General Electric Company

Charles Alan Bulgrin

Ralph Chris Bruner

Iain Robertson Kellock

Ariel Caesar-Prepena Jacala

Tagir Nigmatulin

Tagir Robert Nigmatulin

Gary Michael Itzel

Stephen William Tesh

Robert Craig Akin

A turbomachine includes a casing defining a hot gas path, and a shroud member attached to the casing. The shroud member is spaced from the casing to define a gap. The shroud member includes a first end having a first hook member provided with a first sealing surface and a second end including a second hook member provided with a second sealing surface. At least one of the first and second sealing surfaces includes a plurality of labyrinth seal elements that reduce air leakage through the gap into the hot gas path.

Shroud for a turbomachine

The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.

Turbine bucket angel wing compression seal

A uniquely configured rotating seal tooth is used in conjunction with commonly used labyrinth-type seals that provide a seal between a rotating component and a stationary component. The uniquely configured rotating seal tooth produces a compression mechanism to counter leakage flow through the labyrinth of seal teeth, thereby lessening the pressure gradient that drives leakage and reversing the direction of some of the leakage flow.

Labyrinth compression seal and turbine incorporating the same

Disclosed is a shroud for a turbomachine including at least one support structure and at least one inner shroud disposed at a gas path of a turbomachine. The at least one inner shroud and the at least one support structure have at least one gap therebetween. The at least one gap alternates between at least one restrictive gap and at least one unrestrictive gap and is capable of creating at least one pressure loss mechanism to reduce a hot gas flow in the at least one gap. Further disclosed is a turbomachine and a method for reducing ingestion of hot gas in a turbomachine.

Flow inhibitor of turbomachine shroud

A system for monitoring the displacement of turbine blades that includes a turbine blade with a cutting tooth and one or more sensor wires, each sensor wire including a severable portion, that become severed by the cutting tooth as turbine blade displacement occurs. The sensor wires may be embedded in a honeycomb, which may be an area of abradable material attached to turbine shrouds. The sensor wires may include a plurality of radial sensor wires embedded in the honeycomb at varying predetermined radial distances from a turbine rotor. The sensor wires also may include a plurality of axial sensor wires embedded in the honeycomb at varying predetermined axial locations along the length of the honeycomb.

Methods and systems for monitoring the displacement of turbine blades

A closed loop inner shroud assembly for a gas turbine. The shroud assembly may include a shroud body, a cover plate, an inlet though the cover plate to the shroud body, a serpentine passageway through the shroud body, and an outlet from the shroud body to the cover plate.

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Avon, IN, United States of America

Charles Alan Bulgrin