David A Snider

US Patent:

8122725, Feb 28, 2012

Filed:

Nov 1, 2007

Appl. No.:

11/933898

Inventors:

Geoffrey David Myers - Simpsonville SC, US
David August Snider - Simpsonville SC, US
Eric Motter - Jacksonville FL, US
Daniel R. Tegel - Simpsonville SC, US
James Harper - Greenville SC, US
Stephen R. Watts - Greer SC, US
Joseph Citeno - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/22
F02C 9/26
F02C 9/00
F02C 3/00

US Classification:

60776, 60 3937, 60790, 60 39281

Abstract:

Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation.

US Patent:

8172521, May 8, 2012

Filed:

Jan 15, 2009

Appl. No.:

12/354049

Inventors:

Steven W. Tillery - Simpsonville SC, US
Mark W. Flanagan - Simpsonville SC, US
David A. Snider - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F03B 11/00

US Classification:

415180, 415 1, 415134, 4151731

Abstract:

The present application provides a compressor clearance control system for a gas turbine engine. The gas turbine engine includes a turbine producing exhaust gases and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and an extraction port for exhaust gases from the turbine. The extraction port is in communication with the casing heat exchanger so as to heat the casing of the compressor with the exhaust gases from the turbine.

US Patent:

8322145, Dec 4, 2012

Filed:

Apr 23, 2009

Appl. No.:

12/428769

Inventors:

David August Snider - Simpsonville SC, US
Timothy Andrew Healy - Simpsonville SC, US
John David Stampfli - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/00

US Classification:

60779, 60 39091, 60 3924

Abstract:

Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.

US Patent:

8356484, Jan 22, 2013

Filed:

May 1, 2009

Appl. No.:

12/434015

Inventors:

David August Snider - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/22
F02C 7/224
F02C 9/26

US Classification:

60776, 60 39281, 60736, 60734

Abstract:

According to one aspect, the subject application involves a method of controlling a transition of a gas turbine. The method includes receiving a request of the gas turbine to drive an increased load. The increased load is greater than a load being driven by the gas turbine when the request is received. The method further includes determining that a temperature of a fuel to be ignited within a combustor of the gas turbine is less than a target temperature of the fuel to be introduced into the combustor for driving the increased load. Responsive to this determination, the method also includes controlling introduction of an additive into the combustor of the gas turbine when the temperature of the fuel is less than the target temperature to establish a suitable Wobbe Index of a fuel combination to promote a substantially continuous transition of the gas turbine to drive the increased load, wherein the fuel combination includes the fuel and the additive.

US Patent:

8429917, Apr 30, 2013

Filed:

Apr 13, 2011

Appl. No.:

13/085769

Inventors:

David August Snider - Simpsonville SC, US
Willy Steve Ziminsky - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/22

US Classification:

60776, 60778

Abstract:

Fuel is delivered in a gas turbine engine including a can annular combustor array that includes at least one combustor level subset within the array supplied by an independent fuel delivery system. Fuel is supplied only to one or more subsets during a first mode of operation. Fuel is supplied to the entire array of combustors during a second mode of operation.

US Patent:

8459034, Jun 11, 2013

Filed:

May 22, 2007

Appl. No.:

11/752053

Inventors:

David August Snider - Simpsonville SC, US
Willy Steve Ziminsky - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 1/00
F02C 3/00
F02C 9/00

US Classification:

60739, 60734, 60 3937

Abstract:

A fuel delivery system for a gas turbine engine includes one or more subsets of combustors, and at least two fuel manifolds including a fuel manifold coupled to each combustor subset and configured to deliver fuel to only the subset of combustors during a predetermined gas turbine engine operating mode. A gas turbine engine assembly including a fuel delivery system and a method of operating a gas turbine engine is also described herein.

US Patent:

8510013, Aug 13, 2013

Filed:

May 4, 2009

Appl. No.:

12/434755

Inventors:

David August Snider - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 9/00
F02C 9/26
F02C 9/48
F02C 7/057

US Classification:

701100

Abstract:

A gas turbine includes a rotor, and a controller for controlling a shutdown of the gas turbine based on a target fuel-to-air ratio profile and/or controlling a rotor speed according to a target speed schedule to attain a specified duration for the shutdown. The controller controls the rotor speed by engaging the starting system to turn the rotor.

US Patent:

8538657, Sep 17, 2013

Filed:

Apr 30, 2009

Appl. No.:

12/432867

Inventors:

David August Snider - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/22

US Classification:

701100, 60734

Abstract:

Systems and methods for controlling fuel flow to a turbine component are provided. One or more parameters associated with a fuel flow to a turbine component may be monitored. The fuel flow may be modeled based at least in part on the one or more monitored parameters. The fuel flow may be adjusted to a target flow based at least in part on the modeling of the fuel flow.