General Electric Company

Christophe Jude Day

Anthony Paul Greenwood

Thomas Alan Wall

Kenneth Edward Seitzer

Michael Alan Hile

Carol Anne Venn

James Thompson

Jonathan Russell Ratzlaff

Fei Huang

Mark Joseph Gleason

Clifford Edward Allen, Jr

Jeremy Kevin Payne

Mark Douglas Ehresman

Michael Joseph Gambone

Christopher Francis Poranski

Jeffrey Scott Laubenthal

James L Mazuk

Vernon Leroy Smith

John Wilbur Acree

Anthony James Bailey

Jack Przybylski

Satyambabu Kalyani

Michael Alan Zupancic

Kevin William Caldwell

Clifford Edward Allen

An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Turbine engine inducer assembly

An apparatus and method for a turbine engine having an engine core. A casing can contain a compressor section, a combustor section and a turbine section in axial flow arrangement. An air conduit can extend at least partially between the compressor section and the turbine section. A compliant interface can include a nut and a biasing device mount the air conduit to the casing.

Turbine engine conduit interface

In one aspect the present subject matter is directed to an igniter assembly for a gas turbine engine. The igniter assembly includes an outer housing and an igniter tube that extends radially through the outer housing. The igniter tube includes an ignition tip, a nut coupled to the igniter tube and disposed at least partially within the outer housing and a biasing member that extends between an inner surface of a top portion of the outer housing and the nut. A flexible seal extends radially inwardly from a bottom side of the nut and a retention collar is coupled to the igniter tube proximate to the ignition tip. The retention collar is configured to couple to a mounting ring connected to an outer liner of a combustor for the gas turbine engine.

Igniter assembly for a gas turbine engine

An arcuate panel for a thermal control assembly includes an arcuate panel base, at least one axially extending panel header sealingly attached to a radially outwardly facing surface of the panel base, a plenum therebetween, one or more spray tubes or channels depending radially inwardly from the panel base and in fluid communication with the plenum, and radially outwardly biasing spring means mounted on or attached to the radially inwardly facing surface of the panel base. The panel may include at least one set of clockwise and counter-clockwise hinge wings attached to clockwise and counter-clockwise ends of the panel base, axial positioning, and circumferential positioning. The axial positioning may include a circular row of spring clips mounted on the panel base. A hoop of arcuate panels pivotably attached by hinges may encircle a portion of a casing compressing leaf springs against rings of the casing.

Gas turbine engine spring mounted manifold

A method for making a test specimen includes machining out a chordal core from an annular forging and machining the specimen symmetrical about a chordal axis of the core. A linear cutting tool such as a wire EDM machine is used for the machining which includes at least a partially cylindrical cutting about the chordal axis with the linear cutting tool. A copper or brass tubular EDM electrode may be used. The chordal core may be machined from fat of the forging. The test specimen may have with a gauge section diameter in a range of 0.1-0.5 inches. The EDM process may include directing jets of machining fluid or dielectric in up and down along a cutting portion of an EDM wire of the EDM machine or performing the EDM process in a tank of machining fluid or dielectric with the annular forging submerged in the fluid or dielectric.

Extraction of chordal test specimens from forgings

A dovetail preform having linearly extending hooks and slots is finished to provide arcuate slots and hooks for securement of the finished bucket dovetail to a correspondingly-shaped dovetail of a turbine wheel. An electrode having the general configuration of the dovetail with arcuate hooks and slots is provided. After relatively linearly displacing the electrode and preform, disposed in an electrolytic solution, to insert the electrode hooks into the slots of the preform, the electrode and preform are relatively displaced in a direction normal to the direction of the linear slots and hooks of the preform such that metal of the preform is burned to form arcuate finished surfaces along the hooks of the preform. In another embodiment, the electrode has a dovetail configuration as a negative of the finished dovetail for the bucket and passes along an arc of a circle through the linearly extending slots of the preform to form the opposed concave and convex surfaces of the finished bucket dovetail.

Methods for forming dovetails for turbine buckets

Growing community of inventors

Hamilton, OH, United States of America

Christophe Jude Day