The Boeing Company

Royal E Boggs

Kevin Scott Callahan

Daniel J Murray

Douglas Dean Maben

Kelly Thomas Jones

Paul Robert Tretow

Daniel F Lewinski

David S Krug

Richard Kevin Johnson

Michael L Trent

Julie K Plessner

Scott Schorn

Mohammad M Malik

Keith Douglas Choyke

Alan D Amort

John Carl Szillat

Harry H Ayubi

Michael R Madden

Douglas D Maben

Richard K Johnson

Steve G Mackin

Warren Andrew Atkey

John Rubrecht Lowell

Frederic Lacaux

Bruce Lee Drolen

Donald Ray Snow, Jr

James C Russell

Hosam E El-Gabalawy

Mehdy Barekatein

George A McEachen

Mark E Smith

Alan Grim

Timothy R North

Nels A Olson

Howard E McKenzie

Sidney D Shell

Thomas P Barrera

Brian Dale Hlavka

Mike R Madden

Rodney N Graham

David C Shangraw

Jean-Philippe Belieres

Matthew J O'Brien

Richard P Lorenz

Al R Carlo

Greg A Haack

Bradford L Moravec

Angela O'Gorman

Annika E Carden

David A Adkins

Alfred R Carlo

Craig G Robotham

Kevin S Callahan

Brian D Hlavka

Kelly T Jones

Frederic P Lacaux

Bruce L Drolen

Matthew J O'brien

George A Mceachen

Nels S Olson

Howard E Mckenzie

John R Lowell

Auxiliary power systems, aircraft including the same, and related methods are disclosed herein. In one embodiment, the aircraft includes an airframe and an auxiliary power system that includes an auxiliary power unit (APU), an APU controller, and a bleed air temperature (BAT) sensor. The APU defines a bleed air outlet and is configured to regulate a BAT of a bleed air flow generated by the auxiliary power unit. The BAT sensor is positioned at a remote BAT location that is outside the bleed air outlet of the APU. In another embodiment, the auxiliary power system includes an APU configured to generate a bleed air flow, an APU controller configured to receive and transmit signals, and a BAT sensor suite configured to measure the BAT of the bleed air flow and to generate a BAT signal that is based, at least in part, on the BAT.

Auxiliary power systems, aircraft including the same, and related methods

Auxiliary power systems, aircraft including the same, and related methods. An auxiliary power system comprises an auxiliary power unit (APU) controller and an APU with an air intake, a powerhead, and a load compressor stage. The load compressor stage includes a flow regulator assembly, a load compressor, and a bleed air temperature (BAT) sensor for generating a BAT signal. The APU controller regulates a flow rate of a load compressor airflow through the load compressor based on the BAT signal. A method of utilizing an auxiliary power system includes compressing a load compressor airflow to generate a bleed air flow, measuring the BAT with a BAT sensor, generating a BAT signal based on the BAT, transmitting the BAT signal to an APU controller, generating a flow regulator command with the APU controller, transmitting the flow regulator command to a flow regulator assembly, and controlling a flow regulator assembly.

A method for controlling compressed air sent to pneumatic systems. The method includes acquiring a set of performance demands for each of a plurality of pneumatic systems in a platform, where the performance demands indicate needs for the compressed air supplied to each of the pneumatic systems, identifying a maximum allowable air discharge temperature limit of a variable speed air compressor configured to supply compressed air to the pneumatic systems, and controlling an operation of the compressor to supply the compressed air to the pneumatic systems to meet the acquired performance demands for at least one of the pneumatic systems while operating the compressor below the maximum allowable air discharge temperature limit.

Compressed air system

An air distribution system and method for an air conditioning system in an air vehicle are provided. The air distribution system has lower lobe ducts below a cabin floor of a cabin of the air vehicle. Each lower lobe duct is in fluid communication with a mix manifold coupled to AC packs. The air distribution system further has sidewall riser ducts, outboard manifold ducts, a recirculation air duct, and either recirculation downer ducts, or branch recirculation ducts coupled to the recirculation air duct. The air distribution system has a conditioned air flow, distributed to either the lower lobe ducts, or the lower lobe ducts and then the sidewall riser ducts; has a recirculated air flow, distributed to either the recirculation downer ducts or branch recirculation ducts; and has a mixed air flow distributed to the outboard manifold ducts, and into the cabin.

Air distribution system and method for an air conditioning system in an air vehicle

An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.

Aircraft including mitigation system for rechargeable batteries

An apparatus comprises a rechargeable battery susceptible to thermal runaway, and a metal enclosure for the battery. The enclosure is configured to mitigate battery failure consequences resulting from thermal runaway.

Enclosure for rechargeable batteries

An inerting system () for an aircraft () includes one or more fuel tank circuits () associated with fuel tanks (). An air source () supplies pressurized air. A heat exchanger () cools the pressurized air. An air separation module () is in fluid communication with the heat exchanger () and separates inerting gas from the pressurized air. A controller () controls flow of the inerting gas from the air separation module () to the fuel tanks ().

Commercial aircraft on-board inerting system

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North Charleston, SC, United States of America

Royal E Boggs