Abstract:
Methods and systems may dispense turbine engine anticorrosive protection. In an embodiment, a method may include determining a condition of a gas turbine engine while the gas turbine engine is online, wherein the condition includes the power output level of the gas turbine engine and applying, based on the condition, an anticorrosion fluid to the gas turbine engine while the gas turbine engine is online.
Abstract:
Methods and systems for dispersing anticorrosive treatment for a turbine engine may incorporate an inlet bleed heat system. In an embodiment, a method may include selecting an anticorrosion fluid for a turbine engine and distributing the anticorrosion fluid via a vaporizing system fluidly connected with the turbine engine, wherein the vaporizing system is used to transform the anticorrosion fluid into a vapor.
Abstract:
A gas turbine wash control system may perform a wash and a rinse of a gas turbine that is offline. An inter-rinse solution may be injected into the gas turbine. The gas turbine may be agitated and the inter-rinse solution drained. A second rinse of the gas turbine may be performed followed by the injection of an anticorrosive solution into the gas turbine.
Abstract:
A system and method to preemptively adjust power generation of one or more non-wind power generators based on near term wind generation capability, spinning reserve margin, and/or power grid spinning reserve forecast requirements to offset wind power generation based on geospatial regional wind conditions.
Abstract:
A system and method to preemptively adjust power generation of one or more non-wind power generators based on near term wind generation capability, spinning reserve margin, and/or power grid spinning reserve forecast requirements to offset wind power generation based on geospatial regional wind conditions.
Abstract:
A system for de-icing a gas turbine engine is provided. A manifold is coupled to an inlet screen. A first conduit is coupled to a stage of the compressor and a first input of a mixing component. A second conduit is coupled to the exhaust and a second input of the mixing component. The second conduit being adapted to extract exhaust gases without increasing the pressure at the exhaust. A third conduit is coupled to the output of the mixing component and the manifold. A method for de-icing a gas turbine engine inlet screen includes determining a current temperature at the inlet screen, and determining a desired temperature at the inlet screen. If the current temperature at the inlet screen is less than the desired temperature at the inlet screen first flow rate of an air-exhaust mixture necessary to achieve the desired inlet screen temperature is calculated. The method also includes extracting an amount of exhaust gas from a turbine exhaust subsystem without increasing a pressure at the turbine exhaust subsystem, extracting an amount of air from a compressor stage, and mixing the amount of exhaust gas with the amount of air to generate an air-exhaust mixture that is conveyed to the inlet screen.
Abstract:
A method and system for measuring a flow profile in a portion of a flow path in a turbine engine is provided. The system includes a mass flow sensor assembly having a plurality of hot wire mass flow sensors, the mass flow sensor assembly disposed in the portion of the flow path at a location where the flow profile is to be measured. The system also includes a controller that converts signals from the temperature sensor, the pressure sensor and the plurality of hot wire mass flow sensors to flow profile measurements.