General Electric Company

Glen Arthur MacMillan

John Frederick Ackerman

Gregory Thomas Foster

Andrew Jay Skoog

William Randolph Stowell

Jane Ann Murphy

Craig Allen Bielek

Robert Walter Coign

John Ellington Greene

Alexander Stein

Thomas Walter Rentz

Aaron Gregory Winn

Thomas James Brunt

Linda Jean Farral

Catherine Procik Dulka

David Wesley Sandusky

Ravichandran Meenakshisundaram

Joseph Thomas Begovich

Dainel P Ivkovich, Jr

Leland L Lantz

Mark Olaf Lenz

Joe Timothy Brown

Craig Humanchuk

Michael B McMahan

Mark O Lenz

A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform. The airfoil body includes opposed pressure and suction sidewalls extending between a leading edge and a trailing edge of the airfoil body. The airfoil body includes a first trailing edge fillet blending into the inner platform at a trailing edge of the airfoil body.

Gas turbine nozzle trailing edge fillet

The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.

Turbine nozzle compartmentalized cooling system

The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I. The X and Y values are in inches and the Z value is in inches along the nozzle stacking axis coincident with a turbine radius. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of&#xb1;0.160 inches.

Airfoil shape for a turbine nozzle

A jet pump for a nuclear reactor includes a riser and an inlet mixer having a set of nozzles and a mixing section for receiving coolant flow from the nozzles and suction flow from an annular space between the reactor vessel and the shroud core. To minimize or eliminate electrostatic deposition of charged particulates carried by the coolant on interior wall surface of the inlet-mixer of the jet pump, and also to inhibit stress corrosion cracking, the interior wall surfaces of the nozzles and mixing section are coated with a ceramic oxide such as TiO and Ta O to thicknesses of about 0.5-1.5 microns.

Apparatus and methods for protecting a jet pump nozzle assembly and inlet-mixer

A protective coating and coating method for protecting a thermal barrier coating (TBC) on a component, such as a component of a gas turbine engine. The protective coating comprises alumina particles in a silica-containing matrix, and may be substantially homogeneous or formed of multiple layers having different compositions. The composition and relative amounts of alumina and matrix material in the protective coating enable the coating to react with molten compounds containing calcia, magnesia, alumina and/or silica (CMAS), forming a compound with a melting temperature that is significantly higher than CMAS. As such, infiltration of molten CMAS into the TBC is significantly reduced or entirely avoided.

Protective coating for thermal barrier coatings and coating method therefor

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Simpsonville, SC, United States of America

Glen Arthur MacMillan