The Boeing Company

Honeywell International Inc.

Kyle D Eilers

Warren Andrew Atkey

John Charles Gray

Kevin K Chakkera

Andrew T Johnson

A method for calculating an aircraft fuselage leakage calculation of an aircraft is provided. The method comprises determining a calculation period for an aircraft fuselage leakage value and inputting the calculation period into a computer to obtain a first input data. The method further comprises obtaining one or more outside air inflow rates and inputting the one or more outside air inflow rates into the computer to obtain a second input data. The method further comprises obtaining one or more air outflow rates and inputting the one or more air outflow rates into the computer to obtain a third input data. The method further comprises accumulating the first input data, the second input data, and the third input data in the computer to obtain an accumulated input data. The method further comprises processing the accumulated input data with a process software to obtain an output data in the form of a calculated aircraft fuselage leakage value. The method further comprises sending the output data to a data file. The method further comprises using the calculated aircraft fuselage leakage value to calculate an aircraft fuel savings potential value.

Method for reducing outside air inflow required for aircraft cabin air quality

A method for reducing outside air inflow required for aircraft passenger cabin air quality is provided. The method determines when passenger cabin air quality is the driving outside air inflow requirement and reduces the outside air inflow to that required for passenger cabin air quality. In one embodiment, there is provided a method for reducing outside air inflow required for aircraft passenger cabin air quality using a fixed minimum outflow valve open area setpoint. In another embodiment, there is provided a method for reducing outside air inflow required for aircraft passenger cabin air quality using calculations that are repeated at regular intervals and using a mathematical function relating an outside air inflow requirement to a set of independent variables. In another embodiment, there is provided a method for calculating an aircraft fuselage leakage value and communicating the fuselage leakage value and an increase in a fuel consumption rate due to an additional amount of outside air inflow required to replenish air loss due to fuselage leakage, due to aerodynamic drag, and due to reduced thrust recovery.

An aircraft cabin air treatment system configured in accordance with the invention utilizes oxygen enriched air, which is produced as a byproduct of an onboard inert gas generation system. The oxygen enriched air is released into an environment under ambient pressure conditions, i.e., at a relatively low absolute pressure compared to the cabin pressure. The low pressure oxygen enriched air is compressed with a cabin air compressor, and the outside air is routed back into the cabin. The cabin air compressor functions to generate oxygen enriched outside air and to maintain the desired pressurization of the cabin.

System and method for enriching aircraft cabin air with oxygen from a nitrogen generation system

A thrust reverser system includes one or more actuators each having an integrated locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators with the integrated locking mechanism includes a housing, a drive shaft, and a lock. The drive shaft includes an outer surface, is rotationally mounted within the housing, and is operable, in response to the operation of the one or more motors, to rotate in a first rotational direction, to thereby move the thrust reverser to the deploy position, and a second rotational direction, to thereby move the thrust reverser to the stow position. The lock is movably mounted within the housing and is operable to move between at least a first position and a second position, and includes at least a side surface and a bottom surface. One or more gears are provided on the outer surface of the drive shaft, each of which is adapted to mesh with gears that are operably coupled to the thrust reverser. In addition, one or more protrusions extend from the outer surface of the drive shaft. Each of the protrusions includes a stop surface configured to fixedly abut the lock side surface when the lock is in the first position, and a tapered surface configured to slidingly abut the lock bottom surface when the lock is in the first position. Thus, rotation of the drive shaft in the first rotational direction is prevented and rotation of the drive shaft in the second rotational direction is allowed when the lock is in the first position.

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Everett, WA, United States of America

Kyle D Eilers