Ariel H Lomas

US Patent:

20130042668, Feb 21, 2013

Filed:

Aug 16, 2011

Appl. No.:

13/210849

Inventors:

David Richard Johns - Simpsonville SC, US
Ariel Harter Lomas - Simpsonville SC, US
James Stewart Phillips - Easley SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

G01N 25/00

US Classification:

73 2505

Abstract:

A hot gas path measurement apparatus is provided and includes a substrate having a coating applied on a surface thereof such that the coating is interposed between the substrate and a hot gas path; and a measurement device fixed in a recess formed in the substrate, the measurement device including a sensor, and a holder configured to position the sensor in an alignment condition with a plane of a surface of the coating or at least partially within a span of the hot gas path.

US Patent:

20150118014, Apr 30, 2015

Filed:

Oct 29, 2013

Appl. No.:

14/066225

Inventors:

- Schenectady NY, US
Scott Alan Kopcho - Greenville SC, US
Robert Thomas Thatcher - Greenville SC, US
Ariel Harter Lomas - Greenville SC, US
Bradley Steven Carey - Greenville SC, US
Clive Andrew Morgan - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 9/28
G05B 15/02

US Classification:

415 1, 415 47, 700287

Abstract:

The systems, methods, and computer-readable media set a gas turbine firing temperature to maintain gas turbine metal surface temperatures. In certain embodiments, a method of setting a gas turbine firing temperature is disclosed that may comprise determining a critical temperature at which ash from ash bearing fuels becomes unremovable by conventional water wash procedures, determining hot gas path component metal surface temperatures, and adjusting the gas turbine firing temperature to maintain the metal surface temperatures below the critical temperature. Determining the metal surface temperatures may be based at least in part on measured gas turbine parameters, gas turbine performance models, and empirical models.

US Patent:

20150075265, Mar 19, 2015

Filed:

Sep 17, 2014

Appl. No.:

14/488693

Inventors:

- Schenectady NY, US
Thomas John Freeman - Canton GA, US
Robert Flynn - Glasgow, GB
Ariel Harter Lomas - Simpsonville SC, US
Bradley Steven Carey - Greer SC, US

International Classification:

G01M 15/14
G01B 5/008

US Classification:

7311201, 33503

Abstract:

Measurement devices and methods for evaluating clearances between adjacent components in turbomachines are provided. A measurement device may include a tool and a controller. The tool and controller may determine the clearance by measuring the distance between the adjacent components. The controller may compare the clearance to a predetermined engineering clearance limit and/or a previously measured clearance. A method may include measuring the clearance with a device which includes a controller. The method may further include comparing the clearance in the controller to a predetermined engineering clearance limit and/or a previously measured clearance.

US Patent:

20140260287, Sep 18, 2014

Filed:

Mar 15, 2013

Appl. No.:

13/832270

Inventors:

- Schenectady NY, US
Bradley Steven Carey - Greer SC, US
Paul Burchell Glaser - Albany NY, US
Ariel Harter Lomas - Simpsonville SC, US
Andrew Mitchell Rodwell - Greenville SC, US

Assignee:

GENERAL ELECTRIC COMPANY - Schenectady NY

International Classification:

F02C 7/30
G01N 25/02
F02C 9/00

US Classification:

60772, 60 3924, 374 27

Abstract:

Gas turbine firing temperature optimization based on a measured sulfur content of a fuel supply of the gas turbine system is provided. In one embodiment, a system includes a diagnostic system configured to determine a maximum firing temperature for a combustor of a gas turbine system. The diagnostic system may determine the maximum firing temperature based on a predetermined sulfur content to maximum firing temperature correlation and an actual sulfur content of a fuel supplied to the combustor. The diagnostic system may also be configured to provide an indicator for a change in an actual firing temperature in the combustor of the gas turbine system. The diagnostic system may provide the indicator in response to the determined maximum firing temperature differing from the actual firing temperature of the combustor of the gas turbine system.