The Boeing Company

The United States of America As Represented by the Administrator of the

Boeing Commercial Airplane Company

Gerhard E Seidel

Mithra M K V Sankrithi

Mithra M Sankrithi

Matthew David Moore

Alan K Prichard

Peter Z Anast

James Douglas McLean

John Yeeles

Robert H Kelley-Wickemeyer

Paul W Dees

Chester P Nelson

Harry C Ralph

Eric Evin Adamson

Gary D Reysa

Mannon L Wallace

V Kenneth Stuhr

Edward W Gronenthal

John E Cashman

Gilbert J Nash

Ronaldo O Cabrera

Alan J Atkinson

David W McKenna

Walter H Howard, Jr

Mithra MKV Sankrithi

Mannon Lee Wallace

Kenneth V Stuhr

An ultra-efficient 'green' aircraft propulsor utilizing an augmentor fan is disclosed. A balanced design is provided combining a fuel efficient and low-noise high bypass ratio augmentor fan and a low-noise shrouded high bypass ratio turbofan. Three mass flow streams are utilized to reduce propulsor specific fuel consumption and increase performance relative to conventional turbofans. Methods are provided for optimization of fuel efficiency, power, and noise by varying mass flow ratios of the three mass flow streams. Methods are also provided for integration of external propellers into turbofan machinery.

Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan

Slotted cruise airfoil technology allows production of a substantially unswept wing that achieves the same cruise speed as today's conventional jet airplanes with higher sweep. This technology allows the wing boundary layer to negotiate a strong recovery gradient closer to the wing trailing edge. The result is about a cruise speed of Mach=0.78, but with a straight wing. It also means that for the same lift, the super velocities over the top of the wing can be lower. With very low sweep and this type of cruise pressure distribution, natural laminar flow will be obtained. In addition, heat is transferred from the leading edge of the wing and of the main flap to increase the extent of the natural laminar flow. The slotted cruise wing airfoil allows modularization of the wing and the body for a family of airplanes. The unsweeping of the wing significantly changes the manufacturing processes, reduces manufacturing costs and flow time from detail part fabrication to airplane delivery. The system architecture is all new for cost reduction. A high wing arrangement allows more freedom for installation of higher bypass ratio advanced geared fan engines. A low is wing in conjunction with aft body mounted engines will have a similar effect. Aerodynamic efficiency and engine fuel burn efficiency result in considerable lower emission of noise and greenhouse gases.

Airplane with unswept slotted cruise wing airfoil

An aircraft passenger seating arrangement has at least one passenger seat within an enclosure and an aisle located within the enclosure adjacent to the seat with no seats located adjacent to an opposite side of the aisle from the seat. The enclosure has a frame with a symmetrical cross section, the frame having a curved perimeter wherein the height of the cross section is different than the width to minimize cross sectional area of the aircraft body to reduce sonic boom signature.

Asymmetric passenger arrangement

Liquid hydrogen fueled aircraft

Integrated high-speed aircraft, such as high-speed transport aircraft, and associated methods of manufacture. In one embodiment, a high-speed transport aircraft includes a fuselage having a first fuselage portion and a second fuselage portion positioned aft of the first fuselage portion. The first fuselage portion can have a first cross-sectional area and the second fuselage portion can have a second cross-sectional area that is less than the first cross-sectional area. The high-speed transport aircraft can further include a wing and a propulsion system. The wing can extend outwardly from the fuselage at least proximate to the second fuselage portion and can include a leading edge region and a trailing edge region. The propulsion system can include an engine nacelle fixedly attached to the wing and laterally aligned with the second fuselage portion. In one aspect of this embodiment, the engine nacelle can include an air inlet positioned aft of the leading edge region of the wing and an exhaust gas outlet positioned aft of the trailing edge region of the wing.

Integrated high-speed aircraft and associated methods of manufacture

Aircraft

A dual boundary layer engine inlet for a turbofan propulsion engine of an aircraft having a first air inlet positioned generally within the boundary layer flowing around the exterior surface of the aircraft. A first passageway fluidly interconnects the first air inlet and the turbofan propulsion engine to provide air from the boundary layer to the bypass to reduce aerodynamic drag. A second air inlet is positioned generally outside of the boundary layer. This second passageway fluidly interconnecting the second air inlet and the turbofan propulsion engine to provide air outside of the boundary layer to the core and compressor of the turbofan engine to maintain engine efficiency.

Separate boundary layer engine inlet

An aircraft having a fuselage and a wing employs area-ruling of the fuselage in a vertical direction, with at least a substantial amount of the area-ruling being accomplished by dishing the keel area of the fuselage directly below the center portion of the wing. In one embodiment the aircraft has a main passenger seating deck and forward and aft upper seating decks located above the main deck respectively forward and aft of the wing, and both the upper surface of the fuselage above the wing and the lower surface of the fuselage below the wing are area-ruled.

