Brendan F Sexton, 61214 Gibbs St, Greenville, SC 29601

6390769, May 21, 2002

May 8, 2000

09/567296

Steven Sebastian Burdgick - Schenectady NY
Brendan Francis Sexton - Simpsonville SC
Iain Robertson Kellock - Simpsonville SC

General Electric Company - Schenectady NY

F04D 3100

415116, 415175

A turbine shroud cooling cavity is partitioned to define a plurality of cooling chambers for sequentially receiving cooling steam and impingement cooling of the radially inner wall of the shoud. An impingement baffle is provided in each cooling chamber for receiving the cooling media from a cooling media inlet in the case of the first chamber or from the immediately upstream chamber in the case of the second through fourth chambers and includes a plurality of impingement holes for effecting the impingement cooling of the shroud inner wall.

6402466, Jun 11, 2002

May 16, 2000

09/571814

Steven Sebastian Burdgick - Schenectady NY
Brendan Francis Sexton - Simpsonville SC

General Electric Company - Schenectady NY

F10D 1108

4151733, 415135, 415139, 4151731, 4151742, 4152092, 277630, 277631, 277637, 277644

A leaf seal assembly is secured to the trailing edge of a shroud segment for sealing between the shroud segment and the leading edge side wall of a nozzle outer band. The leaf seal includes a circumferentially elongated seal plate biased by a pair of spring clips disposed in a groove along the trailing edge of the shroud segment to maintain the seal plate in engagement with the flange on the leading edge side wall of the nozzle outer band. The leaf seal plate and spring clips receive pins tack-welded to the shroud segment to secure the leaf seal assembly in place.

6422807, Jul 23, 2002

Nov 28, 2000

09/726213

David Leach - Niskayuna NY
Iain Robertson Kellock - Clifton Park NY
Larry Wayne Plemmons - late of Hamilton OH
Cedric Chow - Schenectady NY
Brendan Francis Sexton - Clifton Park NY
Mark Stewart Schroder - Hendersonville NC

General Electric Company - Schenectady NY

F01D 1124

415 1, 415136, 4151732, 415175, 415176, 415178

A method of operating a gas turbine having inner and outer shells, with the inner shell being radially movable relative to rotor bucket tip passage in the inner shell for flowing a thermal medium. A pair of passage portions are formed in each of the aft and forward inner shell sections with axially communicating passageways between the passage portions. A thermal medium, preferably from an off-turbine site, is provided for flow through the second-stage aft inner shell section, along axial passageways along the mid-line of the inner shell to a first passage portion of the forward inner shell section. Cross-over paths flow the thermal medium from the first passage portions to second circumferentially extending passage portions of the forward inner shell section, in turn, in communication with axial passageways extending from the forward section to the aft section. A second pair of passage portions flow the thermal medium to an outlet in the aft section. By controlling the temperature of the thermal medium for flow through the aft and forward sections of the inner shell, the clearance between the shrouds and the tips of the buckets for at least the first and second stages of the turbine is controllably adjusted.

7303372, Dec 4, 2007

Nov 18, 2005

11/282348

James Anthony West - Simpsonville SC, US
William Stephen Kvasnak - Simpsonville SC, US
Brendan Francis Sexton - Simpsonville SC, US

General Electric Company - Schenectady NY

F03B 11/02

4152081, 415115, 415176

A turbine nozzle cooling sub-system is provided. The sub-system includes at least one turbine nozzle segment. The segment includes an arcuate, radially outermost endwall, an arcuate, radially innermost endwall, and at least one airfoil vane. The endwalls each include at least one open passage. The airfoil vane extends between and is coupled to the endwalls. The vane further includes a cavity, a leading edge, a trailing edge, and an airfoil vane external surface. The cavity includes an airfoil vane internal surface and a plurality of turbulators. The cavity and the open passages are in flow communication such that an airfoil cooling air stream flow is facilitated. The sub-system also includes at least one diffuser in flow communication with a compressor assembly and the segment. The diffuser includes at least one diffuser wall and cavity. The diffuser wall extends from the compressor assembly to the segment such that a channeling of the airfoil cooling air stream to the segment is facilitated.

