General Electric Company

Kenneth Lorenzo Parks

Hui Kuang

Anthony John Dean

Osman Saim Dinc

David A Williams

Gregory Scot Corman

George Ernest Reluzco

Mark Stewart Schroder

Thomas Raymond Farrell

Edward Lee McGrath

Raymond Edward Chupp

Thomas Bradley Beddard

Benjamin Erick Baker

Chris Basil Jiomacas

Gayle Hobbs Goetze

Gilbert Joseph Dean

John Augustus Halbohm

Rachel Elizabeth Kyano

A core for use in casting a gas turbine bucket includes a solid, curved upper body portion and a pair of co-planar legs extending downwardly from the solid, curved upper body portions. The pair of legs are separated by an elongated open slot extending from a lower end of the core upwardly more than half a height dimension of the core, into the upper body portion. A pair of axially aligned pegs project in axially opposite directions from opposite sides of the solid, curved upper body portion, perpendicular to and above the elongated slot but spaced from an upper edge of the solid, curved upper body portion. The pair of pegs lie substantially in a plane containing the co-planar legs, and in a radial direction, the pegs are closer to the elongated slot than to the upper edge.

Perimeter-cooled stage 1 bucket core stabilizing device and related method

A gas turbine having a metallic outer shroud and a ceramic inner shroud. The ceramic inner shroud being secured to the outer shroud by hooks carried on the outer shroud. The hooks on the outer shroud being coated with TBC. A pin and spring system being provided to hold the ceramic inner shroud against the forward hook of the outer shroud. An anti-rotation pin being provided to trap the aft bend of the ceramic inner shroud against the aft hook of the outer shroud. The gas turbine further including a damping spring and pin system, disposed between a heat shield, within the outer shroud, and the ceramic inner shroud, to provide damping of the inner shroud.

Ceramic turbine shroud

The trailing edge of a turbine bucket is cut back from a root portion of the bucket to a location 50-75% of the span of the bucket. The cutback portion is tapered, forming an obtuse angle between it and the remaining original portion of the trailing edge outwardly of the cutback portion. A new conical section is thus created of a slightly larger conical and, hence, transverse configuration. The crack is removed upon removal of the material forming the cutback. With the edges of the recreated conical section surrounded, the cutback portion assumes a scalloped configuration with the exit openings of the cooling holes as seen from opposite sides of the bucket.

Method of forming a trailing edge cutback for a turbine bucket

A brush seal assembly is radially and axially repositionable relative to stationary and rotating components. Shim packs whose thickness can be reduced by peeling adhesively attached foil layers from the shim packs are used to provide both axial and radial repositioning. In another form, a plurality of set screws may be threaded into a mounting member for the brush seal assembly to controllably space the brush seal from the rotating component. In a further form, an eccentric cam is rotated to reposition the brush seal assembly radially inwardly or outwardly with shim packs being used to reposition the brush seal in an axial direction.

Repositionable brush seal for turbomachinery

Growing community of inventors

Simpsonville, SC, United States of America

Kenneth Lorenzo Parks