The Boeing Company

Alan K Prichard

Victor Ken Stuhr

Joseph R Olivadoti

Mithra M K V Sankrithi

Kelly L Boren

Matthew David Moore

Gerhard E Seidel

Lowell Bruce Campbell

Stephen Douglas Friddell

Mark Steven Good

Kevin Matthew Retz

S Douglas Friddell

Lowel B Campbell

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

An aircraft cabin has been reconfigured with a rear fuselage galley and a modified aft pressure bulkhead that enables the galley to be moved rearwardly to provide additional floor space in the aircraft cabin.

Aircraft having a recessed cavity in an aft pressure bulkhead wall surface and a galley moved rearwardly into the recessed cavity increasing floor space in front of the galley

An electrically conductive structure includes a plurality of carbon fiber layers and at least one electrically conductive filament three-dimensionally woven among the carbon fiber layers. The plurality of carbon fiber layers and the at least one electrically conductive filament are operable to conduct electrical current throughout the structure.

Electrically conductive structure

A method and apparatus for controlling a movement of a control surface comprises a first linkage system, a second linkage system, and an actuator system. The first linkage system is connected to a first location of a control surface. The second linkage system is connected to a second location of the control surface. The first location is closer to a leading edge of the control surface than the second location. The actuator system is configured to move the first linkage system and the second linkage system.

Trailing edge flap system

The structural strength of an aircraft wing is continuously tailored along its length to closely match continuously varying imposed wing loads. The wing includes upper and lower skins each formed from panels joined together. Each of the skin panels includes a stiffening web sandwiched between and joined to the inner and outer facesheets. The web has a repeating pattern and at least one dimension that continuously varies along the length of the panel.

Aircraft wings having continuously tailored structural strength

Methods and systems for manufacturing composite aircraft wings and other structures are disclosed herein. A tool assembly for use in manufacturing composite laminates in accordance with one embodiment of the invention includes a tool plate carried by a movable support system. The tool plate includes a tool surface configured to support fiber-reinforced resin material and define an outer mold line (OML) of the fiber-reinforced resin material. The movable support system is configured to respond to signals from a controller to automatically change the shape of the tool surface and alter the OML of the finished part to suit the particular application. In one embodiment, the movable support system can include a plurality of telescoping actuators operably coupled to the tool plate.

Methods and systems for manufacturing a family of aircraft wings and other composite structures

One embodiment includes a system of joined structures that includes a first structure having a first aperture in a composite material. The first aperture has a first interior surface and a first minimum radial extent. The system further includes a second structure having a second aperture in a metallic material. The second aperture has a second interior surface and a second minimum radial extent at least approximately the same as the first minimum radial extent. The system still further includes a coupling device having a first shank section extending through the first aperture and a second shank section extending through the second aperture. The portion of the second shank section applies a first radial force to the second interior surface and the first shank section applies at least approximately no radial force to the first interior surface. The composite material proximate to the first aperture is undamaged.

Methods and systems for joining structures

A vessel, such as a wing-integrated aircraft fuel tank. The vessel can include a first surface portion, a second surface portion spaced apart from the first surface portion, and a core positioned between the first and second surface portions. The core can be sealably connected to the first and second surface portions and can be positioned to carry a load from at least one of the first and second surface portions to the other. The core can include a plurality of cells separated by cell walls, at least some of which have wall openings positioned to provide liquid communication between adjacent cells.

Method and apparatus for liquid containment, such as for aircraft fuel vessels

Stiffened structures and associated methods are disclosed. In one embodiment, an elongated metallic stiffening member can be attached to a composite sheet and positioned to resist bending of the composite sheet. In another embodiment, a structural system can include an elongated composite element attached between a composite sheet and a metallic stiffening member. In still another embodiment, the structural system is formed without attaching a honeycomb stiffening arrangement.

Growing community of inventors

Lynnwood, WA, United States of America

Alan K Prichard