Alstom Technology Limited

Siemens Westinghouse Power Corporation

Doosan Heavy Industries & Construction Co., Ltd

W David Day

Adam Lee Hart

Charles A Ellis

James Page Strohl

Douglas James Dietrich

Stefan Mazzola

Stephen Wayne Fiebiger

Friedrich T Rogers

Richard Ramirez

Keith L Nickols

Walter Marussich

Adam John Fredmonski

Hyunwoo Joo

Jeff Greenberg

Samer Abdel-Wahab

Kuo-Ting Hsia

Elliot I Goodman

Gerald Raresheid

Kelly M Flannery

An airfoil for a gas turbine engine. The airfoil includes a unique cooling path for a coolant, routing the coolant through a cooling cavity, through a column of crossover passages and through a pin array near a trailing edge of the airfoil. The crossover passages produce impingement cooling and the pin array produces convective cooling. This combination of impingement cooling and convective cooling results in increased cooling of the airfoil and better aeromechanical life objectives.

Airfoil with internal crossover passages and pin array

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.

Turbine blade having improved flutter capability and increased turbine stage output

A compressor diaphragm for a gas turbine engine having improved wear capability, manufacturability, and assembly techniques is disclosed. The diaphragm includes a shiplap-type joint at an outer vane platform for connecting to adjacent vane assemblies and a clamshell-like assembly of a seal box secures and seals regions around the inner vane platform of the compressor diaphragm so as to reduce wear between the seal box and the vane assemblies. The inner platform of the diaphragm segments are fastened to each other through circumferentially-oriented fasteners at the inner diameter platform.

Compressor vane diaphragm

A crack-resistant vane segment assembly member for an industrial turbine engine is disclosed. The vane segment includes at least one internally-cooled body portion and inner and outer shroud portions. The body portions include end regions characterized by blending and transition zones that ensure heat is transferred at a non-crack-inducing rate from the shroud portions to the body portions. The vane segment assembly also includes a cooling arrangement that reduces the impact of thermal gradient-induced stresses acting at the interface between the body portions and shroud portions. The cooling arrangement cooperates with the transition and blending zones to produce synergistically-enhanced crack resistance properties.

Crack-resistance vane segment member

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Jupiter, FL, United States of America

W David Day