Dwayne Michael Benson

US Patent:

6581384, Jun 24, 2003

Filed:

Dec 10, 2001

Appl. No.:

10/016512

Inventors:

Dwayne M. Benson - Tempe AZ 85281

International Classification:

F01K 734

US Classification:

60653, 60660, 60670

Abstract:

The present invention provides a process and apparatus for utilizing waste heat to power a reconfigurable thermodynamic cycle that can be used to selectively cool or heat an environmentally controlled space, such as a room or a building. The present invention also provides a method of controlling the system, while allowing large variations in the heat input energy rate. The system provides a design which reasonably balances the need to maximize efficiency, while also keeping the design cost effective.

US Patent:

6838046, Jan 4, 2005

Filed:

May 9, 2002

Appl. No.:

10/142330

Inventors:

Kenneth J. Bartone - Mahwah NJ, US
Donald M. Olson - Dover NJ, US
Dwayne M. Benson - Tempe AZ, US
John N. Tervo - Scottsdale AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B22F 300

US Classification:

419 5, 419 36, 419 54

Abstract:

Improved drying, binder evaporation, and sintering processes which may be used in conjunction with specialized sintering tools to provide for the geometrically stable sintering of large, complex, metal injection molded preform parts or flowbodies. The improved process includes a three-stage drying process, a single stage binder evaporation process, and a two-stage sintering process.

US Patent:

6892745, May 17, 2005

Filed:

Apr 10, 2002

Appl. No.:

10/119686

Inventors:

Dwayne M. Benson - Tempe AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G05D007/01

US Classification:

137 1, 137488, 137489

Abstract:

A flow control valve assembly, and a method of determining and controlling fluid flow through the valve, that is relatively simple in design, is relatively inexpensive, is accurate, and has a relatively wide measurement range. The flow control valve is relatively compact and includes all of the flow measurement and control components in a single, relatively compact assembly. Such components may include a differential pressure sensor, pressure sensor, a temperature sensor, a position sensor, and a processor. The differential pressure sensor senses differential pressure across the variable area flow orifice. The pressure sensor senses fluid pressure within the valve and supplies a fluid pressure signal. The temperature sensor senses fluid temperature and supplies a fluid temperature signal. The position sensor senses the position of the variable area flow orifice and supplies a position signal.

US Patent:

7038192, May 2, 2006

Filed:

May 23, 2002

Appl. No.:

10/155480

Inventors:

John N. Tervo - Scottsdale AZ, US
William R. Rapoport - Bridgewater NJ, US
Dwayne M. Benson - Tempe AZ, US
Devlin M. Gualtieri - Ledgewood NJ, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

G01D 5/34

US Classification:

25023113

Abstract:

An optical sensor system and method for determining the position, displacement and/or angle of a member (for example, a seal plate or valve gate) within a system (for example, a valve assembly in an aircraft turbine engine system or environmental control system). The system has, in one embodiment, a controller in communication with an encoder via a fiber optic line or similar light transmitter and the encoder further has an optically layered element. The optically layered element has at least one coating whose optical characteristics vary over the angles (or distance) of interest to provide feedback based on the position displacement and/or angle of the valve member. The system may communicate and/or be controlled by a computing system via a data communication network.

US Patent:

7231180, Jun 12, 2007

Filed:

Mar 24, 2004

Appl. No.:

10/808630

Inventors:

Dwayne M. Benson - Chandler AZ, US
Haowei Bai - Burnsville MN, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

H04B 7/00
H04B 3/36
H04B 7/15

US Classification:

455 412, 455 7, 455 111

Abstract:

A wireless communication module is used to implement an ad-hoc wireless sensor network. The wireless communication module is configured to interface with numerous and varied types of sensors and, in one particular embodiment, is used to implement an ad-hoc wireless sensor network for an aircraft engine. The modules are also configured to implement various functions to optimize ad-hoc network functionality and to minimize the electrical power dissipated by each module in the ad-hoc network.

US Patent:

7301311, Nov 27, 2007

Filed:

Feb 22, 2006

Appl. No.:

11/360116

Inventors:

Mingzhou Xu - Tucson AZ, US
Dwayne M. Benson - Chandler AZ, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

H02P 9/44

US Classification:

322 59, 322 29, 322 37, 322 46

Abstract:

A starter-generator system supplies a controllable torque to a gas turbine engine, to thereby assist in starting the gas turbine engine, by independently controlling excitation frequency and/or voltage magnitude. The starter-generator includes a multi-phase exciter stator, a rotationally mounted multi-phase exciter rotor, a multi-phase main stator, a rotationally mounted multi-phase main rotor, and an exciter controller. The rotationally mounted multi-phase exciter rotor has a plurality of exciter rotor windings wound thereon that, upon excitation thereof with a rotating electromagnetic exciter flux generated by the exciter stator, have non-rectified excitation currents induced therein. The rotationally mounted multi-phase main rotor has a plurality of main rotor windings wound thereon that are electrically connected to receive the non-rectified excitation currents induced in the exciter rotor windings and that, upon excitation thereof with a rotating electromagnetic flux and in response to the non-rectified excitation currents supplied thereto, have currents induced therein that generate a main rotor torque to thereby cause the multi-phase main rotor and the multi-phase exciter rotor to rotate. The exciter controller is electrically coupled to at least the exciter stator and is configured to selectively supply the electrical excitation thereto, to thereby selectively control the generated main rotor torque.

US Patent:

7552582, Jun 30, 2009

Filed:

Nov 29, 2005

Appl. No.:

11/290745

Inventors:

Chris D. Eick - Phoenix AZ, US
Louie T. Gaines - Phoenix AZ, US
Mitchell J. Laidlaw - Tempe AZ, US
Dwayne M. Benson - Chandler AZ, US
Larry A. Portolese - Granger IN, US
Brian L. Flaherty - Granger IN, US
Wayne T. Pearson - Tucson AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F02C 3/10

US Classification:

60 39163, 60792

Abstract:

A turbofan gas turbine propulsion engine includes a system to transfer power from the low pressure turbine to the high pressure turbine and/or extract additional load from the low pressure turbine during certain turbofan engine operational conditions. The systems include a hydrostatic power transfer system that includes a hydraulic pump and a hydraulic motor coupled to the low pressure and high pressure turbine, respectively. The systems additionally include a mechanical and electrical load shifting/loading sharing systems that use clutches and gear assemblies to share and/or shift load between the turbines.

US Patent:

7607611, Oct 27, 2009

Filed:

Jul 28, 2005

Appl. No.:

11/192625

Inventors:

Paul T. Wingett - Mesa AZ, US
Calvin C. Potter - Mesa AZ, US
Casey Hanlon - Queen Creek AZ, US
Dwayne M. Benson - Chandler AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B64C 13/14

US Classification:

244 993, 244224

Abstract:

A flight control surface actuator assembly includes a pair of flight control surface actuators and a pivot arm. One of the flight control surface actuators is coupled to a flight control surface and a static airframe structure, the other flight control surface actuator is coupled to the flight control surface and the pivot arm. The pivot arm coupled to the static airframe structure and is configured to pivot relative to the second flight control surface actuator and the static airframe structure.