2007024, Oct 18, 2007

Apr 18, 2006

11/406176

Stephen Graham - W. Union SC, US
Brendan Sexton - Simpsonville SC, US

B22C 9/04

164516000, 164035000, 164045000

A method for manufacturing an investment cast article is disclosed. The method comprises positioning an insert relative to a sacrificial form, the insert comprising a first portion and a second portion, the first portion being disposed inside the sacrificial form and the second portion being disposed outside the sacrificial form. The sacrificial form and the second portion of the insert are coated with a material, forming a shell surrounding the sacrificial form and the second portion of the insert. The sacrificial form is evacuated from the shell, followed by introducing molten metal into the evacuated shell, thereby providing a metal form, and resulting in the first portion of the insert being disposed and bonded inside the metal form. The shell is removed from the metal form and the second portion of the insert, thereby resulting in the metal form with the first portion of the insert disposed and bonded therein.

5779442, Jul 14, 1998

Aug 2, 1995

8/510402

Brendan F. Sexton - Clifton Park NY
Hans M. Knuijt - Niskayuna NY
Sacheverel Q. Eldrid - Saratoga Springs NY
Albert Myers - Amsterdam NY
Kyle E. Coneybeer - Schenectady NY
David Martin Johnson - Ballston Lake NY
Iain R. Kellock - Clifton Park NY

General Electric Company - Schenectady NY

F01D 1124

4151732

A turbine includes a plurality of inner shell sections mounting first and second stage nozzle and shroud portions. The inner shell sections are pinned to an outer containment shell formed of sections to preclude circumferential movement of the inner shell relative to the outer shell and enable thermal expansion and contraction of the inner shell relative to the outer shell. Positive bucket tip clearance control is afforded by passing a thermal medium about the inner shell in heat transfer relation with the shrouds about the first and second stage bucket tips, the thermal medium being provided from a source of heating/cooling fluid independent of the turbine. Access is provided to the rotor and turbine buckets by removing the outer and inner shell sections.

6079943, Jun 27, 2000

Apr 19, 1999

9/293920

Brendan F. Sexton - Clifton Park NY
Hans M. Knuijt - Niskayuna NY
Sacheverel Q. Eldrid - Saratoga Springs NY
Albert Myers - Amsterdam NY
Kyle E. Coneybeer - Schenectady NY
David Martin Johnson - Ballston Lake NY
Iain R. Kellock - Clifton Park NY

General Electric Co. - Schenectady NY

F04D 2938

415115

A turbine includes a plurality of inner shell sections mounting first and second stage nozzle and shroud portions. The inner shell sections are pinned to an outer containment shell formed of sections to preclude circumferential movement of the inner shell relative to the outer shell and enable thermal expansion and contraction of the inner shell relative to the outer shell. Positive bucket tip clearance control is afforded by passing a thermal medium about the inner shell in heat transfer relation with the shrouds about the first and second stage bucket tips, the thermal medium being provided from a source of heating/cooling fluid independent of the turbine. Access is provided to the rotor and turbine buckets by removing the outer and inner shell sections.

5685693, Nov 11, 1997

Mar 31, 1995

8/414698

Brendan F. Sexton - Clifton Park NY
Hans M. Knuijt - Niskayuna NY
Sacheverel Q. Eldrid - Saratoga Springs NY
Albert Myers - Amsterdam NY
Kyle E. Coneybeer - Schenectady NY
David Martin Johnson - Ballston Lake NY
Iain R. Kellock - Clifton Park NY

General Electric Co. - Schenectady NY

F01D 520

4151731

A turbine includes a plurality of inner shell sections mounting first and second stage nozzle and shroud portions. The inner shell sections are pinned to an outer containment shell formed of sections to preclude circumferential movement of the inner shell relative to the outer shell and enable thermal expansion and contraction of the inner shell relative to the outer shell. Positive bucket tip clearance control is afforded by passing a thermal medium about the inner shell in heat transfer relation with the shrouds about the first and second stage bucket tips, the thermal medium being provided from a source of heating/cooling fluid independent of the turbine. Access is provided to the rotor and turbine buckets by removing the outer and inner shell sections.