The Boeing Company

Marcus K Richardson

Bryce Avery Vandyke

Chao-Hsin Lin

Colin W Hart

James P Schalla

Raymond H Horstman

Myles Edward Brown

Tateh Wu

Brian Tatsuo Imada

William John Connell

Michael James Tonks

Steve G Mackin

Jeffrey Lynn Duce

David Michael Smith

Cameron Lindsay Carnegie

Steven Michael Loukusa

Michael J Dessero

Clyde Robert Tuohimaa

Sook Kenna Kim

Eric L Sarinas

Kyongsoo Chae

Chae Kyongsoo

A galley cart system employs a dry ice compartment and a refrigeration compartment in a galley cart in flow communication with the dry ice compartment. A ventilation system is in interruptible flow communication with at least the refrigeration compartment and configured to receive gas discharged from at least the refrigeration compartment.

Dry ice draw through galley cooling reference to related applications

Methods, systems, and apparatuses for temporarily increasing, on demand, the relative humidity of an area located proximate to a user in environments having lower than ambient relative humidity are provided by integrating a personal humidification circuit into a water delivery circuit to provide a diverted flow of water, and provide a flow of water vapor to a user, and returning the relative humidity-enhanced environment to a predetermined relative humidity by purging the environment.

Integrated personal humidifier system

Systems to produce cabin supply air for aircraft and related methods are described herein. An example system includes an air conditioning pack including a heat exchanger including a first flow path and a second flow path isolated from the first flow path. The second flow path is to receive cabin exhaust air from a cabin of an aircraft. The cabin exhaust air is to reduce a temperature of the cabin supply air flowing through the first flow path of the heat exchanger. The system also includes a turbine to receive the cabin supply air from the heat exchanger. The turbine is to reduce a temperature and pressure of the cabin supply air. A turbine outlet of the turbine is fluidly coupled to the cabin to provide the cabin supply air to the cabin. The system further includes a fan to direct the cabin exhaust air from the heat exchanger.

Systems and methods to produce aircraft cabin supply air

Dry ice draw through galley cooling

Systems and methods for limiting infiltration of cabin air into the flight deck of an aircraft, where the systems include at least one upper nozzle disposed adjacent to and above an outer upper edge of a flight deck doorway and directed downwardly, and at least one lower nozzle disposed adjacent to and below an outer lower edge of the flight deck doorway and directed upwardly; a conduit system to deliver air from a flight deck air supply to the upper and lower nozzles; and an airflow controller configured to provide sufficient air flow from the flight deck air supply to the upper and lower nozzles to create directional airstreams across the gaps between the closed flight deck door and the upper and lower edges of the flight deck doorway, so that the airstreams limit infiltration of cabin air into the flight deck via the gaps.

Systems and methods for limiting infiltration of cabin air into the flight deck of an aircraft

A test cage and method for testing a gap formed between a wall and an insulation layer in a vehicle. The test cage includes first and second end walls and a sidewall to form an interior space. Openings extend through one or more of the first and second end walls and the sidewall. The openings are configured to allow air flow through the interior space. Two or more ports extend through the first end wall and are in communication with the interior space. Each of the ports comprises an inner end at the interior space with the inner ends spaced apart within the interior space and also spaced away from the second end wall. Hoses can be connected to the ports to provide for inputting a gas and/or testing the air within the gap.

Test cage for testing a gap in a vehicle

A moisture management system for use in an aircraft incorporates a bladder supported between adjacent structural members between a skin and a sidewall panel. The bladder is configured to passively expand to contact at least one of the structural members as a pressure decreases during an ascent of the aircraft and to collapse as the pressure increases during a descent of the aircraft.

Passive moisture management bladder in an aircraft

An air drying system including a compressor coupled to a first air inlet through which moist air is received, a first turbine in fluid communication with the compressor and coupled to a first air outlet through which dry air is expelled, and a second turbine coupled to a second air inlet and a second air outlet and being driven, at least in part, by an air flow caused by a pressure differential between the second air inlet and the second air outlet, where the second turbine is operably coupled to the compressor and the first turbine by a drive mechanism so that rotation of the second turbine drives rotation of the compressor and the first turbine.

Air drying system and method therefor

A galley cart system employs a housing with a door coupled to the housing, the door configured to be moved between a closed position and an open position. A vent plate in the housing communicates between a first compartment and a second compartment. A valve plate adjacent the vent plate is movable from a venting position when the door is in the closed position to a blocking position when the door is in the open position thereby preventing flow communication between the first and second compartment.

Controlling flow of dry ice sublimation inside a galley cart

A pressure relief system is provided and a corresponding method for relieving pressure from a duct routing a gas from a compressor to a load utilizing the same. According to one aspect, a pressure relief assembly, located near the load, and independent of the primary load compressor pressure relief valve, for use with a duct includes a cover, first and second chambers, and a piston. The piston provides a moveable wall between the chambers and is coupled to the cover. As gas from the duct enters the two chambers, the configuration of the chambers provides for a pressure differential that moves the piston and the corresponding cover. This movement transitions the cover from a closed configuration that seals the duct to an open configuration that allows gas within the duct to escape.

Compressor surge protection

Described herein is a composite panel that includes a first layer made from an electrically non-conductive material. The composite panel also includes a resistance heater printed onto the first layer and a capacitive sensor applied onto the first layer. The capacitive sensor is operably coupled with the resistance heater. The composite panel additionally includes a second layer adjacent the resistance heater and the capacitive sensor. The resistance heater and the capacitive sensor are positioned between the first layer and the second layer. Furthermore, the second layer is made from an electrically non-conductive material. The resistance heater is configured to generate heat at least partially in response to input sensed by the capacitive sensor.

Composite panel with integrated heater system and associated methods for manufacturing

A pressure equalization vent for use in an aircraft assembly is provided. The pressure equalization vent includes an opening having a first end and a second end opposite the first end, and a first side and a second side opposite the first side. The vent further includes a plurality of louvers positioned within the opening. Each louver is positioned a predetermined distance from an adjacent louver to form a gap therebetween. Each louver includes an airfoil-shaped cross-section configured to increase airflow efficiency across the vent.

Pressure equalization vent for use in an aircraft assembly

An aircraft air supply system may include a primary duct to supply a primary air flow to a flight deck of an aircraft. A nitrogen generating system may be configured for generating nitrogen enriched air and oxygen enriched air. A secondary duct may be provided for channeling the oxygen enriched air from the nitrogen generating system to the primary duct. The flow of the oxygen enriched air into the primary duct and to the flight deck may be controlled to reduce an effective altitude of the flight deck.

Aircraft air supply systems for reducing effective altitude of flight decks

A ram air system includes a bay comprising an exterior wall defining an interior volume that at least partially encloses a ram air duct. The ram air duct includes an outlet configured to discharge an exhaust airflow at a first temperature. At least one of the exterior wall and the ram air duct defines an aperture therein providing for flow communication between the bay interior volume and the exhaust airflow such that cooling air flows from the interior volume to form a boundary layer between the exhaust airflow and the exterior wall downstream of the outlet. The boundary layer is at a second temperature that is lower than the first temperature.

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Bothell, WA, United States of America

Marcus K Richardson