초록 ▼

A combustion control system controls a turbine engine that includes a fuel manifold and a plurality of fuel injectors. The control system includes a fuel pulsator and a controller. The fuel pulsator is coupled in flow communication with the plurality of injectors and the fuel manifold. The controlle

A combustion control system controls a turbine engine that includes a fuel manifold and a plurality of fuel injectors. The control system includes a fuel pulsator and a controller. The fuel pulsator is coupled in flow communication with the plurality of injectors and the fuel manifold. The controller is coupled to the fuel pulsator such that the pulsator is between the controller and the fuel manifold. The controller is variably selectable and configured to facilitate promoting stable combustion.

대표청구항 ▼

1. A method for controlling an aircraft engine including a combustor, a fuel manifold, and a plurality of fuel injectors, the fuel manifold in flow communication with the fuel injectors for supplying fuel to the combustor, the combustor defining a combustion chamber, said method comprising: suppl

1. A method for controlling an aircraft engine including a combustor, a fuel manifold, and a plurality of fuel injectors, the fuel manifold in flow communication with the fuel injectors for supplying fuel to the combustor, the combustor defining a combustion chamber, said method comprising: supplying fuel to the combustor fuel injectors through a fuel pulsator and the fuel manifold, wherein the fuel pulsator is coupled to a controller; and variably operating the controller without continuous feedback to pulse fuel with the fuel pulsator to facilitate promoting stable combustion within the combustion chamber. 2. A method in accordance with claim 1 wherein variably operating the controller further comprises pulsing fuel at a frequency and amplitude that facilitates natural acoustic avoidance within the combustion chamber. 3. A method in accordance with claim 1 wherein variably operating the controller further comprises pulsing fuel at a frequency and amplitude that facilitates avoidance of natural mechanical vibrational modes inherent within the combustion chamber. 4. A method in accordance with claim 1 wherein supplying fuel to the combustor fuel injectors further comprises supplying fuel to the combustor fuel injectors using a fuel pump coupled upstream from the fuel pulsator. 5. A method in accordance with claim 1 wherein supplying fuel to the combustor fuel injectors further comprises supplying fuel to the fuel injectors through a fuel pulsator and the fuel manifold, wherein the fuel pulsator is coupled to a fuel inlet of the fuel manifold.