Integrated gas turbine engine-nacelle
AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorsArthur P. Adamson, Donald F. Sargisson, Charles L. Stotler, Jr.
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Abstract
A nacelle for use with a gas turbine engine is provided with an integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine. The nacelle is entirely supported in its spacial relationship with the engine by means of the webbed structure. The inner surface of the nacelle defines the outer limits of the engine motive fluid flow annulus while the outer surface of the nacelle defines a steamlined envelope for the engine.
Claims6
An integrated propulsion system comprising:
- a pylon;
- a gas turbofan engine including a core engine for rotatably driving a fan stage to pressurize a motive fluid, a fan bypass flow annulus generally circumscribing said core engine, a core engine inlet duct communicating with said bypass duct, a flow splitter for separating the fan motive fluid into a bypass portion and a core engine portion, an integral composite frame having first and second generally concentric hoop means of bonded composite filament fabrication interconnected by generally radially extending outer struts of composite filament fabrication bonded thereto, said first hoop means substantially spanning said flow splitter and said second hoop means sandwiched between inner and outer walls of composite filament fabrication bonded thereto, said inner wall defining an outer aerodynamic contour of the turbofan engine, and wherein said inner wall, said outer wall and said second hoop means form a shroud entirely supported in spacial relationship with said first hoop means through said outer struts;
- and
- mounting means connecting said first hoop means to said pylon.
Dependencies are inferred from the claim text.