Hybrid electric propulsion system with pitch change mechanism operation
A hybrid electric propulsion system for an aircraft is provided that includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, a propulsion unit, and a controller. The thermal engine has a main oil pump configured to be driven by the thermal engine. The gearbox is in communication with the thermal and electric motors. The propulsion unit includes a propeller having propeller blades, and a pitch change mechanism. The controller is in communication with the thermal and electric motors, the propulsion unit, and a memory storing instructions. The instructions when executed cause the controller to control the electric motor to operate using electrical power from the electric power storage unit to cause the main oil pump to actuate and produce a flow of engine oil to the pitch change mechanism for a period of time sufficient to feather the propeller blades.
1 . A hybrid electric propulsion (HEP) system for an aircraft, comprising:
a thermal engine having an engine oil system with a main oil pump configured to be driven by the thermal engine;
an electric motor;
a gearbox in communication with the thermal engine and the electric motor;
an electric power storage unit;
a propulsion unit including a propeller having propeller blades, and a hydro-mechanical pitch change mechanism; and
a controller in communication with the thermal engine, the electric motor, the propulsion unit, and a memory storing instructions, which instructions when executed cause the controller to control the electric motor to operate using electrical power from the electric power storage unit to cause the main oil pump to actuate and produce a pressurized flow of engine oil to the pitch change mechanism for a period of time sufficient for the pitch change mechanism to feather the propeller blades.
2 . The hybrid electric propulsion system of claim 1 , wherein the thermal engine and the electric motor are in communication with the gearbox in a parallel configuration.
3 . The hybrid electric propulsion system of claim 1 , wherein the gearbox is in communication with thermal engine and the propulsion unit.
4 . The hybrid electric propulsion system of claim 3 , wherein the instructions when executed cause the controller to control the electric motor to operate using electrical power from the electric power storage unit to cause the main oil pump to actuate and produce the pressurized flow of engine oil to the pitch change mechanism for the period of time sufficient for the pitch change mechanism to feather the propeller blades when the thermal engine is in a shutdown mode.
5 . The hybrid electric propulsion system of claim 1 , wherein the instructions when executed further cause the controller to control the electric motor to selectively operate in a generator mode when the hybrid electric propulsion system is operating in a normal mode.
6 . The hybrid electric propulsion system of claim 1 , further comprising an electric motor control system integral with the controller, wherein the electric motor control system includes an inverter.
7 . The hybrid electric propulsion system of claim 1 , further comprising an electric motor control system independent of and in communication with the controller, wherein the electric motor control system includes an inverter.
8 . The hybrid electric propulsion system of claim 1 , further comprising a second gearbox in communication with the thermal engine and the electric motor, wherein the electric motor, the gearbox, the thermal engine, the second gearbox and the propulsion unit are disposed in a series arrangement.
9 . The hybrid electric propulsion system of claim 8 , wherein the instructions when executed cause the controller to control the electric motor to operate using electrical power from the electric power storage unit to cause the main oil pump to actuate and produce the pressurized flow of engine oil to the pitch change mechanism for the period of time sufficient for the pitch change mechanism to feather the propeller blades when the thermal engine is in a shutdown mode.
10 . The hybrid electric propulsion system of claim 8 , wherein the instructions when executed further cause the controller to control the electric motor to selectively operate in a generator mode when the hybrid electric propulsion system is operating in a normal mode.
11 . The hybrid electric propulsion system of claim 8 , further comprising an electric motor control system integral with the controller, wherein the electric motor control system includes an inverter.
12 . The hybrid electric propulsion system of claim 8 , further comprising an electric motor control system independent of and in communication with the controller, wherein the electric motor control system includes an inverter.
13 . The hybrid electric propulsion system of claim 1 , wherein the instructions when executed cause the controller to control the electric motor to control a rate of unfeathering of the propeller.
14 . The hybrid electric propulsion system of claim 13 , wherein the instructions when executed cause the controller to control the electric motor as a function of a torque and/or a rate of change of torque applied by the electric motor to the propeller.