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US 2019/0323453 A1Published application
Tail cone apparatus and methods for reducing nozzle surface temperatures
AssigneeThe Boeing Company
InventorsChad M. Winkler, Andrew J. Dorgan
Life of this patent
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Abstract
Tail cone apparatus and methods for reducing nozzle surface temperatures of aircraft engines are disclosed. An example apparatus includes a tail cone to be coupled to an aircraft engine. The tail cone includes a central axis, a cone section, and a plurality of fins. The fins are spaced about the central axis and extend outwardly from an outer surface of the cone section.
Claims20
An apparatus, comprising:
- a tail cone to be coupled to an aircraft engine, the tail cone having a central axis, a cone section, and a plurality of fins, the fins being spaced about the central axis and extending outwardly from an outer surface of the cone section.
An aircraft engine, comprising:
- a tail cone having a central axis, a cone section, and a plurality of fins, the fins being spaced about the central axis and extending outwardly from an outer surface of the cone section.
A method for reducing a temperature of a nozzle surface of a compartment of an aircraft engine, the method comprising:
- disrupting a vortex to be formed in the compartment of the aircraft engine, the compartment being located rearward of a tail cone of the aircraft engine, the tail cone having a central axis, a cone section, and a plurality of fins, the fins being spaced about the central axis and extending outwardly from an outer surface of the cone section, the disrupting of the vortex occurring via the fins, the disrupting of the vortex reducing the temperature of the nozzle surface.
Dependencies are inferred from the claim text.