An inlet for removal of a boundary layer from an incoming air flow of an engine is disclosed. The inlet includes at least one compression element proximate to an inlet aperture of the engine. The compression element is selectably moveable between a first position and a second position along an axis.
An inlet for removal of a boundary layer from an incoming air flow of an engine is disclosed. The inlet includes at least one compression element proximate to an inlet aperture of the engine. The compression element is selectably moveable between a first position and a second position along an axis. A boundary layer removal aperture is open when the compression element is in the first position and the boundary layer removal aperture is closed when the compression element is in the second position.
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1. An inlet for removal of a boundary layer from an incoming air flow of an engine, the inlet comprising: at least one compression element disposed between an inlet aperture of the engine and a compression ramp surrounded by the inlet aperture, the inlet aperture being positioned proximate to an ext
1. An inlet for removal of a boundary layer from an incoming air flow of an engine, the inlet comprising: at least one compression element disposed between an inlet aperture of the engine and a compression ramp surrounded by the inlet aperture, the inlet aperture being positioned proximate to an external surface of a vehicle, the compression ramp being disposed on a side of the inlet aperture adjacent to the external surface, the compression element selectably moveable relative to the compression ramp between a first position and a second position along an axis parallel to a direction of incoming air flow, wherein a boundary layer removal aperture is open when the compression element is in the first position and the boundary layer removal aperture is closed when the compression element is in the second position, and wherein the compression element is configured to move to at least one third position on the axis between the first and second position to provide a selectable amount of boundary layer removal. 2. The inlet of claim 1, wherein the inlet aperture is generally rectangular. 3. The inlet of claim 2, wherein the compression element comprises an aft compression ramp having a leading edge that is proximate to a trailing edge of the compression ramp, the aft compression ramp linearly movable between a first position and a second position along an axis parallel to the axis of motion of the compression ramp. 4. The inlet of claim 3, wherein the compression ramp and aft compression ramp are configured to move in unison to modify the compression of the incoming air at the inlet aperture and to move differentially to provide a selectable amount of boundary layer removal. 5. The inlet of claim 1, wherein: the inlet aperture is generally a half-ellipsoid; andthe compression ramp comprises a forward compression half-conical ellipsoid. 6. The inlet of claim 5, further comprising an aft compression truncated half-conical ellipsoid having a leading edge that is proximate to a trailing edge of the forward compression half-conical ellipsoid, the aft compression truncated half-conical ellipsoid linearly movable between a first position and a second position along an axis parallel to the axis of motion of the forward compression half-conical ellipsoid. 7. The inlet of claim 6, wherein the forward compression half-conical ellipsoid and the aft compression truncated half-conical ellipsoid are configured to move in unison to modify the compression of the incoming air at the inlet aperture and to move differentially to provide a selectable amount of boundary layer removal. 8. The inlet of claim 1, wherein: the inlet aperture is generally axisymmetric; andthe compression ramp comprises a forward compression conical ellipsoid disposed on a centerline of the inlet aperture. 9. The inlet of claim 8, further comprising an aft compression truncated conical ellipsoid having a leading edge that is proximate to a trailing edge of the forward compression conical ellipsoid, the aft compression truncated conical ellipsoid linearly movable between a first position and a second position along an axis parallel to the axis of motion of the forward compression conical ellipsoid. 10. The inlet of claim 9, wherein the forward compression conical ellipsoid and the aft compression truncated conical ellipsoid are configured to move in unison to modify the compression of the incoming air at the inlet aperture and to move differentially to provide a selectable amount of boundary layer removal. 11. An air-breathing engine assembly, comprising: an engine configured to accept an incoming flow of air at a forward end and expel an exhaust at an aft end;an inlet assembly comprising: a housing coupled to the engine and defining an inlet aperture;a compression ramp surrounded by the inlet aperture, the compression ramp being movable with respect to the housing between a first position and a second position along an axis parallel to the direction of the incoming air flow;at least one compression element coupled to the housing and disposed between the compression ramp and the inlet aperture, the compression element having a first portion linearly movable with respect to the compression ramp between a first position and a second position along an axis parallel to a direction of the incoming air flow, the first portion having a forward edge configured to mate with an aft edge of the compression ramp, the compression element configured such that a boundary layer removal aperture is open when the first portion is in the first position and the boundary layer removal aperture is closed when the first portion is in the second position; anda first actuator coupled to the first portion of the compression element, the first actuator configured to selectable move the first portion between the first and second positions;a second actuator coupled to the compression ramp, the second actuator configured to selectably move the compression ramp between the first and second positions;wherein the first portion and the compression ramp are configured to move in unison to modify the compression of the incoming air and to move differentially to provide a selectable amount of boundary layer removal from the incoming air. 12. A method of removing a boundary layer from an incoming air flow at an inlet of an engine, the method comprising the steps of: moving a forward portion of a compression element disposed in front of and surrounded by the inlet of the engine along an axis parallel to a direction of the incoming air flow so as to open a boundary layer removal aperture located between the inlet and the forward portion, the forward portion being moved to a selectable position to provide a selectable amount of boundary layer removal;moving a second portion of the compression element in unison with the first portion of the compression element to modify the compression of the incoming air at the inlet aperture; andmoving the second portion of the compression element move differentially from the first portion of the compression element to provide a selectable amount of boundary layer removal. 13. The inlet of claim 1, wherein when the boundary layer removal aperture is open, air flow is diverted through the boundary layer aperture along a path within, but separated from, the inlet aperture. 14. The inlet of claim 1, wherein the compression ramp is conical. 15. The inlet of claim 1, wherein the compression ramp is movable relative to the inlet aperture.
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이 특허에 인용된 특허 (3)
Harm Dorson J. (Seattle WA) Zabinsky Joseph M. (Bellevue WA), Translating lip aircraft cowling structure adapted for noise reduction.
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