Abstract: An air disruption system for an enclosure includes an air delivery system, at least one plenum including an inlet fluidically connected to the air delivery system and at least one outlet, and a controller operatively connected to the air delivery system. The controller is configured and disposed to selectively cause one or more discrete amounts of air to pass into the at least one plenum and flow through the outlet creating a localized air disruption.

Abstract: An air disruption system for an enclosure includes an air delivery system, at least one plenum including an inlet fluidically connected to the air delivery system and at least one outlet, and a controller operatively connected to the air delivery system. The controller is configured and disposed to selectively cause one or more discrete amounts of air to pass into the at least one plenum and flow through the outlet creating a localized air disruption.

Abstract: Methods and systems for operating a gas turbine engine system include an electrical generator configured to provide electrical energy to a load, a gas turbine engine including at least one combustor that includes a plurality of fuel injection points configured to inject a fuel into the combustor at a plurality of different locations wherein the combustor configured to combust the fuel and the gas turbine engine is rotatably coupled to the generator through a shaft. The gas turbine engine system includes a control system including a plurality of sensors positioned about the gas turbine engine system and configured to measure at least one parameter associated with the sensor, a processor programmed to receive a signal indicative of a heating value of the fuel, and automatically control a fuel split between the fuel injection points on the combustor using the determined heating value.

Abstract: Methods and systems for operating a gas turbine engine system include an electrical generator configured to provide electrical energy to a load, a gas turbine engine including at least one combustor that includes a plurality of fuel injection points configured to inject a fuel into the combustor at a plurality of different locations wherein the combustor configured to combust the fuel and the gas turbine engine is rotatably coupled to the generator through a shaft. The gas turbine engine system includes a control system including a plurality of sensors positioned about the gas turbine engine system and configured to measure at least one parameter associated with the sensor, a processor programmed to receive a signal indicative of a heating value of the fuel, and automatically control a fuel split between the fuel injection points on the combustor using the determined heating value.