The Boeing Company

Edward Zielinski

Thomas A Campbell

Alan Thomas Bernier

Charles Steven Meis

Warren Andrew Atkey

Farhad Nozari

Charles J Fiterman

Michael D Bowman

Jonathan M Cruse

Thomas M Murray

Casey Y K Ng

Jeffrey Joseph White

Thomas J Connelly

Casey Ng

James Tane Iwamoto

Mark Dixon Ralston

Kent W Knechtel

Casey Y Ng

A heat transfer device for installation in a system having a heat generating element within the system away from which heat is to be transferred is described. The heat transfer device includes a heat pipe having a first portion, a second portion, and a working fluid contained within the heat pipe for transferring heat from the first portion to the second portion. The first portion is disposed in proximity with the heat generating element. The second portion is coupled to the first portion. At least part of the second portion is disposed outside the system to dissipate heat from the heat generating element and the second portion may be variably extended outside the system.

Variably extending heat transfer devices

A method and apparatus comprising a layer of material having a decorative graphic and an electrically conductive material in the layer of material. The layer of material is configured to be attached to a surface of an aircraft. The electrically conductive material is configured to cause a current from an atmospheric electrostatic discharge contacting the layer of material to spread out in a desired amount within the layer of material.

Decorative decal system for an aircraft

Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

Electric-based secondary power system architectures for aircraft

A composite heat shield includes a ceramic composite heat shield body comprising a pair of generally spaced-apart heat shield side panels, a heat shield bottom panel extending between the heat shield side panels and having a heat exposure surface, a heat shield top panel extending between the heat shield side panels in spaced-apart relationship with respect to the heat shield bottom panel and having at least one heat shield surface and at least one heat shield cavity defined between the heat shield bottom panel and the heat shield top panel.

Composite heat shield

Heat exchanger systems and associated systems and methods for cooling aircraft starters/generators are disclosed. A system in accordance with one embodiment includes a first fluid flow path for a first fluid, a second fluid flow path for a second fluid, and a third fluid flow path for a third fluid. The first and second flow paths are positioned proximate to the third flow path to transfer heat between the third fluid and both the first and second fluids. The third flow path is configured to allow a transfer of heat between the second and third fluids at a first transfer rate when the first fluid carries heat at a first rate, and at a second transfer rate different than the first transfer rate when the first fluid does not carry heat, or carries heat at a second rate less than the first rate. Accordingly, when the heat to be rejected by one fluid is decreased, the heat transfer rate for the remaining fluid can be increased.

Heat exchanger systems and associated systems and methods for cooling aircraft starter/generators

Methods and systems for starting aircraft turbofan engines are disclosed. A system in accordance with one embodiment includes an electrically-powered starter motor coupled to a turbofan engine to provide power to the turbofan engine during an engine start procedure. The system can further include an on-board, deployable, ram air driven turbine coupled to an electrical generator, which is in turn coupled to the starter motor to provide electrical power to the starter motor. In other embodiments, the ram air driven turbine can be replaced with a fuel cell or a battery. In still further embodiments, a single controller can control operation of both the engine starter and other motors of the aircraft.

Systems and methods for starting aircraft engines

A fireproof electrical wire housing (9) for routing electrical wires through a barrier wall, such as an aircraft bulkhead (21), without destroying the fireproof and hermetic functions of the bulkhead (21) is disclosed. The fireproof electrical wire housing (9) includes a sleeve (13) which surrounds a wire bundle (11) and a tubular housing (19). The tubular housing (19) includes a cover plate (17) that is mounted to the bulkhead(21). Thereafter, the sleeve (13) is inserted into the tubular housing (19). Holes (35) penetrating the wall of the sleeve (13) are used to inject a sealant into a cavity (39) in the sleeve (13) to prevent vapors and flames from passing through the fireproof electrical wire housing (9).

Growing community of inventors

Kent, WA, United States of America

Edward Zielinski