The Boeing Company

Other

Theboeing Company

Eric W Walliser

Robert A Nowak

Steven D Richardson

Vortex reduction apparatus for use with airfoils are disclosed. An example vortex reduction apparatus includes a housing to couple to a tip of an airfoil. The housing defines a volute fluid flow passageway between an inlet and an outlet. The volute fluid flow passageway is structured to induce a rotational fluid flow in a first rotational direction opposite a second rotational direction of a shed vortex induced at the tip of the airfoil during flight.

Vortex reduction apparatus for use with airfoils

Systems and methods for rotor/wing aircraft are disclosed. In one embodiment, an aircraft includes an airframe, a high-lift canard and tail, a rotor/wing, a propulsion system, and a drive assembly. The drive assembly, which may include a radial inflow turbine, is configured to extract work from the propulsion system to selectively rotate the rotor/wing assembly thus enabling the aircraft to conduct rotary-wing flight, fixed wing flight as well as smoothly transition between the two modes of flight.

Systems and methods for rotor/wing aircraft

A hub fairing system () for a stopped-rotor aircraft () having a fuselage () including a hub (). The hub () is mechanically coupled to the fuselage () and to multiple blades () and is rotated by an engine (). A retractable fairing () covers a portion of the hub (). An actuator () is coupled to the fairing (). A controller () is coupled to the actuator () and retracts the fairing (). A method of reducing drag on the aircraft includes transitioning between a rotary-wing mode and a fixed-wing mode. The fairing () is deployed over a portion of the hub () upon the completion of the transition between flight modes.

Rotor/wing dual mode hub fairing system

Aircraft including an airframe having a fuselage extending between a forward end and an aft end. The aircraft further includes a power plant mounted on the airframe producing exhaust during operation. The aircraft also includes a rotor/wing including a plurality of blades connected to a drive shaft rotatably mounted on the airframe and a radial inflow turbine mounted on the airframe in fluid communication with the power plant for receiving exhaust from the power plant. The radial inflow turbine includes a body forming an annular vortical chamber having an upper portion and a lower portion. The radial inflow turbine also includes a hub rotatably connected to the body and operatively connected to the drive shaft. In addition, the radial inflow turbine includes a plurality of vanes extending radially outward from the hub. The hub and the vanes are positioned in the vortical chamber.

Rotor wing aircraft having a bypassable radial inflow turbine

Aircraft including an airframe having a fuselage extending between a forward end and an aft end and a fixed wing extending laterally from the fuselage. The aircraft includes a power plant mounted on the airframe producing exhaust during operation. The aircraft includes a rotor/wing rotatably mounted on the airframe including a plurality of blades and an adjustable nozzle mounted on the airframe downstream from the power plant exhaust for selectively directing the power plant exhaust to exit the aircraft at a pre-selected angle with respect to the airframe within a range of angles extending from about horizontally rearward to about vertically downward.

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Mesa, AZ, United States of America

Eric W Walliser