Abstract: A method of controlling a gas turbine engine in a vehicle having an automatic system configured to control fuel flow includes determining whether a vehicle operator is requesting to manually control fuel. A pre-relinquishment value of an engine operating condition is determined while fuel flow is controlled by the automatic system. Fuel flow control is relinquished to the vehicle operator if the vehicle operator is requesting to manually control fuel flow and the pre-relinquishment value is within a predetermined range. A post-relinquishment value of the engine operating condition is determined while fuel flow is controlled by the vehicle operator. Fuel flow control is returned to the automatic system if the post-relinquishment value is not maintained within the predetermined range.

Abstract: A system and method of controlling a gas turbine engine controller in a rotorwing aircraft includes determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted. A control loop gain of the gas turbine engine controller is at least selectively varied when the FCTO is being conducted.

Abstract: A method of controlling a gas turbine engine in a vehicle having an automatic system configured to control fuel flow includes determining whether a vehicle operator is requesting to manually control fuel. A pre-relinquishment value of an engine operating condition is determined while fuel flow is controlled by the automatic system. Fuel flow control is relinquished to the vehicle operator if the vehicle operator is requesting to manually control fuel flow and the pre-relinquishment value is within a predetermined range. A post-relinquishment value of the engine operating condition is determined while fuel flow is controlled by the vehicle operator. Fuel flow control is returned to the automatic system if the post-relinquishment value is not maintained within the predetermined range.

Abstract: A system and method of controlling a gas turbine engine controller in a rotorwing aircraft includes determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted. A control loop gain of the gas turbine engine controller is at least selectively varied when the FCTO is being conducted.

Abstract: The present invention provides a multiple manifold fuel metering system with a separate motor, pump, and shut-off/purge valve for each manifold. The present invention may be used for metering fuel to any engine, especially a gas turbine engine. The fuel metering system of the present invention has the capability of independently controlling fuel flow during transitions in engine operation or allowing fuel to flow simultaneously through all manifolds to prevent blowout, optimizing combustion temperature distributions, or minimizing combustion emissions. Brushless DC variable speed electric motors may be used to drive pumps with highly accurate speed control to accurately control fuel flow rate to each of a plurality of manifolds of a fuel metering system. With brushless DC motors, motor speed may be controlled within a revolution for smoothing fuel delivery to an engine.

Abstract: The present invention provides a multiple manifold fuel metering system with a separate motor, pump, and shut-off/purge valve for each manifold. The present invention may be used for metering fuel to any engine, especially a gas turbine engine. The fuel metering system of the present invention has the capability of independently controlling fuel flow during transitions in engine operation or allowing fuel to flow simultaneously through all manifolds to prevent blowout, optimizing combustion temperature distributions, or minimizing combustion emissions. Brushless DC variable speed electric motors may be used to drive pumps with highly accurate speed control to accurately control fuel flow rate to each of a plurality of manifolds of a fuel metering system. With brushless DC motors, motor speed may be controlled within a revolution for smoothing fuel delivery to an engine.