Textron Innovations Inc.

Trey Marcus Siemens

Scott William Weber

Sam Khounsombath

Burl Justin Fletcher

Richard Lee Gaines

A pneumatic flow control system for an aircraft includes a control system operating and implementing a software program through a digital environment, the software program having one or more rules; a sensor in digital communication with the control system, the sensor to relay engine power data to the control system; an electronically controlled valve in digital communication with the control system, the electronically controlled valve to control an amount of bleed air flowing therethrough; a first rule defining an engine power parameter and a valve position for the electronically controlled valve and using the engine power data relayed from the sensor, receiving data equating to the engine power parameter activates transmitting a command to the electronically controlled valve to adjust to the valve position; and the valve position is set to restrict flow through the valve to below a threshold limit.

System and method to prevent bleed air over-extraction in aircraft

An oxygen pressure relief and ventilation system includes a flow fuse fluidly coupled downstream of a pressure regulator. The pressure regulator is operatively coupled to an oxygen tank, and the oxygen tank is located in an unpressurized compartment of an aircraft. A pressure relief valve is fluidly coupled downstream of the flow fuse. A ventilation pathway fluidly couples the unpressurized compartment with a pressurized compartment. The flow fuse and the pressure relief valve are configured to cooperatively mitigate downstream flow of pressurized oxygen if the pressure regulator fails. The ventilation pathway is configured to allow air from the pressurized compartment to pass through to the unpressurized compartment for diluting a concentrated oxygen in the unpressurized compartment.

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Wichita, KS, United States of America

Trey Marcus Siemens