The Boeing Company

Steven Michael Loukusa

Warren Andrew Atkey

Bryce Avery Vandyke

Marcus K Richardson

Daniel F Lewinski

Myles Edward Brown

Charles J Fiterman

Kenneth R Williams

Julie Fatemeh Asfia

Steven M Barton

Casey Ng

Brian Tatsuo Imada

Mark J Lord

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 system and method for regulating pressure inside a vehicle ('cabin pressure') with reduced noise is disclosed. The system can include a forward gate and an aft gate that can be moved from a closed position to an open position to release cabin pressure in a controlled manner. The forward gate and the aft gate can comprise one or more flow disruptors. A first portion of the flow disruptors can be fixed and a second portion can be moveable between a retracted position and a deployed in position. In the retracted position the one or more flow disruptors can reduce broadband noise through the system by smoothing air flow therethrough. In the second position, the one or more flow disruptors can create boundary layer turbulence. The boundary layer turbulence can prevent, or delay, flow separation reducing tonal noises therethrough. In this manner, flow efficiency can be increased and noise reduced.

Cabin pressure outflow valve noise suppression devices and methods

Systems and methods are disclosed for selecting an emergency descent rate for an aircraft based on the rate of depressurization in the cabin of the aircraft. In one embodiment, the method includes the steps of detecting a depressurization warning for the cabin of the aircraft, and determining a rate of depressurization inside the cabin. The method further includes selecting a rate for an emergency descent for the aircraft in response to the depressurization warning based on the rate of depressurization inside the cabin, and initiating the emergency descent at the selected rate.

Selection of emergency descent rates for an aircraft due to cabin depressurization

A detection system is provided for detecting at least one hazardous condition in an enclosure including a ventilation system, where the ventilation system is capable of operating in either an on or off mode. The system includes at least one detector capable of detecting at least one level representative of the severity of the hazardous conditions within the enclosure, where each level is associated with a pre-alarm threshold and an alarm threshold that is higher than the pre-alarm threshold. The detection system also includes a controller capable of operating the ventilation system in the off or on mode when at least one level detected by the detectors is above or below the respective pre-alarm threshold, respectively. The controller is also capable of reporting the hazardous condition when the at least one level is above or below the respective alarm threshold, respectively.

System, controller and method of detecting a hazardous condition within an enclosure having a ventilation system

An all electric air conditioning system for an aircraft, wherein the aircraft defines an interior volume having conditioned air at a first pressure. A compressor is provided and is operable to compress supply air to a second pressure. The compressor being operated in response to an electrical drive motor. A passage fluidly couples the compressor and the interior volume of the aircraft. A heat dissipating device, such as a heat exchanger, is positioned in the passage to extract heat energy from the supply air. This arrangement permits conditioning of air within the aircraft without using bleed air from the engines. The use of bleed air results in a significant amount of fuel burn. An optional conditioned air recovery system may be coupled to the interior volume of the fuselage to direct at least a portion of the conditioned air from the interior volume back for further conditioning and use.

Growing community of inventors

Bothell, WA, United States of America

Steven Michael Loukusa