Adam D Plant

US Patent:

20050172635, Aug 11, 2005

Filed:

Aug 27, 2004

Appl. No.:

10/928523

Inventors:

Charles Carlson - Chuluota FL, US
Adam Plant - Orlando FL, US

International Classification:

F02C003/30
F02C007/10

US Classification:

060775000, 060039511

Abstract:

A gas turbine system () includes a compressor () for receiving air and producing compressor discharge air, a combustor () for combusting an oxygen comprising gas flow including the discharge air and a fuel into a hot gas flow, and a turbine expander () generating output power from the hot gas flow and providing a hot exhaust gas flow. An extractor () is provided for splitting the discharge air into a direct flow portion () which directly reaches the combustor () and an indirect flow portion (). A mixing device () receives the indirect flow portion () and mixes it with a water flow (), either in the form of water or steam, to produce a water enhanced indirect flow portion (). A recuperative heat exchanger () heats the water enhanced indirect flow portion () using heat from at least a portion of the hot exhaust gas flow. The heated water enhanced indirect flow portion () is then reintroduced into the oxygen comprising gas flow.

US Patent:

20100175385, Jul 15, 2010

Filed:

Jan 11, 2010

Appl. No.:

12/685185

Inventors:

Adam D. Plant - Orlando FL, US
Christopher R. Oliveri - Orlando FL, US
Bruce H. Carpenter - Orlando FL, US
Damien G. Teehan - St. Cloud FL, US
David D. Elwood - Oviedo FL, US

International Classification:

F02C 9/18
F02C 6/00

US Classification:

60773, 290 52

Abstract:

A method of operating an electric power generation system (). In one embodiment, a combustion chamber receives a combination of pressurized air () flow output from a compressor () and fuel () for combustion therein. The system () is operated at a relatively high steady state level of power output and then power is turned down by extracting a portion () of the pressurized air () flow before entry into the combustor (). The method may further include throttling of air () flowing through the compressor () with inlet guide vanes (). Features of the reduction in power include maintaining a characteristic combustor () minimum flame temperature with a volumetric percentage of NOor CO emissions not exceeding those corresponding to the relatively high steady state operation.

US Patent:

20110210555, Sep 1, 2011

Filed:

Feb 26, 2010

Appl. No.:

12/713604

Inventors:

Jian Y. Xia - Orlando FL, US
Adam D. Plant - Orlando FL, US
Hans-Juergen Kiesow - Orlando FL, US
Martin Ferdinand Urban - Erlangen, DE

International Classification:

F02C 9/00
F01K 23/06
H02K 7/18

US Classification:

290 52, 60773, 60670

Abstract:

A gas turbine compressor (A, B) sized to support respective maximum design points of other gas turbine driven electrical power generating system components () during a least dense ambient condition within a design range of ambient conditions. A variable inlet () on the compressor automatically modulates to modulate airflow to supply just the amount needed to produce a rated output of the system throughout the full design range of ambient conditions. This safely and economically maintains rated power system output () over a full range of ambient conditions.

US Patent:

20110265486, Nov 3, 2011

Filed:

Apr 29, 2010

Appl. No.:

12/769934

Inventors:

Adam D. Plant - Orlando FL, US

International Classification:

F02C 7/057

US Classification:

60773, 60 3923

Abstract:

A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section, and the turbine engine having a base load. The combustor section includes a combustor and a combustor shell. A flow control device is located in a flow path between the combustor shell and an inlet to the combustor. The flow control device effects an increase in a pressure drop of shell air flowing from the combustor shell to the combustor. A controller is provided for operating the flow control device to change a pressure drop across the flow control device, wherein an increase in the pressure drop across the flow control device results in a corresponding reduction in mass flow through the combustor for effecting a reduction in power output from the turbine engine during a reduction in an operating load to less than the base load.