The Boeing Company

Casey Y K Ng

Warren Andrew Atkey

Gregg Grant LaVoy

Charles Steven Meis

Thomas A Campbell

Farhad Nozari

Edward Zielinski

Alan Thomas Bernier

Charles J Fiterman

Michael D Bowman

Leigh M Sedgwick

Jonathan M Cruse

Mark Stephen Shander

John T Paterson

Michael L Drake

Richard A Cote

Howard Carter, Iii

John T Peters

Michael S Hoag

A ventilation system, aircraft, and method. The ventilation system includes a first conduit in fluid communication with a first air source in the aircraft to direct a fluid flow from the first air source. The ventilation system also includes a first branch in fluid communication with the first conduit and a first outflow point, the first branch including an active air mover to move the fluid flow toward the first outflow point. The ventilation system further includes a second branch that is separate from the first branch and in fluid communication with the first conduit and a second outflow point, the second branch including a passive air mover to move the fluid flow to toward the second outflow point.

Split ventilation systems

An air conditioning system includes a first mix manifold and a second mix manifold. A first air conditioning pack is coupled in flow communication with the first mix manifold, wherein the first air conditioning pack is configured to channel a supply of fresh air to the first mix manifold. A second air conditioning pack is coupled in flow communication with the second mix manifold, wherein the second air conditioning pack is configured to channel the supply of fresh air to the second mix manifold. The first air conditioning pack is also coupled in flow communication with the second air conditioning pack.

Air conditioning system and methods of assembling the same

An integrated environmental control system for a cargo stowage compartment in a mobile platform, for example in a commercial passenger jet aircraft. A fire detection/suppression subsystem is integrated together with an airflow management system. The airflow management system operates to circulate, and optionally to heat or cool, air withdrawn from a cargo stowage compartment of the aircraft before the air is released back into the cargo stowage compartment. A fire suppression substance, for example, Halon gas, can be discharged directly into a recirculation duct of the airflow management system, thus reducing the duct work required to achieve fire suppression and ventilation operations for the cargo stowage compartment. The integration of the fire detection/suppression and airflow management system operations reduces the overall amount, complexity and weight of the ducting employed in a cargo stowage compartment of a commercial jet aircraft. This integration also eliminates or minimizes potential integration and control issues such as smoke penetration from the cargo stowage compartment to the passenger cabin.

Integrated environmental control system for a cargo stowage compartment on a mobile platform

An electrical architecture for an aircraft is provided. The electrical architecture is particularly suitable for relatively small, compact, and lightweight aircraft. In one embodiment, the electrical architecture includes an electrical generator component coupled to the aircraft engine, and an air compression system coupled to the electrical generator component. The electrical generator component is configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the engine mechanical power, and the air compression system is configured to receive the constant frequency AC power as an input and, in response thereto, produce a pressurized air output having variable characteristics (for example, a variable flow rate or a variable air pressure).

Electrical systems architecture for an aircraft, and related operating methods

Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

Electric-based secondary power system architectures for aircraft

An air conditioning system and method are provided for use in an aircraft having a pressurized area and an unpressurized area. The air conditioning system includes an air conditioning pack located in the unpressurized area of the aircraft that conditions fresh air. The air conditioning system also includes a first air duct for directing a flow of recirculation air from the pressurized area, through a pressure bulkhead, and into the unpressurized area. A mixer is also provided and advantageously positioned in the unpressurized area for mixing the conditioned air from the air conditioning pack and the recirculation air from the pressurized area. Advantageously, the mixer obviates the need for a mix manifold and saves valuable space for passengers, cargo, and other aircraft equipment. The air conditioning system also includes a second air duct that directs the mixture of conditioned air and recirculation air from the mixer to the pressurized area of the aircraft. The air conditioning unit also includes an aerodynamic shutoff valve in line with the first air duct at the pressure bulkhead and adapted for protecting against depressurization of the pressurized area as a result of the depressurization of the first air duct.

Aircraft air conditioning system and method

Growing community of inventors

Sammamish, WA, United States of America

Casey Y K Ng