General Electric Company

The Penn State Research Foundation

Ge Infrastructure Technology, LLC

Carl Gerard Schott

Rahul Jaikaran Chillar

Douglas Scott Byrd

Sam David Draper

Amit Toprani

Kenneth Damon Black

Gunnar Leif Siden

Kevin Wayne Kinzie

Kenneth Neil Whaling

John Joseph Lynch

David W Ball

Kevin Weston McMahan

Stanley Kevin Widener

Michael James Dutka

Dean Matthew Erickson

Douglas Frank Beadie

Matthew Stephen Casavant

Marc Edward Blohm

Sylvain Pierre

John David Stampfli

Paul Griffin DeIvernois

Anthony Constantine Thermos

Steven Eric Tomberg

Steven Mark Schirle

Clint Luigie Ingram

John Franklin Ryman

Nathan Stafford Race

Peter Gaines Cleveland

Iris Ziqin Hu

Ronald Stuart Denmark

William John Miller

Venkata Siva Chaluvadi

Christopher David McGowan

Timothy Edward DeJoris

Khoa Dang Cao

Allen L Treaster

Michael J Beam

Gerald Wilson Grove

Roger Claude Beharrysingh

Jennifer B Michenfelder

Anil Salunkhe

Venkata Siva P Chaluvadi

Adrian Mircea Mistreanu

Jeffrey Boyd

Jason Thomas Harrell

Timothy A Brungart

Mukesh Marutrao Yelmule

Lane Porter

Matthew S Kight

A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.

Gas turbomachine diffuser assembly with radial flow splitters

A diffuser strut fairing includes a top portion, a bottom portion, a pressure side portion, a suction side portion, an inner surface and an outer surface. The pressure side portion and the suction side portion extend between the top portion and the bottom portion. The exhaust diffuser strut faring further includes a flow manifold that is at least partially defined between the pressure side portion and the suction side portion. A plurality of openings is disposed along the suction side portion and are in fluid communication with the flow manifold.

Gas turbine exhaust diffuser strut fairing having flow manifold and suction side openings

Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour.

Transition duct assembly with modified trailing edge in turbine system

A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.

Methods and apparatus for assembling a low noise ejector motive nozzle

An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.

Inlet system for an EGR system

A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.

Slotted compressor diffuser and related method

A splitter is provided for improving a pressure recovery of a compressor discharge casing (CDC) by substantially aligning a fluid vortex about a longitudinal axis of a gas turbine engine. The CDC includes an annular wall that extends generally axially along at least a portion of the CDC. The CDC is configured to house a first combustor and a second combustor. The splitter extends from the annular wall between the first and second combustors. The splitter includes a first surface that is configured to direct fluid towards the first combustor and a second surface that is configured to direct fluid towards the second combustor.

Method and system for providing a splitter to improve the recovery of compressor discharge casing

A diffuser for a turbine engine, including an annular casing to seal compressor discharge air and struts attached to the casing to delimit an annular array of intra-strut regions, is provided and includes a ring portion, including a ring shaped annular body with a forward face disposed on a forward side thereof, the ring portion being supportable by one or more of the struts, and a splitter portion, including a ring shaped annular body with an aft face disposed on an aft side thereof to mate with the forward face of the ring portion body, the splitter portion further including a lead edge, on a forward side of the splitter portion body, which is extendable into a flow path of the compressor discharge air to split the flow path into secondary flow paths defined radially outside of and inside of the splitter portion body.

Compressor diffuser

An inlet guide vane having a nominal profile substantially in accordance with Cartesian coordinate values of x, y, and z set forth in TABLE 1 reduces vibration of engine components at various operating conditions. A scaling factor can be applied to the values to make the airfoil larger or smaller. The TABLE 1 x and y values are distances in inches within a tolerance which, when connected by smooth curves, define airfoil profile sections at each distance z in inches, the profile sections being joined smoothly to form a complete airfoil shape. The tolerance in an embodiment is up to about 0.16 inches.

Inlet guide vane

Growing community of inventors

Simpsonville, SC, United States of America

Carl Gerard Schott