Daniel J Dillard

US Patent:

20120297792, Nov 29, 2012

Filed:

May 27, 2011

Appl. No.:

13/117199

Inventors:

Daniel Jackson Dillard - Greenville SC, US
Gregory Thomas Foster - Greer SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F02C 7/20
B23P 15/04

US Classification:

60796, 298892

Abstract:

A turbomachine includes a nozzle. The nozzle includes an end portion and an airfoil portion. A diaphragm is mounted to the end portion of the nozzle in a wheel space portion of the turbomachine. The diaphragm includes an external surface and an internal surface. The diaphragm also includes at least one thermocouple well receiving portion formed in one of the external surface and the internal surface. A thermocouple well is mounted in the at least one thermocouple well receiving portion. The thermocouple well includes a first end exposed to the wheel space portion of the turbomachine and a second end exposed at the internal surface of the diaphragm.

US Patent:

20130058764, Mar 7, 2013

Filed:

Sep 6, 2011

Appl. No.:

13/225895

Inventors:

Daniel Jackson DILLARD - Greenville SC, US
Gregory Thomas FOSTER - Greer SC, US
Niranjan Gokuldas PAI - Clifton Park NY, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 11/08

US Classification:

4151731

Abstract:

A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component.

US Patent:

20130086914, Apr 11, 2013

Filed:

Oct 5, 2011

Appl. No.:

13/253298

Inventors:

Kevin Weston McMahan - Greer SC, US
Daniel Jackson Dillard - Greenville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F02C 7/00

US Classification:

60753

Abstract:

A turbine system is disclosed. The turbine system includes a transition duct having 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 the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The turbine system further includes a turbine section connected to the transition duct. The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures.

US Patent:

20130111911, May 9, 2013

Filed:

Nov 9, 2011

Appl. No.:

13/292366

Inventors:

James Scott Flanagan - Simpsonville SC, US
Jeffrey Scott LeBegue - Simpsonville SC, US
Kevin Weston McMahan - Greer SC, US
Daniel Jackson Dillard - Greenville SC, US
Ronnie Ray Pentecost - Travelers Rest SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F23R 3/42

US Classification:

60752

Abstract:

A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct 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 the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a leaf seal contacting the interface member to provide a seal between the interface member and the turbine section.

US Patent:

20130111912, May 9, 2013

Filed:

Nov 9, 2011

Appl. No.:

13/292389

Inventors:

James Scott Flanagan - Simpsonville SC, US
Jeffrey Scott LeBegue - Simpsonville SC, US
Kevin Weston McMahan - Greer SC, US
Daniel Jackson Dillard - Greenville SC, US
Ronnie Ray Pentecost - Travelers Rest SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F23R 3/42

US Classification:

60752

Abstract:

A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct 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 the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a flexible metallic seal contacting the interface member to provide a seal between the interface member and the turbine section.

US Patent:

20130115048, May 9, 2013

Filed:

Nov 9, 2011

Appl. No.:

13/292351

Inventors:

James Scott Flanagan - Simpsonville SC, US
Jeffrey Scott LeBegue - Simpsonville SC, US
Kevin Weston McMahan - Greer SC, US
Daniel Jackson Dillard - Greenville SC, US
Ronnie Ray Pentecost - Travelers Rest SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F01D 11/00
F01D 25/24

US Classification:

415110

Abstract:

A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct 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 the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a convolution seal contacting the interface member to provide a seal between the interface member and the turbine section.

US Patent:

20130136592, May 30, 2013

Filed:

Nov 28, 2011

Appl. No.:

13/304720

Inventors:

Paul Kendall Smith - Simpsonville SC, US
Mary Virginia Holloway - Simpsonville SC, US
San Jason Nguyen - Simpsonville SC, US
Daniel Jackson Dillard - Greenville SC, US

International Classification:

F01D 9/02

US Classification:

4152081

Abstract:

A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

US Patent:

20130269821, Oct 17, 2013

Filed:

Apr 13, 2012

Appl. No.:

13/446831

Inventors:

Richard Martin DiCintio - Simpsonville SC, US
Patrick Benedict Melton - Horse Shoe NC, US
Daniel Jackson Dillard - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F16L 9/00
B23P 17/04

US Classification:

138177, 29592

Abstract:

Disclosed herein are methods, systems, and apparatuses for hot gas flow. In an embodiment, a transition piece comprises a surface that conforms to an approximately straight line path stretching approximately from the forward end of a transition piece to the aft end of the transition piece wherein the surface may help direct the flow of gases.