Abstract: Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.

Abstract: A system includes a gas turbine. The gas turbine includes a first compressor configured to provide a first portion of a discharge air to a combustor. The gas turbine also includes the combustor configured to combust a mixture of the first portion of the discharge air and fuel to generate an exhaust gas and to provide the exhaust gas to a turbine. The gas turbine also includes an exhaust outlet coupled to the turbine and configured to enable the exhaust gas to exit the gas turbine. The system also includes a nitrogen purification system coupled to the gas turbine. The nitrogen purification system includes a membrane nitrogen generator configured to receive a second portion of the discharge air from the compressor or a portion of the exhaust gas from the exhaust outlet, wherein the membrane nitrogen generator is configured to generate nitrogen from the second portion of the discharge air or the portion of the exhaust gas.

Abstract: A method of operating a fuel heating system is provided. The method includes performing pre-ignition diagnostic checks on a plurality of components of the fuel heating system, wherein at least one inlet damper and at least one outlet damper of an exhaust flow circuit are each in a closed position. The method also includes purging the fuel heating system of unburned hydrocarbons. The method further includes operating the fuel heating system in a normal operating condition. The method yet further includes operating the fuel heating system in a cool down condition, wherein the at least one inlet damper is in the closed position.

Abstract: A system includes a gas turbine system, including an air intake system that includes a housing, a first plurality of air conditioning coils, a second plurality of air conditioning coils that is downstream relative to the first plurality, and a baffle extending between each of the first and second pluralities of air conditioning coils, wherein the baffle is configured to direct an air flow through the first or second pluralities of air conditioning coils in a closed position, and the baffle is configured to enable air flow to bypass the first and second pluralities of coils in an opened position.

Abstract: A turbomachine passage cleaning system includes a first airflow passage having a first inlet configured and disposed to fluidly connect to a compressor portion, a first outlet configured and disposed to fluidly connect to a turbine portion, and a first intermediate portion including a first strainer. A second airflow passage is fluidly coupled to the first airflow passage. The second airflow passage has a second intermediate portion having second strainer. A first valve is arranged in the first intermediate portion upstream from the first strainer, and a second valve is arranged in the second intermediate portion upstream from the second strainer. The first and second valves are selectively operated to control fluid flow into respective ones of the first and second airflow passages to filter air passing from a turbomachine compressor portion to a turbomachine turbine portion.

Abstract: The present application provides a fuel conditioning system for delivering a flow of fuel to a nozzle in a gas turbine engine. The fuel conditioning system may include a fuel compressor to increase the pressure of the flow of fuel, a pressure reduction valve to decrease the pressure of the flow of fuel, and a heater downstream of the pressure reduction valve. The pressure reduction valve may include a rotary control valve.

Abstract: A hazardous gas detection system includes a first and second plurality of air sampling ports in fluid communication with an exhaust duct of a gas turbine enclosure. The first and second plurality of air sampling ports is fluidly connected to a first and second outlet orifice respectfully. A primary sensor is in fluid communication with the first outlet orifice and a secondary sensor is in fluid communication with the second outlet orifice. The primary and secondary sensors generate signals indicative of hazardous gas concentrations in first and second aggregated exhaust air samples. A computing device monitors the hazardous gas concentrations, monitors functionality of the primary and secondary sensors and generates a command signal indicating an operating mode for the gas turbine based on at least one of the hazardous gas concentrations in the first and second aggregated exhaust air samples and the functionality of the primary and secondary sensors.

Abstract: Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.

Abstract: A pressure sensor system for a compressor including an inlet bellmouth is disclosed. The system includes a first static pressure sensor positioned within a plane of a plenum that is upstream of the inlet bellmouth; and a second static pressure sensor positioned at an entrance plane of the compressor. A mass flow rate calculator may calculate a mass flow rate based on a pressure differential between the plane of the plenum and the entrance plane of the compressor.

Abstract: A water delivery system for a gas turbine compressor having a plurality of blade stages positioned about a rotating shaft is provided. The plurality of blade stages are configured to compress an airflow. The water delivery system includes a nozzle system to inject water between at least one pair of the plurality of blade stages; and a controller controlling whether the water injected by the nozzle system is injected at a first pressure that augments power output during an operation mode of the plurality of blade stages and a second, lower pressure that washes at least some of blades of the plurality of blade stages during a wash mode of the plurality of blade stages.

Abstract: A mounting adaptor for mounting a transmitter to a valve manifold includes a base portion having a first side and a second side, the first side having a flat surface. Also included is a connector portion having a threaded external surface, the connector portion operatively coupled to, and extending away from, the second side of the base portion. Further included is at least one through hole defined by the base portion, the at least one through hole extending from the first side to the second side and configured to mount the mounting adaptor to the valve manifold.

