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US 2016/0097290 A1Published application
Engine nacelle
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsRoy D. Fulayter, Crawford F. Smith
Life of this patent
Estimating the term…
Abstract
A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.
Claims20
A nacelle for a jet engine comprising
- an inner surface defining an opening for air to flow to an engine intake,
- an outer surface positioned external to the surface, and
- a leading surface circumscribing the opening, the leading surface connecting the inner surface and the outer surface, the leading surface defining a line of stagnation and formed to include a plurality of vortex generators positioned on leading surface along the line of stagnation.
A housing for a turbine engine comprising
- an opening directing a flow of air to the engine intake, the flow of air being generally parallel to the engine's axis of rotation,
- an outer surface, and
- a plurality of vortex generators, each vortex generator positioned on the outer surface at a position that is located on the stagnation line such that the vortex generator minimally changes the flowfield, the plurality of vortex generators positioned to disrupt a flow of air that has a direction that is perpendicular to the engine's axis of rotation.
A component for housing for a jet engine comprising
- a leading surface, and
- a plurality of vortex generators positioned on the leading surface to disrupt air flow across the leading surface in a direction that is not parallel to the direction of travel of the jet engine.
Dependencies are inferred from the claim text.