Hybrid-electric aircraft propulsion system and method
A propulsion system for an aircraft is provided that includes an electric generator, a compressor, an internal combustion (IC) engine, a turbine, an electric power storage unit, and an electric motor. The compressor is configured to selectively produce a flow of compressor air at an air pressure greater than an ambient air pressure. The IC engine is configured to selectively intake compressor air during operation and produce an exhaust gas flow during operation. The turbine, powered by exhaust gas flow, is in communication with and configured to power the compressor and the electric generator. The electric power storage unit is in communication with the electric generator. The electric motor is in communication with the IC engine. The electric motor is powered by the electrical power produced by the electric generator, and the electric motor is configured to selectively provide motive force to the IC engine.
1 . A propulsion system for an aircraft, the system comprising:
an electric generator configured to produce electrical power;
a compressor configured to selectively produce a flow of compressor air at an air pressure greater than an ambient air pressure;
an internal combustion (IC) engine configured to selectively intake the flow of compressor air during operation and produce an exhaust gas flow during operation;
a turbine in communication with and configured to power the compressor and the electric generator, wherein the turbine is powered by the exhaust gas flow;
a shaft connecting the electric generator, the compressor, and the turbine, wherein the turbine is configured to drive the shaft and thereby drive the compressor, the compressor between the turbine and the electric generator;
a mechanical power management device (MPMD) disposed between the electric generator and the compressor, the MPMD in communication with the shaft, and the MPMD configured to receive an input power and to produce an output power, wherein the input power is different than the output power;
an electric power storage unit in communication with the electric generator;
an electric motor in communication with the IC engine, the electric motor powered by the electrical power produced by the electric generator, and the electric motor configured to selectively provide motive force to the IC engine; and
an electric power management control (EPMC) configured to receive the electrical power from the electric generator and selectively distribute the electrical power to at least one of the electric power storage unit or the electric motor.
2 . The system of claim 1 , wherein the input power includes a first revolutions per minute (RPM) value and the output power includes a second RPM value, and the first RPM value is different from the second RPM value.
3 . The system of claim 1 , further comprising:
a motor control in communication with the electric motor; and
a system controller in communication with the EPMC, the motor control, and a memory device storing instructions.
4 . The system of claim 1 , wherein the electric generator is configurable as a motor/generator, and said motor/generator is configurable in a first mode or a second mode, wherein in the first mode the motor/generator functions as said electric generator and produces the electrical power and in the second mode functions as a second electric motor to provide motive force; and
wherein a motor control is configurable to control the motor/generator to selectively operate in the first mode and the second mode, and in the second mode, the motor/generator is operable to provide motive force to the compressor.
5 . The system of claim 1 , wherein the mechanical power management device is configurable to selectively disconnect the turbine from the electric generator.
6 . A propulsion system for an aircraft, the system comprising:
an electric generator configured to produce electrical power;
a compressor configured to selectively produce a flow of compressor air at an air pressure greater than an ambient air pressure;
an internal combustion (IC) engine configured to selectively intake the flow of compressor air during operation and produce an exhaust gas flow during operation, the IC engine in communication with a mechanical power management device (MPMD);
a turbine in communication with and configured to power the compressor and the electric generator, wherein the turbine is powered by the exhaust gas flow, the turbine configured to drive a shaft in communication with the electric generator and the compressor;
the compressor disposed between the turbine and the electric generator, and the MPMD disposed between the electric generator and the compressor;
an electric power storage unit in communication with the electric generator;
an electric motor in communication with the MPMD, the electric motor powered by the electrical power produced by the electric generator; and
an electric power management control (EPMC) configured to receive the electrical power from the electric generator and selectively distribute the electrical power to at least one of the electric power storage unit or the electric motor;
wherein the IC engine and the electric motor are both configured to selectively provide motive force to the MPMD.
7 . The system of claim 6 , further comprising a shaft connecting the electric generator, the compressor, and the turbine, wherein the turbine is configured to drive the shaft and thereby drive the compressor.
8 . The system of claim 6 , further comprising:
a motor control in communication with the electric motor; and
a system controller in communication with the EPMC, the motor control, and a memory device storing instructions.
