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US 12,590,558 B2Granted
Drag recovery scheme using boundary layer ingestion
AssigneeJetZero, Inc.
InventorMark Allan Page
Life of this patent
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Abstract
Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.
Claims18
An aircraft, comprising:
- at least one engine housed within a nacelle, wherein the at least one engine is mechanically coupled to at least one fan;
- at least one bypass intake duct configured to receive boundary layer air from a surface of the aircraft, wherein the at least one bypass intake duct is located proximate to a fan intake of the at least one fan;
- a second bypass intake duct configured to receive second boundary layer air from the surface of the aircraft;
- at least one bypass exhaust duct located proximate to a fan exhaust of the at least one fan, wherein the at least one bypass exhaust duct is configured to output the boundary layer air into the fan exhaust of the at least one fan;
- a second bypass exhaust duct located proximate to the fan exhaust of the at least one fan;
- a passageway, located substantially between the surface of the aircraft and the at least one engine, fluidically connecting the at least one bypass intake duct with the at least one bypass exhaust duct and configured to direct the boundary layer air from the at least one bypass intake duct to the at least one bypass exhaust duct;
- a second passageway fluidically connecting the second bypass intake duct with the second bypass exhaust duct and configured to direct the second boundary layer air from the second bypass intake duct to the second bypass exhaust duct;
- and
- a nozzle configured to direct the boundary layer air and the fan exhaust out of a nozzle exit.
6 more elements
A method of reducing drag of an aircraft, comprising at least one engine housed within a nacelle, wherein the at least one engine is mechanically coupled to at least one fan and the method comprises:
- receiving, by at least one bypass intake duct, boundary layer air from a surface of the aircraft, the at least one bypass intake duct located proximate to a fan intake of the at least one fan;
- receiving, by a second bypass intake duct, second boundary layer air from the surface of the aircraft;
- fluidically connecting, by a passageway located substantially between the surface of the aircraft and the at least one engine, the at least one bypass intake duct with at least one bypass exhaust duct located proximate to a fan exhaust of the at least one fan;
- fluidically connecting, by a second passageway, the second bypass intake duct with a second bypass exhaust duct located proximate to the fan exhaust of the at least one fan;
- directing, by the passageway, the boundary layer air from the at least one bypass intake duct to the at least one bypass exhaust duct;
- directing, by the second passageway, the second boundary layer air from the second bypass intake duct to the second bypass exhaust duct;
- outputting, using the at least one bypass exhaust duct, the boundary layer air into the fan exhaust of the at least one fan;
- and
- directing, using a nozzle, the boundary layer air and the fan exhaust out of a nozzle exit.
6 more elements
Dependencies are inferred from the claim text.