An actuating device of a pump of a fuel pumping system of an engine, including a motor, a generator, an inverter, a switching member and a control member, the motor including a first rotor coupled to the pump and a first stator including at least one input stator winding, the generator including a second rotor coupled to a drive shaft of the engine, and a second stator including at least one output stator winding, the control member being configured to control the switching member in order to selectively connect each input stator winding: to a corresponding output stator winding if a speed of the engine is higher than or equal to a predetermined speed; to a corresponding output of the inverter, otherwise.

A control device is a device for controlling a gas turbine. The control device is provided with: a prediction unit configured to predict a future state quantity of the gas turbine corresponding to a control input to the gas turbine in a prediction horizon, using a prediction model; an optimization unit configured to optimize the control input in at least a part of the prediction horizon, using a prediction result of the prediction unit; a storage unit for storing sensitivity information indicating sensitivity of the control input to a change speed of the state quantity for each operating condition of the gas turbine; and an update unit configured to read the sensitivity information corresponding to the operating condition assumed in the prediction horizon from the storage unit, and update one or more coefficients of a prediction equation of the state quantity used in the prediction model.

A control device is a device for controlling a gas turbine. The control device is provided with: a prediction unit configured to predict a future state quantity of the gas turbine corresponding to a control input to the gas turbine in a prediction horizon, using a prediction model; an optimization unit configured to optimize the control input in at least a part of the prediction horizon, using a prediction result of the prediction unit; a storage unit for storing sensitivity information indicating sensitivity of the control input to a change speed of the state quantity for each operating condition of the gas turbine; and an update unit configured to read the sensitivity information corresponding to the operating condition assumed in the prediction horizon from the storage unit, and update one or more coefficients of a prediction equation of the state quantity used in the prediction model.

A fuel pumping system of an aircraft, having a first boost pump; a main pump; a main pump feed conduit fluidly coupled to the main pump and configured to receive fuel after it has passed through the first boost pump; a main pump discharge conduit fluidly coupled to the main pump; an ejector fluidly coupled to the main pump feed conduit, between the first boost pump and the main pump; a bypass conduit fluidly coupled to the main pump discharge conduit and the ejector such that the bypass conduit is configured to provide fluid to the ejector drawn from the output of the first boost pump into the main pump; and a backpressure regulating valve fluidly coupled to the bypass conduit, and configured to transition to an open state when pressure in the main pump discharge conduit is above a threshold.

A fuel pumping system of an aircraft, having a first boost pump; a main pump; a main pump feed conduit fluidly coupled to the main pump and configured to receive fuel after it has passed through the first boost pump; a main pump discharge conduit fluidly coupled to the main pump; an ejector fluidly coupled to the main pump feed conduit, between the first boost pump and the main pump; a bypass conduit fluidly coupled to the main pump discharge conduit and the ejector such that the bypass conduit is configured to provide fluid to the ejector drawn from the output of the first boost pump into the main pump; and a backpressure regulating valve fluidly coupled to the bypass conduit, and configured to transition to an open state when pressure in the main pump discharge conduit is above a threshold.

A fuel pump system can include a motor and a pump connected to the motor. The pump can be configured to receive an inlet flow from an inlet line, to pressurize the inlet flow, and to output a pressurized flow to an output line for an engine. The system can include a bypass line disposed between the outlet line and the inlet line, and a bypass valve disposed on the bypass line and configured to allow pressurized flow to flow to the inlet line in an open state, and to prevent pressurized flow from flowing to the inlet line in a closed state. The bypass valve can be configured to allow pressurized flow to flow to the inlet line to circulate flow and to maintain a constant pressure on the output line.

A fuel pump system can include a motor and a pump connected to the motor. The pump can be configured to receive an inlet flow from an inlet line, to pressurize the inlet flow, and to output a pressurized flow to an output line for an engine. The system can include a bypass line disposed between the outlet line and the inlet line, and a bypass valve disposed on the bypass line and configured to allow pressurized flow to flow to the inlet line in an open state, and to prevent pressurized flow from flowing to the inlet line in a closed state. The bypass valve can be configured to allow pressurized flow to flow to the inlet line to circulate flow and to maintain a constant pressure on the output line.

A rotodynamic pump for pumping a fluid includes an impeller, a housing surrounding the impeller, and a pressure regulating mechanism. The pressure regulating mechanism is configured to adjust the clearance between the impeller and the impeller housing to regulate pressure of the fluid downstream of the impeller. A method of regulating the delivery pressure is also disclosed.

A rotodynamic pump for pumping a fluid includes an impeller, a housing surrounding the impeller, and a pressure regulating mechanism. The pressure regulating mechanism is configured to adjust the clearance between the impeller and the impeller housing to regulate pressure of the fluid downstream of the impeller. A method of regulating the delivery pressure is also disclosed.

In a fuel control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4): a main fuel regulator (12) determines a demand (W.sub.fdem) of fuel flow (W.sub.f) to be introduced in the gas turbine engine (1), based on an input request (PLA); and a first limiter stage (14), operatively coupled to the main fuel regulator (12), causes an adjustment of the fuel flow (W.sub.f) based on engine safety operating limits. The first limiter stage (14) is provided with a Ngdot limiter (20) to cause an adjustment of the fuel flow (W.sub.f) when the gas generator speed rate of change (N.sub.gdot) is determined to overcome acceleration/deceleration scheduled safety limits; the Ngdot limiter (20) implements a predictor (23), to perform a prediction (W.sub.fdot) of the fuel flow rate of change (W.sub.fdot), or fuel flow (W.sub.f), allowing the gas generator speed rate of change (N.sub.gdot) to track a scheduled reference value (Ngdot.sub.ref).