Hybrid propulsion systems with power sharing
An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide forward propulsion of the aircraft and a respective electrical machine each configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.
1. An aircraft comprising:
a parallel propulsion unit, the parallel propulsion unit comprising:
a propulsor that provides forward propulsion of the aircraft;
a gas turbine engine that drives the propulsor;
a first electrical machine that generates, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and
a power sharing module that controls a ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy, wherein the power sharing module comprises:
a gearbox, wherein an output shaft of the gas turbine engine is connected to a first input of the gearbox, and wherein the propulsor of the parallel propulsion unit is connected to an output of the gearbox; and
a second electrical machine connected to a second input of the gearbox; and
a controller that controls operation of the second electrical machine to control the ratio; and
a plurality of series propulsion units, each series propulsion unit of the plurality of series propulsion units comprising a respective propulsor of a plurality of propulsors that provide forward propulsion of the aircraft and a respective electrical machine of a plurality of electrical machines, each respective electrical machine driving a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.
2. The aircraft of claim 1 , wherein the first electrical machine is connected to the output shaft of the gas turbine engine.
3. The aircraft of claim 2 , wherein the gearbox comprises a planetary gearbox.
4. The aircraft of claim 1 , further comprising:
a mechanical brake that selectively inhibits rotation of the second electrical machine.
5. The aircraft of claim 4 , wherein the controller:
selectively causes the power sharing module to cause all of the mechanical energy derived from the gas turbine engine to be used to drive the propulsor of the parallel propulsion unit.
6. The aircraft of claim 5 , wherein, to selectively cause the power sharing module to cause all of the mechanical energy derived from the gas turbine engine to be used to drive the propulsor of the parallel propulsion unit, the controller:
determines determine whether a fault has occurred in the aircraft; and
responsive to determining that the fault has occurred, causes the power sharing module to cause all of the mechanical energy derived from the gas turbine engine to be used to drive the propulsor of the parallel propulsion unit.
7. The aircraft of claim 6 , wherein, to determine whether the fault has occurred, the controller determines whether a fault has occurred in the one or more electrical busses or the plurality of series propulsion units.
8. The aircraft of claim 5 , wherein, to selectively cause the power sharing module to cause all of the mechanical energy derived from the gas turbine engine to be used to drive the propulsor of the parallel propulsion unit, the controller:
causes the mechanical brake to inhibit rotation of the second electrical machine.
9. The aircraft of claim 5 , wherein causing all of the mechanical energy derived from the gas turbine engine to be used to drive the propulsor of the parallel propulsion unit causes an increase in a rotational speed of the propulsor of the parallel propulsion unit.
10. The aircraft of claim 5 , wherein the controller:
selectively causes the power sharing module to cause all of the mechanical energy derived from the gas turbine engine to be used to generate electrical energy.
11. The aircraft of claim 1 , wherein a noise level emitted by the aircraft is correlated to the ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy.
12. The aircraft of claim 1 , wherein the plurality of propulsors comprise variable pitch propellers.
13. The aircraft of claim 1 , further comprising:
one or more electrical energy storage devices operably coupled to at least one of the one or more electrical busses, wherein the one or more electrical energy storage devices both:
charge using electrical energy sourced via the at least one of the one or more electrical busses; and
discharge to provide electrical energy to the at least one of the one or more electrical busses.
14. The aircraft of claim 1 , wherein the aircraft does not include an auxiliary power unit (APU) that outputs electrical energy onto the one or more electrical busses.
15. The aircraft of claim 1 , wherein the aircraft includes an auxiliary power unit (APU) that outputs electrical energy onto the one or more electrical busses.
16. The aircraft of claim 1 , wherein the aircraft comprises a fixed wing aircraft.
17. The aircraft of claim 1 , wherein the parallel propulsion unit is mounted on a centerline of the aircraft.
18. The aircraft of claim 1 , wherein, to control operation of the second electrical machine, the controller controls an amount of electrical energy generated by the second electrical machine.
19. A method comprising:
controlling, by a controller, a power sharing module that mechanically controls a ratio of mechanical energy derived from a gas turbine engine of a parallel propulsion unit:
used to drive a propulsor of the parallel propulsion unit that provides forward propulsion of an aircraft, and
used by an electrical machine of the parallel propulsion unit to generate electrical energy for output via one or more electrical busses of the aircraft, wherein a plurality of series propulsion units of the aircraft provide forward propulsion using electrical energy received from the one or more electrical busses; and
selectively causing, by the controller, the power sharing module to cause all of the mechanical energy derived from the gas turbine engine to be used to drive the propulsor of the parallel propulsion unit.
20. The method of claim 19 , wherein selectively causing the power sharing module to cause all of the mechanical energy derived from the gas turbine engine to be used to drive the propulsor of the parallel propulsion unit comprises:
determining whether a fault has occurred in the aircraft; and
causing, responsive to determining that the fault has occurred, the power sharing module to cause all of the mechanical energy derived from the gas turbine engine to be used to drive the propulsor of the parallel propulsion unit.