flade duct surrounding said inner fan duct and said bypass fan duct, said flade duct for channeling airflow through the fladed fan assembly; and a ram duct surrounding an upstream portion of said flade duct; and a plurality of control valves for controlling the airflow through the engine. 7. An airflow system in accordance with claim 6 wherein said flade duct is configured to capture at least a portion of airflow channeled around said inner fan duct, said ram duct is configured to capture at least a portion of airflow channeled around said flade duct. 8. An airflow system in accordance with claim 6 wherein said bypass duct comprises a forward bypass duct positioned downstream from said inner fan duct, an intermediate bypass duct positioned between said forward bypass duct and said core engine duct, and an aft bypass duct, said plurality of control valves comprise an inner mode selector valve and an outer mode selector valve, said inner mode selector valve for controlling airflow in said forward bypass duct such that, when said inner mode selector valve is in a closed position, airflow is restricted between said inner fan duct and said aft bypass duct, said outer mode selector valve for controlling airflow in said flade duct such that, when said outer mode selector valve is in a closed position, airflow is restricted between an upstream end and a downstream end of said flade duct. 9. An airflow system in accordance with claim 6 wherein said plurality of control valves comprise an inner mode selector valve and an outer mode selector valve, said inner mode selector valve for controlling airflow between said inner fan duct and said bypass duct such that, when said inner mode selector valve is in a closed position, said ram duct is in flow communication with said bypass duct, said outer mode selector valve for controlling airflow in said flade duct such that, when said outer mode selector valve is in a closed position, said ram duct is in flow communication with said flade duct. 10. An airflow system in accordance with claim 6 wherein said plurality of control valves comprise at least one closing flap positioned upstream from said inner fan duct and said flade duct, said closing flaps moveable between an open position and a closed position, said closing flaps for controlling an amount of airflow entering said inner fan duct and said flade duct. 11. An airflow system in accordance with claim 6 wherein said plurality of control valves comprise a rear closure system positioned proximate a downstream end of said core engine, said rear closure system comprising a plurality of closing flaps for controlling an amount of airflow exiting said core engine duct. 12. An airflow system in accordance with claim 6 further comprising a thermal management system for controlling a temperature of airflow channeled through the engine, and an auxiliary duct coupled in flow communication with said ram duct for channeling a portion of airflow from said ram duct to an upstream end of at least one of said inner fan duct and said flade duct. 13. A gas turbine engine comprising: a core engine comprising an inner fan duct for channeling airflow through a portion of said core engine, and at least one inner fan section a plurality of fan blades coupled in flow communication with said inner fan duct; a flade system comprising a flade duct surrounding said core engine and comprising at least one fladed fan coupled in flow communication with said flade duct, said fladed fan comprising a plurality of fladed fan blades radially outward of, and coupled to, said inner fan section such that said fladed fan blades are driven by said inner fan section; and a ram duct system comprising a ram duct surrounding a portion of said flade system, and a plurality of mode selector valves for controlling airflow between said ram jet and at least one of said flade duct and said inner fan duct. 14. A gas turbine engine in accordance with claim 13 wherein said flade duct is configured to capture at least a portion of airflow channeled around said inner fan duct, said ram duct is configured to capture at least a portion of airflow channeled around said flade duct. 15. A gas turbine engine in accordance with claim 13 wherein said mode selector valves are moveable between an open position, an intermediate position, and a closed position, wherein when said mode selector valves are in said open position, air is channeled through said core engine and said flade system, when said mode selector valves are in said intermediate position, at least a portion of airflow is channeled through said ram duct into at least one of said flade duct and said inner fan duct, and when said mode selector valves are in said closed position said core engine is shut down. 16. A gas turbine engine in accordance with claim 13 further comprising a front closure system comprising a plurality of closing flaps for restricting airflow into said inner fan duct and said flade duct, said front closure system operable between an open position and a closed position to facilitate controlling an amount of airflow entering said inner fan duct and said flade duct. 17. A gas turbine engine in accordance with claim 13 wherein said ram duct system comprises a thermal management system coupled in flow communication with said ram duct, said thermal management system comprises an auxiliary duct for channeling a portion of airflow into said ram duct and a heat exchanger for cooling airflow in said auxiliary duct, said auxiliary duct coupled in flow communication with at least one of said flade duct and said inner fan duct. 18. A gas turbine engine in accordance with claim 17 further comprising a thermal management system valve for controlling an amount of airflow entering said auxiliary duct, and a front closure system for controlling an amount of airflow entering said inner fan duct and said flade duct, said thermal management system and said front closure system cooperating with one another to facilitate maintaining engine operating temperatures. 19. A gas turbine engine in accordance with claim 13 further comprising a flade stream augmentor positioned proximate a downstream end of said flade duct, said flade stream augmentor facilitates increasing the thrust of said engine. 20. A gas turbine engine in accordance with claim 13 further comprising an exhaust nozzle assembly positioned downstream of and in flow communication with said core engine, said flade system, and said ram duct system.