The Boeing Company

Theboeing Company

Karen M Jost

Carlos Angelo Fracchia

Neal A Froeschner

Philip O Chrissos

Ronald J Byington

Mark David Higgins

Jeffrey D Martin

Keith Rupel

Jimmy S Piszar

Colleen M Harper

Jeffrey Edward Polus

Gayl J Miller

Donald E Bowdle

David Miltenberger

James A Thomas

Danny Heineman

Danny E Heineman

Keith E Rupel

Gas turbine engine fan blade containment systems are disclosed. An example fan blade containment system includes a shield to be coupled to an aircraft structure and to at least partially surround a circumference of an aircraft engine. The shield is to be spaced from an outer surface the aircraft engine when the shield is coupled to the aircraft structure. A shield termination fitting is to couple a terminating end of the shield to the aircraft structure.

Gas turbine engine fan blade containment systems

Gas turbine engine fan blade containment systems are disclosed. An example fan blade containment system includes a shield to be coupled to an aircraft structure and to at least partially surround a circumference of an aircraft engine. The shield is to be spaced from an outer surface the aircraft engine when the shield is coupled to the aircraft structure. The shield is to form a laminated clevis at an end of the shield. A retention rod is to be positioned in the laminated clevis of the shield. The retention rod is to engage a lug hook of the aircraft structure to anchor the shield to the aircraft structure.

A cooling bond pad and methods are disclosed. A plurality of internal-cooling channels cool the cooling bond pad, and an internal-flow channel is coupled to the internal-cooling channels, and directs an internal-coolant flow to the internal-cooling channels. An external-flow channel directs a through-coolant flow through the cooling bond pad.

Multi-channel cooling plenum

An apparatus and methods for forming a composite part are provided. A method for forming a composite part may include placing initial composite material on a base tool, placing a tooling mandrel on the composite material, placing additional composite material over the tooling mandrel, covering at least a portion of the composite material that overlays the tooling mandrel with a composite forming tool, heating the composite material to at least partially cure the composite material, and permitting a first portion of the composite forming tool to change size during the heating of the composite material to a greater degree than a second portion of the composite forming tool. In this regard, the second portion of the composite forming tool is closer to the base tool than the first portion of the composite forming tool. A composite forming tool is provided that permits differential expansion of different portions of the tool.

Apparatus for forming hat stiffened composite parts using thermally expansive tooling cauls

A method for making a honeycomb composite structure wherein the method allows for fluid flow from cells of a honeycomb core during a cure process. More specifically, the method involves forming one or more vents in a skin of the structure, which are preferably filled with venting wicks, to allow for fluid flow before being sealed by the polymer matrix during a skin bonding process. Additionally, the structure preferably comprises a scrim that allows for fluid flow between multiple cells of the honeycomb core. The honeycomb composite structure produced according to this process comprises, among other things, a sealed venting region that comprises a polymer matrix and fibers that are transverse to the skin.

Low temperature, vacuum cure fabrication process for large, honeycomb core stiffened composite structures

An apparatus and methods for forming a composite part are provided. A method for forming a composite part may include placing initial composite material on a base tool, placing a tooling mandrel on the composite material, placing additional composite material over the tooling mandrel, covering at least a portion of the composite material that overlays the tooling mandrel with a composite forming tool, heating the composite material to at least partially cure the composite material, and permitting a first portion of the composite forming tool to change size during the heating of the composite material to a greater degree than a second portion of the composite forming tool. In this regard, the second portion of the composite forming tool is closer to the base tool than the first portion of the composite forming tool. A composite forming tool is also provided that permits differential expansion of different portions of the tool.

Apparatus and methods for forming hat stiffened composite parts using thermally expansive tooling cauls

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St. Louis, MO, United States of America

Karen M Jost