FAULT DETECTION AND LOAD MANAGEMENT IN A SERIES HYBRID PROPULSION SYSTEM
A series hybrid propulsion system of an aircraft includes a gas turbine engine, an electrical generator operably connected to the gas turbine engine configured to generate electrical power from operation of the gas turbine engine, and one or more electrically-driven propulsors configured to provide propulsion for the aircraft, and an electrical power grid configured to distribute electrical power generated at least at the electrical generator to the one or more electrically-driven propulsors. A voltage regulator is positioned downstream of the electrical generator and is configured to take one or more actions to compensate for a loss of load on the generator.
1 . A series hybrid propulsion system of an aircraft, comprising:
a gas turbine engine;
an electrical generator operably connected to the gas turbine engine configured to generate electrical power from operation of the gas turbine engine;
one or more electrically-driven propulsors configured to provide propulsion for the aircraft;
an electrical power grid configured to distribute the electrical power generated at least at the electrical generator to the one or more electrically-driven propulsors;
a voltage regulator disposed downstream of the electrical generator configured to take one or more actions to compensate for a loss of load on the electrical generator; and
a system controller operably connected to the gas turbine engine and the voltage regulator, and configured to slow operation of the gas turbine engine when the loss of load is detected by the voltage regulator.
2 . The system of claim 1 , wherein the one or more actions includes applying an emergency load to the electrical generator.
3 . The system of claim 2 , wherein the emergency load is applied to the electrical generator when the electrical generator is disconnected from the electrical power grid.
4 . The system of claim 2 , wherein the emergency load is applied via a shunt circuit at the voltage regulator.
5 . The system of claim 1 , wherein the loss of load is determined by measuring one of a current or a voltage at the electrical generator.
6 . The system of claim 1 , wherein the one or more actions includes applying a variable resistive load to the electrical generator.
7 . The system of claim 6 , wherein the variable resistive load is applied to the electrical generator when one or more electrically-driven propulsors are disconnected from the electrical power grid.
8 . The system of claim 1 , wherein the one or more electrically-driven propulsors includes:
a fan; and
an electric motor configured to drive the fan.
9 . The system of claim 8 , further comprising a motor controller configured to control operation of the electric motor.
10 . The system of claim 1 , further comprising an energy storage system operably connected to the electrical power grid configured to store the electrical power generated at the electrical generator.
11 . A method of operating a series hybrid propulsion system of an aircraft, comprising:
generating electrical power at an electrical generator via operation of a gas turbine engine operably connected to the electrical generator;
distributing the electrical power to an electrical power grid;
operating one or more electrically-driven propulsors from the electrical power provided to the electrical power grid to provide propulsion for the aircraft;
abruptly reducing a load on the electrical generator; and
taking one or more actions at a voltage regulator disposed downstream of the electrical generator to compensate for the reduction of the load on the electrical generator;
slowing operation of the gas turbine engine when the reduction of the load is detected by the voltage regulator.
12 . The method of claim 11 , wherein the reduction of the load on the electrical generator is due to the electrical generator being disconnected from the electrical power grid.
13 . The method of claim 12 , wherein the one or more actions includes applying an emergency load to the electrical generator.
14 . The method of claim 13 , wherein the emergency load is applied via a shunt circuit at the voltage regulator.
15 . The method of claim 11 , wherein the reduction of load is determined by measuring one of a current or a voltage at the electrical generator.
16 . The method of claim 11 , wherein the reduction in load on the electrical generator is due to one or more electrically-driven propulsors being disconnected from the electrical power grid.
17 . The method of claim 16 , wherein the one or more actions includes applying a variable resistive load to the electrical generator.
18 . The method of claim 11 , wherein the one or more electrically-driven propulsors includes:
a fan; and
an electric motor configured to drive the fan.
19 . The method of claim 18 , further comprising a motor controller configured to control operation of the electric motor.
20 . The method of claim 11 , further comprising storing the electrical power generated at the electrical generator at an energy storage system operably connected to the electrical power grid.