Methods and apparatus for assembling a gas turbine engine
AssigneeGeneral Electric Company
InventorJames Edward Johnson
Life of this patent
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Abstract
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.
Claims20
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.
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.
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.
Dependencies are inferred from the claim text.