Abstract: A fuel supply system includes a main fuel line path configured to route a fuel to a combustion inlet region and a secondary fuel line path fluidly coupled to the main fuel line path. The secondary fuel line path is configured to divert a portion of the fuel from the main fuel line path through a first segment of the secondary fuel line path and return the fuel to the main fuel line path through a second segment of the secondary fuel line path. An obstruction mechanism is located proximate the main fuel line path at an obstruction location and is configured to cyclically translate into the main fuel line path to cyclically alter a cross-sectional area of the main fuel line path to effectively oscillate fuel flow pressure into a combustion system.

Abstract: The present application provides an inlet bleed heat system for supplying a flow of bleed air to a flow of incoming air into a compressor of a gas turbine engine. The inlet bleed heat system may include an air knife and a silencer panel. The air knife may include a compressor bleed air port in communication with the flow of bleed air and a discharge gap to discharge the flow of bleed air into the flow of incoming air. The air knife may and the silencer panel may form an integrated air knife/silencer panel.

Abstract: A hazardous gas detection system includes a first and second plurality of air sampling ports in fluid communication with an exhaust duct of a gas turbine enclosure. The first and second plurality of air sampling ports is fluidly connected to a first and second outlet orifice respectfully. A primary sensor is in fluid communication with the first outlet orifice and a secondary sensor is in fluid communication with the second outlet orifice. The primary and secondary sensors generate signals indicative of hazardous gas concentrations in first and second aggregated exhaust air samples. A computing device monitors the hazardous gas concentrations, monitors functionality of the primary and secondary sensors and generates a command signal indicating an operating mode for the gas turbine based on at least one of the hazardous gas concentrations in the first and second aggregated exhaust air samples and the functionality of the primary and secondary sensors.

Abstract: A method for detecting hazardous gas concentration from an exhaust duct of a gas turbine enclosure includes aggregating multiple exhaust air samples collected via a first and a second plurality of sampling ports disposed within the exhaust duct to provide first and second aggregated exhaust air samples to primary and secondary sensors disposed outside of the exhaust duct. The method further includes sensing hazardous gas concentrations within the first and second aggregated exhaust air samples, where the primary and secondary sensors communicate signals that are indicative of the hazardous gas concentrations and functionality of the primary and secondary sensors to a computing device. The method further includes monitoring the hazardous gas concentrations within the first and second aggregated exhaust air samples with respect to a percentage of a lower explosive limit and monitoring the functionality of the primary and secondary sensors via the computing device.

Abstract: An approach for utilizing fuel gas to purge a dormant fuel gas circuit is disclosed. In one aspect, there is a fuel gas supply that supplies fuel to fuel gas circuits. Gas control valves, each coupled to one of the fuel gas circuits control the flow of fuel gas thereto from the fuel gas supply. A fuel purge system selectively purges fuel gas circuits from the fuel gas circuits that are dormant with fuel gas from the fuel gas supply.

Abstract: A gas turbine exhaust diffuser includes a frustoconical portion that defines an interior surface and an axial centerline. In particular embodiments, the interior surface may have a slope greater than 6 degrees, 10 degrees, or 20 degrees with respect to the axial centerline to define an axial cross-sectional area of at least 200 square feet, 240 square feet, or 260 square feet. In other particular embodiments, the interior surface may have an axial length of less than 25 feet or less than 10 feet. A helical turbulator on the interior surface of the frustoconical portion may reduce flow separation between exhaust gases and the interior surface to enhance recovery of potential energy from the exhaust gases.

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: The present application provides a fuel conditioning system for delivering a flow of fuel to a nozzle in a gas turbine engine. The fuel conditioning system may include a fuel compressor to increase the pressure of the flow of fuel, a pressure reduction valve to decrease the pressure of the flow of fuel, and a heater downstream of the pressure reduction valve. The pressure reduction valve may include a rotary control valve.

Abstract: A gas turbine exhaust diffuser includes a frustoconical portion that defines an interior surface and an axial centerline. In particular embodiments, the interior surface may have a slope greater than 6 degrees, 10 degrees, or 20 degrees with respect to the axial centerline to define an axial cross-sectional area of at least 200 square feet, 240 square feet, or 260 square feet. In other particular embodiments, the interior surface may have an axial length of less than 25 feet or less than 10 feet. A helical turbulator on the interior surface of the frustoconical portion may reduce flow separation between exhaust gases and the interior surface to enhance recovery of potential energy from the exhaust gases.