The Boeing Company

Edward L Lawson

Antonio B Gonzales

Aaron Jonathan Kutzmann

Jack William Mauldin

David W Kwok

John A Weidler

Andrew C Kulak

Max Urban Kismarton

John Charles Vassberg

Kevin Reed Lutke

Neal A Harrison

Christopher K Droney

Darold B Cummings

Benjamin A Harber

David J Manley

Norman Henry Princen

Robert H Liebeck

Robb Gregg, Iii

Steve Hollowell

David A Boyer

An aircraft having a blended-wing-body configuration includes a centerbody, a pair of wings, at least one pair of engines, a pair of air inlets, and a pair of exhaust outlets. The centerbody has an airfoil-shaped cross section, an aircraft centerline, an aft portion, an upper mold line, a lower mold line, and a pair of centerbody leading edge portions respectively on opposite sides of the aircraft centerline. The wings are integral with the centerbody. The pair of engines are located on opposite sides of the aircraft centerline and are mounted within the centerbody between the upper mold line and the lower mold line. The pair of air inlets are located respectively along the centerbody leading edge portions and are respectively fluidly coupled to the pair of engines. The pair of exhaust outlets our located in the aft portion of the centerbody and our respectively fluidly coupled to the pair of engines.

Aircraft having embedded engines

Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing.

Methods and apparatus for supporting engines and nacelles relative to aircraft wings

Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a first support structure to be coupled to a wing, a second support structure to be coupled to the wing and a nacelle. The support structures are coupled to opposite sides of the nacelle. The support structures are to be coupled to opposite sides of an engine to enable thrust loads to be reacted through the support structures to the wing.

Apparatus and methods provide for an engine nozzle having a universal convergent nozzle and a distinct nozzle aperture. Aspects of the disclosure provide a universal convergent nozzle that includes a nozzle throat and is attachable at a first end to an aircraft engine and at a second end to a distinct nozzle aperture. While the distinct nozzle aperture may include features that are specific to the corresponding engine mounting location, the universal convergent nozzle may be interchangeably used with any engine and distinct nozzle aperture at any engine mounting location. The configuration of the universal convergent nozzle ensures consistent engine performance and engine exhaust plume conditioning across all engine mounting locations, irrespective of the distinct nozzle aperture features downstream of the universal convergent nozzle.

Universal convergent nozzle and distinct nozzle aperture

Apparatus and methods provide for an aircraft configuration that utilize structural and engine exhaust flow control devices to enhance performance. Aspects of the disclosure provide a fuselage with a pressure vessel nested within a non-cylindrical outer mold line fairing. A twin-boom empennage may be connected to the fuselage. A wing may attach in a blended wing configuration with a sweep angle that positions the aircraft center of lift to minimize any pitching moment induced by the activation or deactivation of an upper surface blown (USB) system. The USB system may include a conformal USB flap positioned downstream of an engine exhaust plume, as well as a controllable USB nozzle aperture to promote exhaust flow attachment to the conformal USB flap. A universal convergent nozzle may be utilized to connect each controllable USB nozzle aperture to a corresponding internally mounted aircraft engine.

Aircraft configuration utilizing fuselage, wing, empennage, and exhaust flow control devices

A method of generating lift for a vehicle including heating a flow of gas using a gas generator mounted on the vehicle that contributes no more than about ten percent of thrust used to propel the vehicle in a forward direction, and driving a lift fan using the heated gas flow to generate lift for the vehicle.

Method and apparatus for generating lift

A method of generating lift for a vehicle including a gas turbine engine having a combustor, a core flow heated by the combustor, and a bypass flow which bypasses the combustor. The method includes segregating at least a portion of the core flow from the bypass flow, directing the segregated portion of the core flow in a first direction to generate lift for the vehicle, segregating at least a portion of the bypass flow from the core flow, and directing the segregated a portion of the bypass flow in a second direction to generate lift for the vehicle.

Growing community of inventors

Long Beach, CA, United States of America

Edward L Lawson