General Electric Company

Kevin Lee Worley

Stephen Paul Wassynger

Gregory Thomas Foster

William Scott Zemitis

Melbourne James Myers

Robert Walter Coign

Richard Ryan Pilson

Spencer Aaron Kareff

David John Humanchuk

Christopher Michael Penny

Benjamin Arnette Lagrange

Felipe Roman-Morales

Nathan Stafford Race

Raymond Joseph Lecuyer

Poorna Krishnakumar

Spencer A Kareff

A method of modifying a shank of a turbine blade from an initial profile to an undercut profile includes removing a first portion of material from an underside of a downstream angel wing of the turbine blade. The downstream angel wing extends axially from a downstream cover plate of the shank. The method also includes removing a second portion of material from a generally axially-extending portion of the downstream cover plate adjacent a dovetail of the turbine blade.

Turbine blades having shank features and methods of fabricating the same

A damper pin for damping adjacent turbine blades coupled to a rotor disk comprises a first elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the first elongated body. The first elongated body defines a slot that extends axially therethrough. The damper pin further includes a second elongated body having a generally arcuate top portion. The second elongated body is at least partially disposed within the slot and is slideably engaged in an axial direction with the first elongated body.

Damper pin having elongated bodies for damping adjacent turbine blades

Arcuate seal layers conforming with one another are disposed between inner retainer segments and inner rails of nozzle segments of a gas turbine. The layers are secured to the aft axial face of the segments and project radially outwardly to seal against the forward axial faces of the rails. The rear axial faces of the rails have chordal seals for sealing against the forward axial faces of the support rings. The seal layers have radial cuts misaligned with one another in an axial direction to preclude leakage flows through gaps formed by the cuts. Arcuate spacers are staggered circumferentially with the arcuate retainer segments whereby an intermediate pressure plenum is formed between the finger seals and chordal seals.

System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor

The dovetails of turbine buckets are received in dovetail grooves between circumferentially adjacent wheelposts on a turbine wheel of a gas turbine rotor. The wheel and a spacer are rabbeted one to the other and an axially forwardly extending projection on each bucket dovetail is undercut to space the bucket projection from the outer rim of the spacer eliminating stress on the bucket from the spacer. A cavity is formed between radially outwardly converging wall portions of the spacer and end faces of the wheelposts and bucket dovetails. An annular seal wire conforms and seals between the spacer wall portions and end faces of the wheelposts and bucket dovetails in response to centrifugal forces during turbine operation.

Rotating seal arrangement for turbine bucket cooling circuits

A damper pin is disposed between adjacent buckets of a turbine rotor. A first bucket has circumferentially extending supports defining a pair of axially spaced surfaces on which a damper pin rests in a cold condition of the turbine. The adjacent bucket is undercut adjacent its platform to provide an angled surface overlying a generally correspondingly angled surface of the damper pin. The damper pin fits slightly loose within the recess and, upon turbine rotation at speed, the angled surfaces of the damper pin and recess cooperate to bias the damper pin against the first bucket whereby the damper pin engages both buckets and dissipates vibratory action.

Vibration damper assembly for the buckets of a turbine

Growing community of inventors

Easley, SC, United States of America

Kevin Lee Worley