Airframe having area-ruled fuselage keel

A system for aiding ground maneuvering of an airplane. The system includes at least one camera mounted on the airplane for generating video images of at last one gear with tires, preferably a main or nose landing gear and the surrounding ground. The cockpit of the airplane includes a video display device that displays the generated video images and a user interface that allows selection of the format for displaying the generated video images. A camera mounted within a moveable component of the airplane is mounted on a movable device that compensates for component movement. The system also includes a display generator for generating in real-time superimposed oversteer targets on the displayed video images. The video images with oversteer targets assist the pilot in determining the airplane's actual position relative to runways, taxiways, obstacles and other ground features and to maneuver a plane with a wide wheel track long wheelbase, or both accordingly.

Airplane ground maneuvering camera system

Slotted cruise airfoil technology allows production of a substantially unswept wing that achieves the same cruise speed as today's conventional jet airplanes with higher sweep. This technology allows the wing boundary layer to negotiate a strong recovery gradient closer to the wing trailing edge. The result is about a cruise speed of Mach&equals;0.78, but with a straight wing. It also means that for the same lift, the super velocities over the top of the wing can be lower. With very low sweep and this type of cruise pressure distribution, natural laminar flow will be obtained. In addition, heat is transferred from the leading edge of the wing and of the main flap to increase the extent of the natural laminar flow. The slotted cruise wing airfoil allows modularization of the wing and the body for a family of airplanes. The unsweeping of the wing significantly changes the manufacturing processes, reduces manufacturing costs and flow time from detail part fabrication to airplane delivery. The system architecture is all new for cost reduction. A high wing arrangement allows more freedom for installation of higher bypass ratio advanced geared fan engines. A low is wing in conjunction with aft body mounted engines will have a similar effect. Aerodynamic efficiency and engine fuel burn efficiency result in considerable lower emission of noise and greenhouse gases.

An improvement to a subsonic passenger aircraft is provided. The passenger aircraft has a fuselage including a main passenger seating deck (14) including forward, middle, and aft regions. The fuselage includes an upper forward deck (16) located above the main passenger seating deck forward region and accessible thereto. Both the main deck and upper forward deck having doors (30), (26) therein for passenger and supplies ingress and egress. The fuselage includes an aft upper deck (18) located above the main passenger seating deck aft region and accessible from the main deck. An upper middle region (20) is located above the main deck middle region. In one embodiment, the upper middle region (20) is of a height elevationally less than either of the forward and aft upper decks. The cross-sectional area of the fuselage at the upper middle region is less than the cross-sectional area of the fuselage at either the forward upper deck region or the aft upper deck region. In another embodiment, the forward upper cabin and the aft upper cabin are separate, longitudinally non-adjacent cabins for accommodating seated passengers.

Dual upper deck airplane

A multiwheel landing gear assembly includes a forward set of wheels which are in tandem with a middle set of wheels which in turn are in tandem with a rear set of wheels. The forward set of wheels are connected to a main support strut of the landing gear by a levered arrangement. The middle and rear set of wheels are connected together by a truck beam which in turn is connected to the main support strut by a radius rod. When the middle and rear wheels are subject to an upward force such as when the aircraft is landing, the radius rod limits movement of the wheels in a generally upward direction along a path having a radius which is equal to the length of the radius rod. Movement of the middle and rear wheels along the path in the upward direction is resisted by a shock absorber. In this manner, the vertical loads are reacted in a lengthwise direction along the radius rod and shock absorber.

Multiwheeled trailing type landing gear assembly

A device which actuates aircraft control surfaces is disclosed. The actuator 19 is disposed entirely within the control surface structure 15. Because the actuator 19 is disposed entirely within the control surface 15, the gap 14 between the wing structural box 13 and control surface 15 may be reduced. Reducing the size of the gap 14 is especially desirable for wings with high aspect ratio, wherein the volume of structural box 13 is at a premium.

Control surface actuator

A fan jet engine assembly comprising a hoop fan surrounding a turbojet (19) is disclosed. The hoop fan includes a pair of rotatable hubs (27, 29) that encircle the turbojet. A stage of fan blades (31, 33) is attached to each hub (27, 29) and radiates outwardly therefrom. The tips of the blades (31, 33) of at least one of the stages attached to a loop (23/25 or 61) that encircles the tips of the blades (31, 33) of both stages. Due to the attachment of the hoop (23/25 or 61) to the blades (31, 33), the hoop rotates as the hubs (27, 29) are rotated by the turbojet (19). The pitch of the blades of at least one of the stages is adjustable.

Growing community of inventors

Renton, WA, United States of America

Gerhard E Seidel