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Gary Paul Vavrek

from San Diego, CA
Age ~65
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Also known as:
Gary P Vavrek, Gary Varek, Paul Vavrek Gary
Phone and address:
1729 Corsica St, San Diego, CA 92111
(858) 573-9705
Related to:
Carol VavrekJoseph Vavrek
Connected to:
Carolyn M Vavrek, 71Dennis J Vavrek, 73Gregory J Vavrek, 44Michael J Vavrek, 63Milan C Vavrek, 68William R Vavrek, 95Jeffrey S Vavricek, 61Joyce M Vavricek, 72Christopher J Vavricka, 42Lisa K Vavrik, 61

Gary Vavrek Phones & Addresses

  • 1729 Corsica St, San Diego, CA 92111 (858) 573-9705
  • 5960 Mission Center Rd, San Diego, CA 92123
  • 1729 Corsica St, San Diego, CA 92111

Work

Company: Solar turbines Position: Design engineer

Education

Degree: Associate degree or higher

Languages

English

Interests

Christianity • Cooking • Exercise • Investing • Outdoors • Electronics • Home Improvement • Reading • Music • Sports • Family Values • Travel • Movies

Emails

v***p@solarturbines.com

Industries

Oil & Energy

Resumes

Resumes

Gary Vavrek Photo 1

Design Engineer

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Location:
1729 Corsica St, San Diego, CA 92111
Industry:
Oil & Energy
Work:
Solar Turbines
Design Engineer
Interests:
Christianity
Cooking
Exercise
Investing
Outdoors
Electronics
Home Improvement
Reading
Music
Sports
Family Values
Travel
Movies
Languages:
English

Publications

Us Patents

Stepped Bearing

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US Patent:
20130195387, Aug 1, 2013
Filed:
Jan 30, 2012
Appl. No.:
13/361403
Inventors:
Jeffrey Carl Brill - Poway CA, US
Gary Paul Vavrek - San Diego CA, US
Qingxuan Michael Zhang - San Diego CA, US
Paul Edward Pickett - San Diego CA, US
International Classification:
F16C 32/06
B21D 53/10
US Classification:
384100, 2989802
Abstract:
A bearing assembly having a cylindrical outer bearing shell. The outer bearing shell including a first annular outer land, a second annular outer land, and a recess therebetween. The outer bearing shell further including a first positioning bore having a first bore diameter and a second positioning bore having a second bore diameter. The second bore diameter may be smaller than the first bore diameter. A diameter of the first annular outer land may be larger than a diameter of the second annular outer land.

First Stage Compressor Disk Configured For Balancing The Compressor Rotor Assembly

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US Patent:
20140023504, Jan 23, 2014
Filed:
Jul 17, 2012
Appl. No.:
13/551517
Inventors:
Dover M. Fernandez - Chula Vista CA, US
Cory Patrick Muscat - Poway CA, US
Gary Paul Vavrek - San Diego CA, US
James Eric Miller - El Cajon CA, US
Assignee:
Solar Turbines Incorporated - San Diego CA
International Classification:
F01D 5/10
B23P 17/00
US Classification:
416144, 2988921
Abstract:
A first stage compressor disk of a gas turbine engine includes a body. The body includes a forward end, an aft end, and an outer surface. The body also includes a plurality of forward balancing holes through the outer surface. The forward balancing holes align circumferentially about the body. The body further includes a plurality of aft balancing holes through the outer surface. The aft balancing holes align circumferentially about the body and are located aft of the forward balancing holes. The first stage compressor disk also includes a radial flange at the aft end of the body. The radial flange extends radially outward from the body. The radial flange includes slots for mounting airfoils.

Process For Starting A Gas Turbine And Gas Turbine

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US Patent:
51652234, Nov 24, 1992
Filed:
Dec 10, 1990
Appl. No.:
7/624555
Inventors:
Peter C. Ingham - El Cajon CA
Sven B. Sjoberg - San Diego CA
Gary P. Vavrek - San Diego CA
Gary L. Goldberg - San Diego CA
William D. Treece - La Mesa CA
Assignee:
Sundstrand Corporation - Rockford IL
International Classification:
F02C 726
US Classification:
60 3906
Abstract:
A method of starting a gas turbine (10) having a combustor (12) and a fuel supply system (14) supplying fuel to the combustor in accordance with the invention includes turning on a fuel valve (40) to control fuel flow to the combustor for combustion after a first starting condition (100) is reached; and cyclically turning (116) the main fuel valve on and off when a sensed exhaust gas temperature (114) initially reaches a first set temperature and continuing to cyclically turn the main fuel valve on and off until the sensed exhaust gas temperature falls to a second set temperature (118) lower than the first set temperature or until a second starting condition (102) is reached.

Gas Turbine Engine Compressor Rotor Assembly And Balancing System

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US Patent:
20140140849, May 22, 2014
Filed:
Nov 21, 2012
Appl. No.:
13/684056
Inventors:
- San Diego CA, US
Laura Elizabeth McDonald - San Diego CA, US
James Eric Miller - El Cajon CA, US
Gary Paul Vavrek - San Diego CA, US
Assignee:
Solar Turbines Incorporated - San Diego CA
International Classification:
F01D 5/02
US Classification:
416144
Abstract:
A method for balancing a compressor rotor assembly including a forward weldment () and an aft weldment () includes pre-balancing the aft weldment () of the compressor rotor assembly () with compressor disks () prior to populating the compressor disks () with circumferentially installed compressor rotor blades (). Pre-balancing the aft weldment () includes measuring a rotational balance of the aft weldment (). Pre-balancing the aft weldment () also includes determining a number of underplatform weights () needed and a location for each underplatform weight () within a circumferential slot () of one the compressor disks (). Pre-balancing the aft weldment () further includes mounting each underplatform weight () in the determined location.
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Gary Paul Vavrek from San Diego, CA, age ~65 Get Report