Glen Arthur Macmillan

US Patent:

6633623, Oct 14, 2003

Filed:

Nov 29, 2000

Appl. No.:

09/723276

Inventors:

Catherine P. Dulka - West Chester PA
John F. Ackerman - Laramie WY
David W. Sandusky - Los Gatos CA
Mark O. Lenz - San Jose CA
Leland L. Lantz - Wayne SC
Michael B. McMahan - Glenmore PA
Glen Arthur MacMillan - Simpsonville SC

Assignee:

General Electric Company - Schenectady NY

International Classification:

G21C 900

US Classification:

376306, 376305, 376372, 417195, 417157, 239591, 239589, 239600, 428312

Abstract:

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.

US Patent:

7527473, May 5, 2009

Filed:

Oct 26, 2006

Appl. No.:

11/586766

Inventors:

Craig Humanchuk - Simpsonville SC, US
Craig Bielek - Simpsonville SC, US
Linda Farral - Greenville SC, US
Glen MacMillan - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 9/04

US Classification:

415191, 415193, 4152082, 4152091, 4152101, 4152112

Abstract:

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 of0. 160 inches.

US Patent:

20120128472, May 24, 2012

Filed:

Nov 23, 2010

Appl. No.:

12/952922

Inventors:

Anshuman Singh - Simpsonville SC, US
Glen Arthur MacMillan - Simpsonville SC, US
Charles Andrew Malinowski - Mauldin SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 1/02
F01D 25/12

US Classification:

415178, 415202

Abstract:

A turbomachine nozzle segment includes a vane having a first end extending to a second end through an airfoil portion. An outer member is positioned at the first end of the vane. The outer member includes a mounting element configured and disposed to secure the turbomachine nozzle segment to a turbomachine. An inner member is positioned at the second end of the vane. The inner member includes an upstream section and a downstream section. An upstream diaphragm member extends substantially radially outwardly from the inner member at the upstream section, and a downstream diaphragm member extends substantially radially outwardly from the inner member at the downstream section. Each of the upstream diaphragm member and down stream member includes an outer surface and an inner surface. One of the outer surface and inner surface of each of the upstream diaphragm member and downstream diaphragm member includes a cartridge mounting member.

US Patent:

20130177384, Jul 11, 2013

Filed:

Jan 9, 2012

Appl. No.:

13/345781

Inventors:

Robert Walter Coign - Piedmont SC, US
Gregory Thomas Foster - Greer SC, US
Ravichandran Meenakshisundaram - Greenville SC, US
Glen Arthur MacMillan - Simpsonville SC, US
Aaron Gregory Winn - Piedmont SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 9/02
F01D 25/12

US Classification:

415 1, 415115

Abstract:

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.

US Patent:

6465090, Oct 15, 2002

Filed:

Oct 17, 2000

Appl. No.:

09/690860

Inventors:

William R. Stowell - Rising Sun IN
Joseph Thomas Begovich - West Chester OH
Thomas Walter Rentz - Cincinnati OH
Glen A. MacMillan - Simpsonville SC
John Greene - Simpsonsville SC
Jane Ann Murphy - Middletown OH
Andrew J. Skoog - West Chester OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F03B 312

US Classification:

428325, 428323, 428332, 428469, 428450, 428699, 428702, 416241 B

Abstract:

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.

US Patent:

20150110616, Apr 23, 2015

Filed:

Oct 23, 2013

Appl. No.:

14/061095

Inventors:

- SCHENECTADY NY, US
Glen Arthur MACMILLAN - Greenville SC, US
Thomas BRUNT - Greenville SC, US
Joe Timothy BROWN - Greenville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - SCHENECTADY NY

International Classification:

F01D 9/02

US Classification:

4152081

Abstract:

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.