Solar Turbines Inc.

General Electric Company

Qingxuan Michael Zhang

Leslie John Faulder

Andrew T Meier

Theresa A Brown

Jeffrey Carl Brill

Muhammad Saqib Riaz

Gary Paul Vavrek

Paul Edward Pickett

A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper includes a width dimension, a height dimension, and a length dimension and a forward plate. The damper further includes an aft plate that is larger than the forward plate along the width and height dimension and having a lower portion including two legs extending in the height dimension. The damper also includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate.

Turbine damper

A damper for a turbine rotor assembly of a gas turbine engine includes a width dimension, a height dimension, and a length dimension, and includes a forward plate and an aft plate. The aft plate is larger than the forward plate along the width and height dimensions and includes an upper portion, which has a non-symmetric configuration and extends in the height dimension. The damper further includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate.

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 steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a tangential entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. The blade includes an exit annulus area of about 18.1 ft(1.68 m) or greater.

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San Diego, CA, United States of America

Qingxuan Michael Zhang