General Electric Company

Timothy Edward DeJoris

Michael James Dutka

Paul Griffin DeIvernois

David August Snider

Marc Edward Blohm

Jeremy Peter Latimer

Carl Gerard Schott

Joshy John

John David Stampfli

Christopher Edward LaMaster

Prakash Bavanjibhai Dalsania

Steven Eric Tomberg

Steven Mark Schirle

John Franklin Ryman

Sunil Rajagopal

Siddaraja Mallikarjuna Devangada

Aaron David Williamson

Nathan Stafford Race

Peter Gaines Cleveland

Ronald Stuart Denmark

William John Miller

Vasantharuban S

Steven Lynn Huskins

Brian Patrick Hansen

Christopher David McGowan

Narasimha K V Rao

Nandakumar A R

Venkata Siva P Chaluvadi

Nancy Chaudhary

Roger Claude Beharrysingh

Jennifer B Michenfelder

Adrian Mircea Mistreanu

Jeffrey Boyd

Jason Thomas Harrell

Bala Muralidhar Singh B

Phillip Matthew Malloy

A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, or Table VIII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Compressor stator vane airfoils

Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control a fuel flow provided to a combustor component associated with the gas turbine. A drive component may be configured to supply a rotational force to a shaft associated with the gas turbine. At least one control device may be configured to (i) direct the gas discharge component to discharge gas from the compressor component, (ii) direct the fuel control component to adjust the fuel flow, and (iii) direct the drive component to rotate the shaft.

Systems and methods for controlling the startup of a gas turbine

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S&#x2013;16S, 1R&#x2013;17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Air foil shape for a compressor blade

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Mauldin, SC, United States of America

Timothy Edward DeJoris