Jerry Allen Farstad

7870929, Jan 18, 2011

Apr 29, 2008

12/111596

Jerry E. Farstad - Seattle WA, US

The Boeing Company - Chicago IL

B64D 33/02
B64D 33/00
E04B 1/82

181214, 181292, 244538, 415119

An engine assembly, an acoustical liner and an associated fabrication method are provided to address fan blade flutter and fan noise control simultaneously within the same liner area. Fan blade flutter is therefore controlled without necessarily increasing the weight of the engine, impairing the structural integrity of the engine, or increasing the noise generated by the engine. The acoustical liner may have additional acoustical degrees of freedom which permit these seemingly competing concerns to be addressed in a complementary manner. The acoustical liner may include inner and outer barrels with the inner barrel having a perforated face sheet, a perforated back skin and a core disposed between the perforated face sheet and the back skin. The fluid communication between the core and the space between the inner and outer barrels provides additional acoustical degrees of freedom which may be utilized to reduce fan blade flutter while concurrently limiting fan blade noise.

20180355928, Dec 13, 2018

Jun 11, 2017

15/619527

- Chicago IL, US
Victoria L. Garcia - Everett WA, US
Jerry E. Farstad - Seattle WA, US
Kenneth B. Dunkelberg - Seattle WA, US
Ernest H. Kanning - Redmond WA, US
Kyle A. Peterson - Kirkland WA, US
Joel R, Will - St. Louis MO, US
Michel G. Malett - Edmonds WA, US

F16D 48/06
F16D 9/00
G07C 5/00

An example system for disconnecting a driven member from a driving member is described. The system includes a vibration detection device configured to output vibration signals indicative of vibration levels of the driven member. The system also includes a controller including at least one processor. The controller is arranged to (i) determine that a vibration signal output by the vibration detection device satisfies a threshold condition and (ii) based at least on the determination that the vibration signal satisfies the threshold condition, trigger a mechanical disconnection of the driven member from the driving member by a mechanical disconnect device.

20180316294, Nov 1, 2018

Apr 28, 2017

15/582421

- Chicago IL, US
Kamiar J. Karimi - Kirkland WA, US
Sheau-Wei J. Fu - Bellevue WA, US
Eugene V. Solodovnik - Kenmore WA, US
Paul A. Mezs - Bellevue WA, US
Jerry E. Farstad - Seattle WA, US

H02P 9/10
H03B 1/04
B64D 27/02

Systems and methods are provided for an aircraft propulsor configured to generate electrical power through a variable frequency generator in response to rotation of a gear train. The aircraft propulsor includes compensation circuitry. The aircraft propulsor further includes exciter circuitry that, when powered by an excitation signal, generates a magnetic field that interacts with a rotating variable frequency generator to generate electrical power. The exciter circuitry may be powered by at least a portion of the power generated by the variable frequency generator. The compensation circuitry may adjust the excitation signal to reduce the effect of torsional oscillation of the gear train and/or the variable frequency generator on the quality of power produced by the variable frequency generator.

20150122904, May 7, 2015

Nov 1, 2013

14/070393

- Chicago IL, US
Jerry Edward Farstad - Seattle WA, US

THE BOEING COMPANY - Chicago IL

F02K 1/76
F02K 1/62

239 1, 23926519

Systems and methods are provided that lock thrust reversers and also drive fan nozzles of an aircraft. One system includes a coupling configured to selectively engage and disengage. While engaged, the coupling is configured to rotate to drive a Variable Area Fan Nozzle (VAFN), at least a portion of which is on a translating portion of a thrust reverser of an aircraft. Furthermore, while engaged the coupling is configured to prevent displacement of the translating portion.