MICHAEL DENNISON FOX
Pilots at Bancroft St, San Diego, CA
License number
California A3968350
Issued Date
Sep 2016
Expiration Date
Sep 2018
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
2344 Bancroft St, San Diego, CA 92104
Professional information
Director Of Global Product Marketing At Adams Golf
Position:
Director of Global Product Marketing at Adams Golf
Location:
Greater San Diego Area
Industry:
Marketing and Advertising
Work:
Adams Golf
- Plano, TX since Oct 2012
-
Director of Global Product Marketing
TaylorMade-adidas Golf
- Carlsbad, CA May 2010 - Sep 2012
-
Global Product Line Manager
TaylorMade-adidas Golf
2009 - 2010
-
Global Marketing Manager
TayloMade-adidas Golf
2006 - 2008
-
Global Marketing Project Leader
Education:
State University of New York at Albany 2001 - 2005
Construction Professional
Location:
Greater San Diego Area
Industry:
Construction
Combustor Assembly For Gas Turbine Engine
US Patent:
7975487, Jul 12, 2011
Filed:
Sep 20, 2007
Appl. No.:
11/901980
Inventors:
John F. Lockyer - San Diego CA, US
Stuart A. Greenwood - San Diego CA, US
Partha X. Dutta - San Diego CA, US
Ted E. Groocock - Chula Vista CA, US
Michael D. Fox - San Diego CA, US
Stuart A. Greenwood - San Diego CA, US
Partha X. Dutta - San Diego CA, US
Ted E. Groocock - Chula Vista CA, US
Michael D. Fox - San Diego CA, US
Assignee:
Solar Turbines Inc. - San Diego CA
International Classification:
F02C 1/00
US Classification:
60752, 60740
Abstract:
A combustor liner assembly includes a liner assembly, including a hot dome, a hot wall, and an impingement shield. The liner assembly further includes a convector assembly. The combustor liner assembly further includes an impingement dome assembly, including a ring-shaped portion defining a plurality of apertures configured to receive a plurality of fuel injectors, and a face. The ring-shaped portion and the face define an annular passage, and the face defines a plurality of apertures and a plurality of orifices. The convector assembly and the impingement dome assembly are operably coupled to one another, and the plurality of orifices of the face are configured such that the hot dome is exposed to air flowing in the annular passage of the impingement dome assembly. The combustor liner assembly is configured to provide flow communication between the annular passage of the impingement dome assembly and the plurality of fuel injectors.
Gas Turbine Engine Lubrication Fluid Barrier
US Patent:
2013021, Aug 22, 2013
Filed:
Feb 16, 2012
Appl. No.:
13/398167
Inventors:
Engward William Nielsen - El Cajon CA, US
Michael D. Fox - San Diego CA, US
Michael D. Fox - San Diego CA, US
Assignee:
Solar Turbines Incorporated - San Diego CA
International Classification:
F16J 15/16, B23P 17/00, F01D 11/02, F16J 15/447, F01D 11/00
US Classification:
277347, 29888
Abstract:
A system for forming a barrier between a lubrication oil region and an air region of a gas turbine engine comprising a lubrication oil return path, a centrifugal oil slinger on a rotating member fixed to a spool of the gas turbine engine, a spiral groove configured to directs lubrication oil toward an oil return path, a labyrinth seal, and a cavity configured to form a non-contacting seal with the spiral groove and the labyrinth seal.
Buffer Air For A Labyrinth Seal
US Patent:
2012015, Jun 21, 2012
Filed:
Dec 16, 2010
Appl. No.:
12/970451
Inventors:
ENGWARD WILLIAM NIELSEN - El Cajon CA, US
Daniel William Burnes - San Diego CA, US
Simon Ferguson Reynolds - San Diego CA, US
Michael Dennison Fox - San Diego CA, US
Daniel William Burnes - San Diego CA, US
Simon Ferguson Reynolds - San Diego CA, US
Michael Dennison Fox - San Diego CA, US
International Classification:
F02C 7/28, F04B 49/22
US Classification:
415 1, 417286, 417 53
Abstract:
A method of providing buffer air to a labyrinth seal includes operating a multi-stage compressor system having an earlier stage and a later stage such that the air pressure at the later stage is higher than the air pressure at the earlier stage. The method may further include selectively directing compressed air from one of the earlier stage or the later stage to the seal based on a parameter indicative of air pressure within the compressor system.
Data Path Processing
US Patent:
2012028, Nov 8, 2012
Filed:
May 7, 2012
Appl. No.:
13/466023
Inventors:
Michael Fox - San Diego CA, US
Faisal Mushtaq - San Jose CA, US
Karl Gierach - Irvine CA, US
Faisal Mushtaq - San Jose CA, US
Karl Gierach - Irvine CA, US
Assignee:
ORTIVA WIRELESS, INC. - La Jolla CA
International Classification:
G06F 15/16
US Classification:
709219, 709228
Abstract:
An intermediate device receives a content data message addressed to a receiving device for a communication session between a source device and the receiving device. The intermediate device substitutes adapted content data for content data of the content data message and then sends the adapted content data to the receiving device such that it appears to the receiving device that the adapted content data originated from the source device. The communication from the source device to the receiving device is intercepted by the intermediate device in a manner that is transparent to the source device and receiving device.
Method And Apparatus For Session Bandwidth Estimation And Rate Control
US Patent:
2012032, Dec 20, 2012
Filed:
Jun 15, 2012
Appl. No.:
13/525069
Inventors:
Michael Fox - San Diego CA, US
Faisal Mushtaq - San Jose CA, US
Ashwani Arya - La Jolla CA, US
Ron Garrison - San Diego CA, US
Faisal Mushtaq - San Jose CA, US
Ashwani Arya - La Jolla CA, US
Ron Garrison - San Diego CA, US
Assignee:
Ortiva Wireless, Inc. - La Jolla CA
International Classification:
G06F 15/16
US Classification:
709231, 709232
Abstract:
An intermediate device receives a content data message addressed to a receiving device for a communication session between a source device and the receiving device. The intermediate device substitutes adapted content data for content data of the content data message and then sends the adapted content data to the receiving device such that it appears to the receiving device that the adapted content data originated from the source device. The communication from the source device to the receiving device is intercepted by the intermediate device in a manner that is transparent to the source device and receiving device
Turbine Disc Ingress Prevention Method And Apparatus
US Patent:
5759012, Jun 2, 1998
Filed:
Dec 13, 1996
Appl. No.:
8/768008
Inventors:
Boris Glezer - Del Mar CA
Michael D. Fox - San Diego CA
Michael D. Fox - San Diego CA
Assignee:
Caterpillar Inc. - Peoria IL
International Classification:
F04D 2938
US Classification:
415115
Abstract:
The invention disclosed and taught herein teaches method and apparatus for restricting the ingress of hot combustion gases into the turbine disc plenum of a gas turbine engine as the hot gases flow from a turbine nozzle assembly and into the turbine blades. A jet of engine cooling air is injected into the wake region immediately behind and down stream of the nozzle assembly's stator vanes thereby reducing the static pressure recovery otherwise occurring within the wake region. Thus, a lessor amount of buffering air is required within the turbine disc plenum to prevent the ingress of hot gases thereby resulting in an increased efficiency of the engine's cooling air delivery system and over all engine performance.