A distributed control system for a turbomachine and method of operating the distributed control system are provided. In one aspect, a distributed control system includes a central controller and a distributed controller communicatively coupled thereto. The distributed controller has one or more associated local actuators and one or more associated local sensors. The actuators and the sensors are communicatively coupled with the distributed controller. If a communication link between the central controller and the distributed controller becomes faulty, the distributed controller enters an autonomous safety mode. In this mode, the distributed controller uses a combination of its own associated local sensors and past commands received from the central controller to autonomously govern its associated local actuators to maintain safe operation of the turbomachine.

A fan assembly is provided. The fan assembly includes a fan, a fan casing circumscribing the fan, and a fan casing heating system in thermal communication with the fan casing. The fan includes a hub, and a plurality of fan blades extending from the hub. Each fan blade of the plurality of fan blades terminates at a respective blade tip. A clearance gap is defined between the fan casing and the blade tips. The fan casing heating system is configured to apply heat to the fan casing when the fan is operating in a first operational mode, and remove the applied heat when the fan transitions into a second operational mode.

A gas turbine power plant comprises a gas turbine, a power turbine, a clutch, an electrical generator and a controller. The power turbine is fluidly connected to the gas turbine without any mechanical connection. The clutch comprises an input mechanically connected to the power turbine and an output mechanically connected to the electric generator. The controller can identify that a speed of the electric generator is greater than a speed of the power turbine, determine a difference between the speed of the electric generator and the power turbine, in response to the difference being greater than a threshold, control the gas turbine to a first maximum acceleration of the power turbine, and in response to the difference being equal or less than to the threshold, control the gas turbine to a second maximum acceleration of the power turbine that is less than the first maximum acceleration.

A gas turbine power plant comprises a gas turbine, a power turbine, a clutch, an electrical generator and a controller. The power turbine is fluidly connected to the gas turbine without any mechanical connection. The clutch comprises an input mechanically connected to the power turbine and an output mechanically connected to the electric generator. The controller can identify that a speed of the electric generator is greater than a speed of the power turbine, determine a difference between the speed of the electric generator and the power turbine, in response to the difference being greater than a threshold, control the gas turbine to a first maximum acceleration of the power turbine, and in response to the difference being equal or less than to the threshold, control the gas turbine to a second maximum acceleration of the power turbine that is less than the first maximum acceleration.

A distributed control system for a turbomachine and method of operating the distributed control system are provided. In one aspect, a distributed control system includes a central controller and a distributed controller communicatively coupled thereto. The distributed controller has one or more associated local actuators and one or more associated local sensors. The actuators and the sensors are communicatively coupled with the distributed controller. If a communication link between the central controller and the distributed controller becomes faulty, the distributed controller enters an autonomous safety mode. In this mode, the distributed controller uses a combination of its own associated local sensors and past commands received from the central controller to autonomously govern its associated local actuators to maintain safe operation of the turbomachine.

A fan assembly is provided. The fan assembly includes a fan, a fan casing circumscribing the fan, and a fan casing heating system in thermal communication with the fan casing. The fan includes a hub, and a plurality of fan blades extending from the hub. Each fan blade of the plurality of fan blades terminates at a respective blade tip. A clearance gap is defined between the fan casing and the blade tips. The fan casing heating system is configured to apply heat to the fan casing when the fan is operating in a first operational mode, and remove the applied heat when the fan transitions into a second operational mode.