General Electric Company

Ronald Stuart Denmark

Michael James Dutka

Carl Gerard Schott

Paul Griffin DeIvernois

John David Stampfli

Nicholas Francis Martin

David Randolph Spracher

Steven Eric Tomberg

Steven Mark Schirle

Sanjeev Kumar Jha

Michael Thomas Hudson

John Franklin Ryman

John David Memmer

Nathan Stafford Race

Peter Gaines Cleveland

Richard Francis Gutta

William John Miller

Srinivas Ravi

Christopher David McGowan

Timothy Edward DeJoris

Vasantharuban Subramanian

Venkata Siva P Chaluvadi

Ashok Kumar Haveri Murigeppa

Prem Navin Dhayanandam

Roger Claude Beharrysingh

Yagnesh Dalpatbhai Hathiwala

Jennifer B Michenfelder

Wilton Andrew Green, Jr

Paul Anthony Santos

Adrian Mircea Mistreanu

Jeffrey Boyd

Jason Thomas Harrell

An airfoil and shroud assembly includes an airfoil including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base. A shroud includes an opening configured to receive the base of the tenon. A nut is configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil to couple the shroud to the airfoil.

Airfoil shroud assembly using tenon with externally threaded stud and nut

A method of repairing a turbomachine rotor wheel including a first outer circumferential edge extending to a second outer circumferential edge through a circumferential surface, a dovetail interface extending across the outer circumferential surface between the first and second outer circumferential edges, and a bucket mounted to the dovetail interface includes identifying a defect on one of the first and second outer circumferential edges of the rotor wheel adjacent the bucket, securing the bucket in the dovetail interface to substantially constrain axial movement, and removing a portion of the one of the first and second outer circumferential edges to remove the defect.

Method and apparatus to repair a turbomachine rotor wheel

A stator ring for use in a compressor of a gas turbine engine and a method of assembling the stator ring are provided. The stator ring includes a first plurality of segments that includes a first segment including a first circumferential end formed with a first cut and a second circumferential end formed with a second cut that is complementary to the first cut, wherein the first plurality of segments are configured to be circumferentially-coupled together, and a second plurality of segments that includes a second segment including a first circumferential end with a third cut and a second circumferential end with a fourth cut that is complementary to the third cut, wherein the second plurality of segments are configured to be circumferentially-coupled together.

Stator ring configuration

A stator blade segment for a compressor includes an inner ring segment and an outer ring segment and a plurality of stator blades extending radially between the inner and outer ring segments, the stator blade secured to the outer ring at a shank portion of the blade and loosely held in a slot in the inner ring segment at a tip portion of the blade, the slot formed to substantially match a cross-sectional profile of the tip portion of the blade but sized to create a clearance between the tip portion and the slot.

Compressor stator floating tip shroud and related method

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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Simpsonville, SC, United States of America

Ronald Stuart Denmark