Abstract: A gas detection method and system for detecting a predetermined gas in a system is disclosed. A gas detection system includes a valve system for initially positioning a first gas sensor in fluid communication with a first sensing location and a second gas sensor in fluid communication with a second sensing location. In response to detecting the predetermined gas with a selected sensor from a selected sensing location, the other sensor that did not detect the predetermined gas is placed in fluid communication with the selected sensing location for which the selected sensor sensed the predetermined gas. If the other sensor also detects the predetermined gas in the selected sensing location, an alarm occurs. If the other sensor does not detect the predetermined gas in the selected sensing location, the selected sensor is recalibrated.

Abstract: An integration system for use with a gas turbine engine includes an exhaust gas recirculation (EGR) system in flow communication with a gas turbine section of the gas turbine engine. The EGR system includes an EGR conduit fluidly coupled to an exhaust line of the gas turbine engine and fluidly coupled to an EGR manifold upstream from an inlet of a compressor section of the gas turbine engine. The EGR conduit is oriented to provide a portion of exhaust gases discharged from the gas turbine section to the EGR manifold. Additionally, the EGR system also includes a flow restriction component in flow communication with the exhaust line of the gas turbine engine. The flow restriction component is downstream from the EGR conduit of the EGR system. The flow restriction component facilitates increasing a pressure of the exhaust gases discharged from the gas turbine section.

Abstract: A system includes a gas turbine system having a gas turbine engine including a compressor, a combustor, and a turbine. The gas turbine system further includes an exhaust gas recirculation (EGR) system configured to recirculate a first portion of an exhaust flow from the gas turbine engine to an intake of the gas turbine engine. The gas turbine system further includes an exhaust gas injection system, including a multi-stage compressor including a plurality of stages, wherein the multi-stage compressor is configured to compress a second portion of the exhaust flow. The exhaust gas injection system further includes an intercooler coupled to the multi-stage compressor. The exhaust gas injection system is configured to inject the second portion of the exhaust flow into the gas turbine engine at one or more exhaust injection locations other than the intake to provide power augmentation of the gas turbine engine.

Abstract: A three-way valve for a liquid fuel supply system includes a housing defining a liquid fuel inlet, a purge gas inlet, and at least one drain port. The liquid fuel inlet is sized to receive liquid fuel therethrough for selectively channeling the liquid fuel to a combustor of a gas turbine engine. The purge gas inlet is sized to receive purge gas therethrough for selectively purging liquid fuel from said three-way valve. The at least one drain port is oriented to selectively channel liquid fuel from said three-way valve when purge gas is purging liquid fuel from said three-way valve.

Abstract: A foundation temperature control system for use with a rotary machine is positioned between the rotary machine and a foundation. The foundation temperature control system includes a heat shield, an insulation pack positioned below the heat shield, and an air gap at least partially defined by the heat shield and the insulation pack. The heat shield, the insulation pack, and the air gap are oriented to facilitate maintaining a temperature of the foundation supporting the rotary machine below a maximum rated operating temperature of the foundation.

Abstract: A three-way valve for a liquid fuel supply system includes a housing defining a liquid fuel inlet, a purge gas inlet, and at least one drain port. The liquid fuel inlet is sized to receive liquid fuel therethrough for selectively channeling the liquid fuel to a combustor of a gas turbine engine. The purge gas inlet is sized to receive purge gas therethrough for selectively purging liquid fuel from said three-way valve. The at least one drain port is oriented to selectively channel liquid fuel from said three-way valve when purge gas is purging liquid fuel from said three-way valve.

Abstract: In a one embodiment, a gas turbine system that includes a first pump that supplies distillate fuel to a combustor. A second pump that supplies fuel oil to the combustor. A fuel selection unit that controls a first flow of distillate fuel and a second flow of fuel oil to the combustor. A controller that receives feedback from a sensor and in response to the feedback from the sensor controls the fuel selection unit to start the gas turbine system on the fuel oil.

Abstract: A foundation temperature control system for use with a rotary machine is positioned between the rotary machine and a foundation. The foundation temperature control system includes a heat shield, an insulation pack positioned below the heat shield, and an air gap at least partially defined by the heat shield and the insulation pack. The heat shield, the insulation pack, and the air gap are oriented to facilitate maintaining a temperature of the foundation supporting the rotary machine below a maximum rated operating temperature of the foundation.

Abstract: In a one embodiment, a gas turbine system that includes a first pump that supplies distillate fuel to a combustor. A second pump that supplies fuel oil to the combustor. A fuel selection unit that controls a first flow of distillate fuel and a second flow of fuel oil to the combustor. A controller that receives feedback from a sensor and in response to the feedback from the sensor controls the fuel selection unit to start the gas turbine system on the fuel oil.