Aircraft propulsion system with hybrid-electric powerplant
An aircraft system includes a powerplant configured to drive rotation of a propulsor rotor during a first mode and a second mode. The powerplant includes a turbine engine, a first electric machine and a power coupler. A first rotating structure includes a first turbine rotor disposed along a core flowpath. The first electric machine is configured as an electric motor during the second mode. The first electric machine is disposed between the propulsor rotor and the turbine engine. The first electric machine includes a first electric machine rotor coupled to the propulsor rotor. The power coupler is disposed between the first electric machine and the turbine engine. The power coupler is configured to couple the first rotating structure to the first electric machine rotor during the first mode. The power coupler is configured to decouple the first rotating structure from the first electric machine rotor during the second mode.
1 . A system for an aircraft, comprising:
a propulsor rotor;
a powerplant configured to drive rotation of the propulsor rotor during a first mode and a second mode, the powerplant including a turbine engine, a first electric machine and a power coupler;
the turbine engine including a compressor section, a combustor section, a turbine section, a core flowpath and a first rotating structure, the core flowpath extending through the compressor section, the combustor section and the turbine section, and the first rotating structure comprising a first turbine rotor disposed along the core flowpath within the turbine section;
the first electric machine configured as an electric motor during at least the second mode, the first electric machine disposed between the propulsor rotor and the turbine engine, and the first electric machine comprising a first electric machine rotor coupled to the propulsor rotor;
the power coupler disposed between the first electric machine and the turbine engine, the power coupler configured to couple the first rotating structure to the first electric machine rotor during the first mode, and the power coupler configured to decouple the first rotating structure from the first electric machine rotor during the second mode; and
a geartrain operatively coupled between the power coupler and the first electric machine rotor.
2 . The system of claim 1 , wherein
during the first mode, the turbine engine is configured to generate engine mechanical power, and the powerplant is configured to transfer the engine mechanical power from the first rotating structure, through the power coupler and the first electric machine rotor, to the propulsor rotor to drive the rotation of the propulsor rotor; and
during the second mode, the first electric machine is configured to generate electric machine mechanical power, and the powerplant is configured to transfer the electric machine mechanical power from the first electric machine rotor to the propulsor rotor to drive the rotation of the propulsor rotor.
3 . The system of claim 2 , wherein, during the first mode, the first electric machine is further configured to generate the electric machine mechanical power, and the powerplant is configured to transfer the electric machine mechanical power from the first electric machine rotor to the propulsor rotor to further drive the rotation of the propulsor rotor.
4 . The system of claim 1 , wherein the first electric machine is further configurable as an electric generator outside of the second mode.
5 . The system of claim 1 , wherein
the powerplant further includes a second electric machine electrically coupled to the first electric machine;
the second electric machine is configured as an electric generator during at least the second mode; and
the second electric machine comprises a second electric machine rotor operatively coupled to the first rotating structure.
6 . The system of claim 5 , wherein the second electric machine rotor is coaxial with the first rotating structure.
7 . The system of claim 5 , wherein a rotational axis of the second electric machine rotor is offset from a rotational axis of the first rotating structure.
8 . The system of claim 1 , wherein
the turbine engine further includes a second rotating structure rotationally independent of the first rotating structure, and the second rotating structure comprises a second turbine rotor disposed along the core flowpath within the turbine section; and
the powerplant further includes a second electric machine electrically coupled to the first electric machine, the second electric machine is configured as an electric generator during at least the second mode, and the second electric machine comprises a second electric machine rotor operatively coupled to the second rotating structure.
9 . The system of claim 8 , wherein the second electric machine rotor is coaxial with the second rotating structure.
10 . The system of claim 8 , wherein a rotational axis of the second electric machine rotor is offset from a rotational axis of the second rotating structure.
11 . The system of claim 8 , wherein the second rotating structure further comprising a compressor rotor disposed along the core flowpath within the compressor section.
12 . The system of claim 8 , wherein the second turbine rotor is configured as a power turbine rotor.
13 . The system of claim 1 , further comprising:
a propulsion system including the propulsor rotor and the powerplant; and
a power source discrete from the propulsion system, the power source configured to supply electrical power to the first electric machine during the second mode.
14 . The system of claim 1 , further comprising a power storage configured to supply electrical power to the first electric machine during the second mode.
15 . The system of claim 1 , wherein the power coupler comprises a clutch.
16 . The system of claim 1 , further comprising a second geartrain operatively coupled between the first electric machine rotor and the propulsor rotor.
17 . A system for an aircraft, comprising:
a propulsor rotor;
a powerplant including a turbine engine, a first electric machine and a power coupler;
the powerplant configured to drive rotation of the propulsor rotor using engine mechanical power generated by the turbine engine during a first mode where the engine mechanical power is transferred from the turbine engine, through the power coupler and the first electric machine, to the propulsor rotor;
the powerplant configured to drive the rotation of the propulsor rotor using electric machine mechanical power generated by the first electric machine during a second mode where the electric machine mechanical power is transferred from the first electric machine to the propulsor rotor;
the power coupler configured to operatively couple the turbine engine to the first electric machine during the first mode, and the power coupler configured to operatively decouple the turbine engine from the first electric machine during the second mode; and
a geartrain operatively coupled between the power coupler and a rotor of the first electric machine.
18 . The system of claim 17 , wherein the powerplant is further configured to drive the rotation of the propulsor rotor using the electric machine mechanical power generated by the first electric machine during the first mode where the electric machine mechanical power is transferred from the first electric machine to the propulsor rotor independent of the turbine engine and the power coupler.
19 . A system for an aircraft, comprising:
a propulsor rotor;
a powerplant including a turbine engine, a first electric machine and a clutch, the powerplant configured to drive rotation of the propulsor rotor using engine mechanical power generated by the turbine engine during a first mode, and the powerplant configured to drive the rotation of the propulsor rotor using electric machine mechanical power generated by the first electric machine during a second mode;
the turbine engine including a compressor section, a combustor section, a turbine section, a core flowpath and a first rotating structure, the core flowpath extending through the compressor section, the combustor section and the turbine section, and the first rotating structure comprising a first turbine rotor disposed along the core flowpath within the turbine section;
the first electric machine comprising a first electric machine rotor, and the first electric machine rotor mechanically coupled to the propulsor rotor;
the clutch configured to operatively couple the first rotating structure to the first electric machine rotor during the first mode, and the clutch configured to operatively decouple the first rotating structure from the first electric machine rotor during the second mode; and
a geartrain operatively coupled between the clutch and the first electric machine rotor.