Mark W Flanagan

US Patent:

8061971, Nov 22, 2011

Filed:

Sep 12, 2008

Appl. No.:

12/209832

Inventors:

Eric Roush - Simpsonville SC, US
Mark W. Flanagan - Simpsonville SC, US
Ian David Wilson - Simpsonville SC, US
George Frey - Houston TX, US
John Raymond Hess - Seneca SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 25/26

US Classification:

415108, 415116

Abstract:

A cooling system for a turbine includes a blower configured to generate a cooling gas flow to be passed through a rotor cavity of the turbine; piping configured to deliver the cooling gas flow to the turbine; and at least one valve configured to control the cooling gas flow. The piping is operatively connected to the rotor of the turbine. A method of cooling a turbine includes generating a cooling gas flow with a blower to be passed through a rotor cavity of the turbine; and delivering the cooling gas flow to the turbine.

US Patent:

8128353, Mar 6, 2012

Filed:

Sep 30, 2008

Appl. No.:

12/285242

Inventors:

Mark W. Flanagan - Greenville SC, US
Christopher P. Cox - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 25/14
F01D 25/28

US Classification:

4151821, 4152151, 4152141, 415 13

Abstract:

A method and apparatus for controlling distortion in the casing of a gas turbine are disclosed. The method uses a split in the flange ID underneath “false” flanges to tune the hoop stiffness of the casing to match the stiffness and behavior of the bolted joint. By matching the hoop carrying capability and load path of the split-line flange, as well as the thermal mass effect, the distortion can be channeled to a higher order distortion mode that can evenly distribute the deflection and approach a pure circular form.

US Patent:

8152457, Apr 10, 2012

Filed:

Jan 15, 2009

Appl. No.:

12/354066

Inventors:

Mark W. Flanagan - Simpsonville SC, US
Steven W. Tillery - Simpsonville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/08
F01D 5/18
F01D 25/08
F04D 29/58

US Classification:

415177, 4151731, 415180

Abstract:

The present application provides a compressor clearance control system for a gas turbine engine having an oil recirculation system with a flow of oil therein 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 a conduit in communication with the casing heat exchanger and the oil recirculation system so as to heat the casing of the compressor with the flow of oil from the oil recirculation system.

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:

8177501, May 15, 2012

Filed:

Jan 8, 2009

Appl. No.:

12/350386

Inventors:

Mark W. Flanagan - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 1/02
F01D 9/00
F03B 1/00
F03B 11/02
F03B 3/16
F03D 1/04
F03D 3/04
F03D 5/00
F04D 29/44
F04D 29/54

US Classification:

4152082

Abstract:

A turbine power generation system, comprising a stator including a shroud and a rotor rotatably situated within the shroud, wherein the shroud is structured such that the inner diameter of the inner surface of the shroud reduces when the inner surface is exposed to a thermal load. The reduction of the inner diameter allows a minimum blade-casing clearance to be achieved during steady-state operation instead of during transient operations. Blade-casing clearance is configured to be greatest at when the engine is in a cold, stationary position. The clearance is further configured to decrease as thermal load increases until a steady-state, thermal equilibrium is achieved. The clearance grows during shutdown as the stator and rotor begin to cool.

US Patent:

8197197, Jun 12, 2012

Filed:

Jan 8, 2009

Appl. No.:

12/350624

Inventors:

Mark W. Flanagan - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 25/08
F01D 5/08
F01D 5/18
F03B 11/00
F04D 29/58

US Classification:

415177, 415 1

Abstract:

A turbine power generation system with thermal response rate matching provided by one or more fluidic thermal switches and a method for mitigating restart pinch during a hot restart. The turbine power generating system includes a stator and a rotor situated within the casing of the stator. Auxiliary heat is provided to the stator casing during shutdown operations from a heat source via one or more fluidic thermal switch which are configured to provide localized heating to portions of the stator casing subject to restart pinch. The fluidic thermal switch includes two solid, thermal conductors having fluid contacting elements spatially separated within an insulated vessel. A highly conductive and capacitive fluid is provided to the insulated vessel when localized heating is needed.

US Patent:

8523512, Sep 3, 2013

Filed:

Apr 9, 2012

Appl. No.:

13/442174

Inventors:

Mark W. Flanagan - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 25/08
F01D 5/08
F01D 5/18
F03B 11/00
F04D 29/58

US Classification:

415 1

Abstract:

A method for mitigating restart pinch during a hot restart. The method comprises providing a gas turbine engine including a stator and a rotor rotatably situated within the casing of the stator and providing an external heat source capable of selectively supplying auxiliary heat to the casing. The method further comprises operating the gas turbine engine for a first period of time at a steady state condition without supplying the auxiliary heat to the casing and supplying the auxiliary heat to the casing for a second period of time when shutting down the gas turbine after operating at the steady state condition for the first period of time.