Abstract: In one embodiment, a system is provided. The system includes a combustor configured to combust a fuel, and a three-way valve fluidly coupled the combustor and disposed upstream of the combustor. The system also includes a fuel circuit comprising a fuel supply, wherein the fuel circuit is disposed upstream of the three-way valve and is configured to provide the fuel to the three-way valve. The system additionally includes a fuel conduit section fluidly coupling the fuel circuit to the combustor. The system further includes an inert fluid supply configured to provide an inert fluid to the three-way valve and a compressor discharge (CPD) fluid source configured to provide a purge fluid to the three-way valve. The three-way valve is configured to purge the fuel from a first portion of the fuel conduit section by using the purge fluid.

Abstract: A monitoring system for use with a turbine engine is described herein. The turbine engine includes a compressor and at least one compressor bleed valve coupled to the compressor. The monitoring system includes at least one sensor that is for sensing an operational parameter of the compressor bleed valve, and a controller that is coupled to the sensor and the compressor bleed valve. The controller is configured to determine an operating mode of the turbine engine and receive a monitoring signal indicative of the sensed operational parameter. The controller is also configured to calculate at least one operational value of the compressor bleed valve based at least in part on the sensed operational parameter. The controller is further configured to determine a condition of the turbine engine based at least in part on the calculated compressor bleed valve operational value.

Abstract: In one embodiment, a system is provided. The system includes a combustor configured to combust a fuel, and a three-way valve fluidly coupled the combustor and disposed upstream of the combustor. The system also includes a fuel circuit comprising a fuel supply, wherein the fuel circuit is disposed upstream of the three-way valve and is configured to provide the fuel to the three-way valve. The system additionally includes a fuel conduit section fluidly coupling the fuel circuit to the combustor. The system further includes an inert fluid supply configured to provide an inert fluid to the thee-way valve and a compressor discharge (CPD) fluid source configured to provide a purge fluid to the three-way valve. The three-way valve is configured to purge the fuel from a first portion of the fuel conduit section by using the purge fluid.

Abstract: A monitoring system for use with a turbine engine is described herein. The turbine engine includes a compressor and at least one compressor bleed valve coupled to the compressor. The monitoring system includes at least one sensor that is for sensing an operational parameter of the compressor bleed valve, and a controller that is coupled to the sensor and the compressor bleed valve. The controller is configured to determine an operating mode of the turbine engine and receive a monitoring signal indicative of the sensed operational parameter. The controller is also configured to calculate at least one operational value of the compressor bleed valve based at least in part on the sensed operational parameter. The controller is further configured to determine a condition of the turbine engine based at least in part on the calculated compressor bleed valve operational value.

Abstract: In certain embodiments, a system includes a fuel heater. The fuel heater includes a first heat exchanger configured to receive compressed air from a compressor and to transfer heat from the compressed air to feedwater. The fuel heater also includes a second heat exchanger configured to receive heated feedwater from the first heat exchanger and to transfer heat from the heated feedwater to a fuel.

Abstract: Systems and methods for prediction of gas turbine trips due to component failures such as thermocouple failures. Exemplary embodiments include prediction of gas turbine trips due to component failures, including collecting raw gas turbine operational data and using the raw gas turbine operational data to generate a prognostic indicator for the prediction of a turbine trip due to the failed thermocouples.

Abstract: Systems and methods for prediction of gas turbine trips due to component failures such as thermocouple failures. Exemplary embodiments include prediction of gas turbine trips due to component failures, including collecting raw gas turbine operational data and using the raw gas turbine operational data to generate a prognostic indicator for the prediction of a turbine trip due to the failed thermocouples.