9 . The system of claim 6 , wherein the electric generator is configurable as a motor/generator, and as said motor/generator configurable in a first mode to function as said electric generator and produce the electrical power and in a second mode to function as an electric motor to provide motive force; and
wherein a motor control is configurable to control the motor/generator to selectively operate in the first mode and the second mode, and in the second mode, the motor/generator is operable to provide motive force to the compressor.
10 . The system of claim 6 , wherein the electric generator includes a first electric generator and a second electric generator; and
wherein the compressor includes a first compressor and a second compressor; and
wherein the turbine includes a first turbine and a second turbine, and the first turbine is in communication with and configured to power the first compressor and the first electric generator, and the second turbine is in communication with and configured to power the second compressor and the second electric generator; and
wherein the system is configured such that the first compressor, or the second compressor, or both, are configured to produce the flow of compressor air to the IC engine; and
wherein the system is configured such that the first turbine, or the second turbine, or both, are configured to be powered by the exhaust gas flow from the IC engine; and
the electric motor includes a first electric motor and a second electric motor, and the first electric motor is powered by the electrical power produced by the first electric generator, or the first electric motor is powered by the electrical power produced by the second electric generator, or the first electric motor is powered by the electrical power produced by both the first electric generator and the second electric generator.
11 . The system of claim 10 , wherein the IC engine, the first electric motor, and the second electric motor are configured to selectively provide motive force to the MPMD.
12 . An aircraft, comprising:
a fuselage;
at least one nacelle;
a propulsor;
at least one propulsion system for driving the propulsor, the propulsion system having:
an electric generator configured to produce electrical power;
a compressor configured to selectively produce a flow of compressor air at an air pressure greater than an ambient air pressure;
an internal combustion (IC) engine configured to selectively intake the flow of compressor air during operation and produce an exhaust gas flow during operation, the IC engine in communication with a mechanical power management device (MPMD);
a turbine in communication with and configured to power the compressor and the electric generator, wherein the turbine is powered by the exhaust gas flow;
the compressor disposed between the turbine and the electric generator;
an electric power storage unit in communication with the electric generator;
an electric motor in communication with the MPMD, the electric motor powered by the electrical power produced by the electric generator; and
an electric power management control (EPMC) configured to receive the electrical power from the electric generator and selectively distribute the electrical power to at least one of the electric power storage unit or the electric motor;
wherein the IC engine and the electric motor are both configured to selectively provide motive force to the MPMD and the MPMD provides motive force to the propulsor.
13 . The aircraft of claim 12 , wherein the propulsion system further comprises a shaft connecting the electric generator, the compressor, and the turbine, wherein the turbine is configured to drive the shaft and thereby drive the compressor.
14 . The aircraft of claim 12 , wherein the propulsion system further comprises:
a motor control in communication with the electric motor; and
a system controller in communication with the EPMC, the motor control, and a memory device storing instructions.
15 . The aircraft of claim 12 , wherein the electric generator is configurable as a motor/generator, and as said motor/generator configurable in a first mode to function as said electric generator and produce the electrical power and in a second mode to function as an electric motor to provide motive force; and
wherein a motor control is configurable to control the motor/generator to selectively operate in the first mode and the second mode, and in the second mode, the motor/generator is operable to provide motive force to the compressor.
16 . The aircraft of claim 12 , wherein the electric generator includes a first electric generator and a second electric generator; and
wherein the compressor includes a first compressor and a second compressor; and
wherein the turbine includes a first turbine and a second turbine, and the first turbine is in communication with and configured to power the first compressor and the first electric generator, and the second turbine is in communication with and configured to power the second compressor and the second electric generator; and
wherein the system is configured such that the first compressor, or the second compressor, or both, are configured to produce the flow of compressor air to the IC engine; and
wherein the system is configured such that the first turbine, or the second turbine, or both, are configured to be powered by the exhaust gas flow from the IC engine; and
the electric motor includes a first electric motor and a second electric motor, and the first electric motor is powered by the electrical power produced by the first electric generator, or the first electric motor is powered by the electrical power produced by the second electric generator, or the first electric motor is powered by the electrical power produced by both the first electric generator and the second electric generator.
17 . The aircraft of claim 16 , wherein the IC engine, the first electric motor, and the second electric motor are configured to selectively provide motive force to the MPMD.