Alstom Technology Limited

Other

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Stephen Wayne Fiebiger

Douglas James Dietrich

Edward Len Miller

Wes Smith

Wilm Philipp Hecker

Andreas Martin Mattheiss

Reiner Jochen Digele

Gregory Edwin Vogel

Adam Lee Hart

W David Day

Christopher Charles Williams

Richard Ramirez

Jeff Tessier

Lonnie Adolphus Houck, Iii

Kuo-Ting Hsia

Megan Burke

Roy E Struble

Adam John Fredmonski

Alexander Vasili Rozendaal

Samer Abdel-Wahab

A turbine blade, airfoil, and rotor stage for a gas turbine engine is disclosed. The turbine blade, airfoil, and rotor stage each includes an uncoated airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z disclosed herein. The resulting airfoil exhibits high flutter margins, thus enabling the gas turbine engine to be operated at an increased power output while avoiding operational limitations required in known gas turbine engines.

Turbine blade having improved flutter capability and increased turbine stage output

A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased surface area over a portion of the airfoil chord length. The increased surface area allows for a greater amount of air to be taken in by the airfoil, thus increasing the air flow through the gas turbine engine.

Adjusted rotating airfoil

A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area.

Adjusted stationary airfoil

A turbine blade, airfoil configuration, and rotor stage are disclosed in which through the airfoil profile disclosed in Table 1, a modification in airfoil flutter and swirl are achieved. Through the airfoil configuration, the swirl and improved platform sealing configuration, result in the turbine blades having the airfoil profile with an increased performance output from the turbine.

A system and method of extending the useable life of a gas turbine blade is disclosed in which the gas turbine blade includes an undercut configuration designed to relieve mechanical and thermal stress imparted into the pedestal region of the airfoil trailing edge. The embodiments of the present invention include turbine blade configurations having different trailing edge undercut configurations as well as additional cooling supplied to the internal passages of the trailing edge region of the turbine blade.

Turbine blade platform undercut

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Jupiter, FL, United States of America

Stephen Wayne Fiebiger