Abstract: 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.

Abstract: 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.

Abstract: Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed.

Abstract: Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed.

Abstract: 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.

Abstract: 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.

Abstract: 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.