Abstract: A turbomachine is provided and includes a compressor to compress inlet gas to produce compressed gas, a combustor coupled to the compressor in which the compressed gas is combusted along with a first fuel and/or a second fuel to produce a fluid flow, a turbine coupled to the combustor through which the fluid flow is directed for power and/or electricity generation and first and second supply circuits to supply the first fuel and the second fuel to the combustor, respectively. The first and second supply circuits are operable to enable transfers between operations associated with the first fuel and the second fuel being respectively supplied to the combustor at a high load.

Abstract: A method, apparatus and gas turbine for monitoring an operation of a valve of a gas turbine is disclosed. A first sensor obtains a first indicator of a configuration of the valve of the gas turbine. A second sensor measures a physical parameter affected by the valve configuration. A processor is used to obtain a second indicator of the valve configuration from the measured physical parameter and compare the first indicator to the second indicator to monitor the operation of the valve.

Abstract: A turbomachine is provided and includes a compressor to compress inlet gas to produce compressed gas, a combustor coupled to the compressor in which the compressed gas is combusted along with a first fuel and/or a second fuel to produce a fluid flow, a turbine coupled to the combustor through which the fluid flow is directed for power and/or electricity generation and first and second supply circuits to supply the first fuel and the second fuel to the combustor, respectively. The first and second supply circuits are operable to enable transfers between operations associated with the first fuel and the second fuel being respectively supplied to the combustor at a high load.

Abstract: A method, system and generator for controlling a flow of fuel during a shut down of a gas turbine generator is disclosed. A first fuel flow rate to a combustion flame of the gas turbine generator is set at a beginning of a shut-down sequence. A sensor is configured to measure a rotation rate of a turbine rotor of the generator. A processor determines a deceleration of the turbine rotor from the measured rotation rates corresponding to the first fuel flow rate and compares the determined deceleration to a selected criterion. When the deceleration matches the selected criterion, the processor adjusts the fuel flow rate from the first fuel flow rate to a second fuel flow rate.