Warren A Atkey

Address:

22601 17 Pl W, Bothell, WA 98021

Phone:

4252667838

VIN:

JF1GPAK66CH215234

Make:

SUBARU

Model:

IMPREZA

Year:

2012

US Patent:

6449963, Sep 17, 2002

Filed:

Dec 19, 2001

Appl. No.:

10/023738

Inventors:

Casey Y. K. Ng - Issaquah WA
Warren Andrew Atkey - Bothell WA
Gregg Grant LaVoy - Kirkland WA
Leigh M. Sedgwick - Mercer Island WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

F25D 900

US Classification:

62 86, 62402, 454 71, 454 74

Abstract:

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.

US Patent:

6526775, Mar 4, 2003

Filed:

Sep 14, 2001

Appl. No.:

09/952820

Inventors:

Julie F. Asfia - Huntington Beach CA
Kenneth R. Williams - Huntington Beach CA
Warren A. Atkey - Bothell WA
Charles J. Fiterman - Mukilteo WA
Steven M. Loukusa - Bothell WA
Casey Y. Ng - Sammamish WA

Assignee:

The Boeing Company - Chicago IL

International Classification:

F25D 900

US Classification:

62402, 62401

Abstract:

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.

US Patent:

7121100, Oct 17, 2006

Filed:

Sep 9, 2003

Appl. No.:

10/658001

Inventors:

Warren A. Atkey - Bothell WA, US
Charles J. Fiterman - Mukilteo WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

F25B 9/00
F25D 9/00

US Classification:

62 86, 62172, 62401, 62402

Abstract:

A thermal management system for an aircraft is provided. The aircraft includes a primary air conditioning system which compresses and cools outside air to create inside air. The inside air pressurizes the internal volume of the aircraft and ventilates a first object in the internal volume. An exhaust exhausts a portion of the inside air to allow more outside air to be drawn into the aircraft. A cooler cools a coolant which in turn controls temperature of at least two objects in the internal volume.

US Patent:

7207521, Apr 24, 2007

Filed:

Dec 12, 2005

Appl. No.:

11/301179

Inventors:

Warren A. Atkey - Bothell WA, US
Alan T. Bernier - Woodinville WA, US
Michael D. Bowman - Bellevue WA, US
Thomas A. Campbell - Seattle WA, US
Jonathan M. Cruse - Everett WA, US
Charles J. Fiterman - Mukilteo WA, US
Charles S. Meis - Renton WA, US
Casey Y. K. Ng - Sammamish WA, US
Farhad Nozari - Woodinville WA, US
Edward Zielinski - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 41/00

US Classification:

244 58

Abstract:

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.

US Patent:

7210653, May 1, 2007

Filed:

Oct 21, 2003

Appl. No.:

10/691440

Inventors:

Warren A. Atkey - Bothell WA, US
Alan T. Bernier - Woodinville WA, US
Michael D. Bowman - Bellevue WA, US
Thomas A. Campbell - Seattle WA, US
Jonathan M. Cruse - Everett WA, US
Charles J. Fiterman - Mukilteo WA, US
Charles S. Meis - Renton WA, US
Casey Y. K. Ng - Sammamish WA, US
Farhad Nozari - Woodinville WA, US
Edward Zielinski - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 41/00

US Classification:

244 58

Abstract:

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.

US Patent:

7624944, Dec 1, 2009

Filed:

Oct 26, 2006

Appl. No.:

11/553181

Inventors:

Pradip G Parikh - Renton WA, US
Warren A Atkey - Bothell WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 33/02

US Classification:

244 53B, 137 151

Abstract:

A tandem inlet apparatus for use with a high speed mobile platform, for example a commercial or military aircraft. The tandem inlet apparatus includes a Pitot inlet for feeding air to a cabin air compressor (CAC) of an air conditioning pack carried on the mobile platform. A flush heat exchanger inlet is disposed forwardly of the Pitot inlet and longitudinally aligned with the Pitot inlet, for supplying cooling air to a heat exchanger of the air conditioning pack. By locating the heat exchanger inlet forwardly and longitudinally in line with the Pitot inlet, the heat exchanger inlet is able to effectively swallow a large portion of the boundary layer, which results in a thinner boundary layer at the inlet face of the Pitot inlet. This enables a smaller throat area Pitot inlet to be used, as well as a shorter diverter height to be employed with the Pitot inlet, while still realizing an improved recovery factor (RF) performance with the Pitot inlet. The reduced height Pitot inlet also enables drag to be reduced.

US Patent:

7837541, Nov 23, 2010

Filed:

Dec 13, 2006

Appl. No.:

11/637993

Inventors:

John C. Gray - Shoreline WA, US
Kyle D. Eilers - Everett WA, US
Warren A. Atkey - Bothell WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 13/04
B64D 13/02
B64D 11/00

US Classification:

454 74, 454 70, 454 71, 454 75, 454 76, 2441185

Abstract:

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.

US Patent:

7871038, Jan 18, 2011

Filed:

May 17, 2007

Appl. No.:

11/750169

Inventors:

David R. Space - Everett WA, US
Jane V. Matera - Seattle WA, US
Warren A. Atkey - Bothell WA, US
Charles J. Fiterman - Mukilteo WA, US
John Gray - Shoreline WA, US
Timothy J. Arnaud - Everett WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 13/00

US Classification:

2441185, 454 71, 454 76

Abstract:

Systems and methods for providing airflow in an aerospace vehicle are disclosed. A system in accordance with one embodiment includes an aerospace vehicle having an interior volume with a first portion and a second portion. The system can further include an external air supply device positioned to provide supply air to the interior volume at a variable supply flow rate and a recirculation fan configured to move air positioned within the interior volume between the first portion of the interior volume and the second portion of the interior volume. The system can still further include a controller operably coupled to the recirculation fan and configured to vary a rotation speed of the recirculation fan. Variations in the rotation speed of the recirculation fan can be associated with variations in a recirculation flow rate. In selected embodiments, the system can include sensors and/or data link devices operably coupled to the controller.