Abstract: The present application provides a doubly-fed induction generator system for a multi-shaft gas turbine engine. The doubly-fed induction generator system may include a first doubly-fed induction generator in communication with a first shaft of the multi-shaft gas turbine engine, a first rotor of the first doubly-fed induction generator in communication with a converter via a first rotor bus, and a first breaker on the first rotor bus. The first doubly-fed induction generator acts as a generator or a motor depending in part upon the position of the first breaker.

Abstract: The present application provides a doubly-fed induction generator system for a multi-shaft gas turbine engine. The doubly-fed induction generator system may include a first doubly-fed induction generator in communication with a first shaft of the multi-shaft gas turbine engine, a first rotor of the first doubly-fed induction generator in communication with a converter via a first rotor bus, and a first breaker on the first rotor bus. The first doubly-fed induction generator acts as a generator or a motor depending in part upon the position of the first breaker.

Abstract: Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation. At least one secondary fuel circuit of the fuel delivery system is configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation. The secondary fuel circuit includes at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies. The at least one isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation. The fuel delivery system, using the isolation valve, replaces a purging system in the gas turbine engine.

Abstract: A system includes a turbine fuel supply system. The turbine fuel supply system includes a first turbine fuel mixer configured to mix a first liquid fuel and a first deaerated water to generate a first fuel mixture. The first fuel mixture is configured to combust in a combustor of a gas turbine engine. The turbine fuel supply system also includes a deaerated water flow path configured to route the first deaerated water to the first turbine fuel mixer and a liquid fuel flow path configured to route the first liquid fuel to the first turbine fuel mixer.

Abstract: A system includes a gas turbine engine having a combustor, a liquid fuel supply coupled to the combustor, and a water supply coupled to the liquid fuel supply. The water supply is configured to flow water through the liquid fuel supply while the liquid fuel supply is not in use to flow a liquid fuel.

Abstract: A system includes a mixing assembly configured to mix a liquid fuel and a water to generate a fuel mixture. The fuel mixture is configured to combust in a combustor of a gas turbine. The mixing assembly includes a liquid fuel passage disposed in an integrated housing. The liquid fuel passage is configured to flow the liquid fuel and to exclude liquid traps. The mixing assembly also includes a water passage disposed in the integrated housing. The water passage is configured to flow the water and to exclude liquid traps. The mixing assembly also includes a mixer disposed in the integrated housing and coupled to the liquid fuel passage and the water passage. The mixer is configured to mix the liquid fuel and the water to form the fuel mixture.

Abstract: Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation. At least one secondary fuel circuit of the fuel delivery system is configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation. The secondary fuel circuit includes at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies. The at least one isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation. The fuel delivery system, using the isolation valve, replaces a purging system in the gas turbine engine.

Abstract: A system includes a turbine fuel supply system. The turbine fuel supply system includes a first turbine fuel mixer configured to mix a first liquid fuel and a first deaerated water to generate a first fuel mixture. The first fuel mixture is configured to combust in a combustor of a gas turbine engine. The turbine fuel supply system also includes a deaerated water flow path configured to route the first deaerated water to the first turbine fuel mixer and a liquid fuel flow path configured to route the first liquid fuel to the first turbine fuel mixer.

Abstract: A system includes a gas turbine engine having a combustor, a liquid fuel supply coupled to the combustor, and a water supply coupled to the liquid fuel supply. The water supply is configured to flow water through the liquid fuel supply while the liquid fuel supply is not in use to flow a liquid fuel.

Abstract: A system includes a mixing assembly configured to mix a liquid fuel and a water to generate a fuel mixture. The fuel mixture is configured to combust in a combustor of a gas turbine. The mixing assembly includes a liquid fuel passage disposed in an integrated housing. The liquid fuel passage is configured to flow the liquid fuel and to exclude liquid traps. The mixing assembly also includes a water passage disposed in the integrated housing. The water passage is configured to flow the water and to exclude liquid traps. The mixing assembly also includes a mixer disposed in the integrated housing and coupled to the liquid fuel passage and the water passage. The mixer is configured to mix the liquid fuel and the water to form the fuel mixture.

Abstract: Embodiments of the present invention incorporate a relatively slow acting valve to throttle the fuel flow through the compressor. Embodiments of the present invention seek to reduce the need for recirculating compressed fuel that is not needed by the turbomachine. This may increase the net power output and efficiency of a turbomachine-fuel gas compressor system.

Abstract: A system and method for providing fuel mixes a first fuel with a second fuel at a mixing point to create a mixed fuel having a first calorie content. A control valve is located upstream of the mixing point. A process system downstream of the mixing point processes the mixed fuel to create a processed mixed fuel having a second calorie content. A first control signal is reflective of the first calorie content of the mixed fuel. A second control signal is reflective of the second calorie content of the processed mixed fuel. A third control signal is reflective of the operating level of the combustion engine. A controller connected to the control valve operates the control valve based on the first, second, and third control signals.

Abstract: The present invention pertains generally to a system and method for providing fuel having a desired calorie content to a combustion engine over a range of operating levels. The system mixes a first fuel from a first fuel supply pipe with a second fuel from a second fuel supply pipe at a mixing point to create a mixed fuel having a first calorie content. A control valve is located in the second fuel supply pipe upstream of the mixing point. A process system downstream of the mixing point processes the mixed fuel to create a processed mixed fuel having a second calorie content. A first control signal is reflective of the first calorie content of the mixed fuel. A second control signal is reflective of the second calorie content of the processed mixed fuel. A third control signal is reflective of the operating level of the combustion engine. A controller connected to the control valve operates the control valve based on the first, second, and third control signals.