General Electric Company

William John Miller

Michael James Dutka

Bruce Clark Busbey

Daniel Ross Predmore

Carl Gerard Schott

Paul Griffin DeIvernois

John David Stampfli

Anthony Constantine Thermos

Steven Eric Tomberg

Steven Mark Schirle

Max Robert Farson

Thomas J Napolitano

John Franklin Ryman

Govindarajan Rengarajan

Nathan Stafford Race

Peter Gaines Cleveland

Ronald Stuart Denmark

James Michael Placko

William E Dixon

Christopher David McGowan

Timothy Edward DeJoris

Venkata Siva P Chaluvadi

Lynn M Naparty

Jennifer B Michenfelder

Roger Claude Beharrysingh

Jeffrey Boyd

Adrian Mircea Mistreanu

Jason Thomas Harrell

Scott Yiming Yu

A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot.

Gas turbine compressor last stage rotor blades with axial retention

A turbine or compressor blade assembly includes a blade fixed to a dovetail section attachable to a wheel. The dovetail section has a dovetail shaped to fit in a correspondingly shaped slot in the wheel. A dovetail platform serves as an interface between the blade and the dovetail. An undercut fillet radius is formed at an intersection of the dovetail platform and a dovetail pressure surface, where the undercut radius has a multi-part profile shape configured to attenuate edge of contact stresses. An additional feature is the area where the undercut radius transitions into the P-cut area at the forward end (leading edge) of the dovetail.

Undercut fillet radius for blade dovetails

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

A pair of hollow elongated insert bodies are disposed in one or more of the nozzle vane cavities of a nozzle stage of a gas turbine. Each insert body has an outer wall portion with apertures for impingement-cooling of nozzle wall portions in registration with the outer wall portion. The insert bodies are installed into the cavity separately and spreaders flex the bodies toward and to engage standoffs against wall portions of the nozzle whereby the designed impingement gap between the outer wall portions of the insert bodies and the nozzle wall portions is achieved. The spreaders are secured to the inner wall portions of the insert bodies and the bodies are secured to one another and to the nozzle vane by welding or brazing.

Gas turbine nozzle vane insert and methods of installation

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Simpsonville, SC, United States of America

William John Miller