Robin B Langtry

US Patent:

20110150645, Jun 23, 2011

Filed:

Dec 21, 2009

Appl. No.:

12/643554

Inventors:

Matthew D. Moore - Everett WA, US
Kelly L. Boren - Marysville WA, US
Robin B. Langtry - Burien WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64C 27/72

US Classification:

416 1, 416 87

Abstract:

A method and apparatus for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft. A diameter of the propeller is set to be at a first diameter during at least a portion of a first flight condition of the aircraft. The diameter of the propeller is set to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft.

US Patent:

20100206982, Aug 19, 2010

Filed:

Feb 13, 2009

Appl. No.:

12/371413

Inventors:

Matthew D. Moore - Everett WA, US
Kelly L. Boren - Marysville WA, US
Robin B. Langtry - Burien WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64D 27/00
F01D 1/24

US Classification:

244 62, 415 1, 415 60

Abstract:

An air vehicle propulsion system incorporates an engine core with a power shaft to drive an outer blade row. The power shaft is extends through and is supported by a counter rotation transmission unit which drives an inner blade row in counter rotational motion to the outer blade row. The counter rotation transmission unit exchanges power from the engine core with the shaft. An actuator engages the shaft for translation from a first retracted position to a second extended position.

US Patent:

20220375628, Nov 24, 2022

Filed:

Sep 2, 2021

Appl. No.:

17/766449

Inventors:

Robin Langtry - Seattle WA, US
Brian Riordan - Seattle WA, US

International Classification:

G21B 1/05

Abstract:

Systems, devices, and methods for generating an orbital confinement fusion reaction are described. An orbital confinement fusion device can include a cathodic inner electrode defining a longitudinal axis of the device. The inner electrode can include an emitter material. The orbital confinement fusion device can include an anodic outer electrode, concentric with the longitudinal axis and defining a chamber between the inner electrode and the outer electrode. The orbital confinement fusion device can also include a plurality of magnetic field generators disposed in a coaxial arrangement relative to the longitudinal axis. The plurality of magnetic field generators can be configured to form a magnetic field parallel to the longitudinal axis in the chamber.

US Patent:

20140308124, Oct 16, 2014

Filed:

Nov 13, 2013

Appl. No.:

14/079550

Inventors:

- Chicago IL, US
Kelly L. Boren - Marysville WA, US
Robin Blair Langtry - Seattle WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 11/00
B64C 11/30
B64C 11/48

US Classification:

416 1, 416 87, 416 34, 416 89

Abstract:

A method and apparatus for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft is provided. A diameter of the propeller is set to be at a first diameter during at least a portion of a first flight condition of the aircraft. The diameter of the propeller is set to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft.

US Patent:

20140151498, Jun 5, 2014

Filed:

Nov 30, 2012

Appl. No.:

13/689766

Inventors:

Robin B. Langtry - Burien WA, US
Drew A. Wetzel - Everett WA, US

International Classification:

B64C 23/00
B64C 25/16

US Classification:

244 1 N, 244100 R

Abstract:

A quiet landing gear door and methods are presented. A landing gear door comprises a trailing edge and a leading edge and is operable to deploy to a landing gear door deployed position. A door flap comprises the trailing edge and is hinged to the landing gear door. The door flap deflects toward a landing gear strut to a door flap deployed position in response to deployment of the landing gear door. A leading edge section comprises the leading edge and is coupled to the door flap. The leading edge section deflects toward the landing gear strut to a leading edge deployed position in response to deployment of the landing gear door.