The Boeing Company

Robert Darel Morrow

Aaron William Bartel

Randall Dow Wilkerson

Tunde Abiodun Olaniyan

Alexandre D Curaudeau

Alan James Scott

Leonard Joseph England

Robin L Westberg

Donald T Powell

Jason Franklin Joel

Luke D Torjesen

Richard D Stokes, Jr

Richard D Stokes Jr

An engine nacelle inlet is provided. The inlet comprises an inner barrel having a leading edge and a trailing edge. A segmented attach flange is connected to an outer circumference of the trailing edge of the inner barrel, wherein the segmented attach flange comprises a number of discrete attach flange fittings. An outer barrel having a leading edge and a trailing edge surrounds the inner barrel. A number of attachment brackets connect the outer barrel to the segmented attach flange. Each attachment bracket comprises two struts connected at a common point on the trailing edge of the outer barrel and connected at separate points on one of the attach flange fittings to form a truss. Each attachment bracket is connected to a separate respective attach flange fitting.

Inlet outer barrel segmented attach flange

There is provided a load distribution panel assembly for a gas turbine engine. The assembly has a panel structure having at least one circumferential structural panel having a first end, and a second end coupled to a fixed structure of the gas turbine engine. The circumferential structural panel has a first compliant portion extending away from the first end, and has a second stiffened portion angled with respect to and extending radially away from the first compliant portion, and terminating at the second end. The second stiffened portion has a closed stiffened cavity portion integral with a perimeter flange portion. The panel assembly converts fore/aft point load(s) applied to it by load applying apparatus(es), to hoop tension and compression loads, and reacts a load offset in in-plane load(s), to provide uniform load distribution of the fore/aft point load(s) to the fixed structure.

Load distribution panel assembly, system and method

A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers.

Thermoformed cascades for jet engine thrust reversers

A thrust reverser torque box assembly for an aircraft engine is constructed with a torque tube having a cross section configuration tailored and conducive to carrying torsion and discrete major fittings at opposite ends of the torque tube that connect the torque tube and thrust reverser actuation and reacts loading due to reverse thrust operation to the aircraft engine fan case.

Thrust reverser torque box with discrete major fittings

Growing community of inventors

Milton, WA, United States of America

Robert Darel Morrow