Solar Turbines Inc.

Sundstrand Corporation

Gary Paul Vavrek

Cory Patrick Muscat

James Eric Miller

William Dean Treece

Gary Lester Goldberg

Jeffrey Carl Brill

Qingxuan Michael Zhang

Sven B Sjoberg

Laura Elizabeth McDonald

Peter C Ingham

Dover M Fernandez

Paul Edward Pickett

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.

Gas turbine engine compressor rotor assembly and balancing system

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.

First stage compressor disk configured for balancing the compressor rotor assembly

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.

Stepped bearing

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.

Process for starting a gas turbine and gas turbine

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San Diego, CA, United States of America

Gary Paul Vavrek