Aircraft propulsion system and method for operating same

1 . A propulsion system for an aircraft, the propulsion system comprising:

an engine assembly including an engine, the engine including an air inlet, an exhaust outlet, and an engine output shaft, the engine output shaft is configured to be operably connected to a propulsor of the aircraft, and the engine is configured to drive rotation of the propulsor with the engine output shaft;

an interburner including an interburner inlet and an interburner outlet, the interburner is configured to mix and burn a gas from the interburner inlet with fuel to form a combustion gas;

a turbocompressor assembly including at least one turbocompressor, the at least one turbocompressor including a turbine and a compressor, the turbine including a turbine inlet and a turbine outlet, the compressor including a compressor inlet and a compressor outlet, the turbine and the compressor forming a rotational assembly, the rotational assembly including a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor, the shaft interconnecting the bladed turbine rotor and the bladed compressor rotor; and

a flow control assembly including an engine exhaust diverter subassembly and at least one compressor outlet diverter subassembly,

the engine exhaust diverter subassembly connected in fluid communication with and between the exhaust outlet, the interburner inlet, and the turbine inlet, the engine exhaust diverter subassembly selectively configurable in a first condition, a second condition, and a closed condition:

in the first condition, the engine exhaust diverter subassembly connecting the exhaust outlet in fluid communication with the interburner inlet,

in the second condition, the engine exhaust diverter subassembly connecting the exhaust outlet in fluid communication with the turbine inlet, and

in the closed condition, the engine exhaust diverter subassembly isolating the exhaust outlet from the interburner inlet and the turbine inlet, and

the at least one compressor outlet diverter subassembly connected in fluid communication with and between the compressor outlet, the air inlet, and the interburner inlet.

2 . The propulsion system of claim 1 , wherein the at least one compressor outlet diverter subassembly is selectively configurable in a first condition, a second condition, and a closed condition:

in the first condition, the at least one compressor outlet diverter subassembly connects the compressor outlet in fluid communication with the air inlet,

in the second condition, the at least one compressor outlet diverter subassembly connects the compressor outlet in fluid communication with the interburner inlet, and

in the closed condition, the at least one compressor outlet diverter subassembly isolates the compressor outlet from the air inlet and the interburner inlet.

3 . The propulsion system of claim 1 , wherein the engine assembly further includes an intercooler, the intercooler is connected in fluid communication with and between the at least one compressor outlet diverter subassembly and the air inlet.

4 . The propulsion system of claim 3 , wherein the intercooler includes a particle separator.

5 . The propulsion system of claim 1 , further comprising an electrical assembly including at least one electric generator, and the at least one electric generator is operably connected to the rotational assembly of one or more turbocompressors of the at least one turbocompressor.

6 . The propulsion system of claim 5 , wherein the turbocompressor assembly further includes a first gearbox, and the first gearbox is operably connected to and between the at least one generator and the rotational assembly of the one or more turbocompressors of the at least one turbocompressor.

7 . The propulsion system of claim 6 , wherein the engine assembly further includes a second gearbox, the electrical assembly includes a first electric motor electrically connected to the at least one electric generator, and the engine output shaft and the first electric motor are operably connected to the second gearbox.

8 . The propulsion system of claim 7 , wherein the electrical assembly further includes an energy storage device electrically connected to the at least one electric generator and the first electric motor.

9 . The propulsion system of claim 7 , wherein the engine output shaft is operably connected to the second gearbox by a one-way clutch.

10 . The propulsion system of claim 1 , wherein:

the at least one turbocompressor includes a first turbocompressor and a second turbocompressor;

the at least one compressor outlet diverter subassembly includes a first compressor outlet diverter subassembly and a second compressor outlet diverter subassembly;

the first compressor outlet diverter subassembly is connected in fluid communication with and between the compressor outlet of the compressor of the first turbocompressor, the air inlet, and the interburner inlet; and

the second compressor outlet diverter subassembly is connected in fluid communication with and between the compressor outlet of the compressor of the second turbocompressor, the air inlet, and the interburner inlet.

11 . The propulsion system of claim 10 , further comprising an electrical assembly including a first electric generator and a second electric generator, wherein the first electric generator is operably connected to the rotational assembly of the first turbocompressor and the second electric generator is operably connected to the rotational assembly of the second turbocompressor.

12 . The propulsion system of claim 1 , wherein the engine is an intermittent combustion engine.

13 . A propulsion system for an aircraft, the propulsion system comprising:

an engine assembly including an engine, the engine including an air inlet, an exhaust outlet, and an engine output shaft, the engine output shaft is configured to be operably connected to a propulsor of the aircraft, and the engine is configured to drive rotation of the propulsor with the engine output shaft;

an interburner including an interburner inlet and an interburner outlet, the interburner is configured to mix and burn a gas from the interburner inlet with fuel to form a combustion gas;

a turbocompressor assembly including at least one turbocompressor, the at least one turbocompressor including a turbine and a compressor, the turbine including a turbine inlet and a turbine outlet, the compressor including a compressor inlet and a compressor outlet, the turbine and the compressor forming a rotational assembly, the rotational assembly including a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor, the shaft interconnecting the bladed turbine rotor and the bladed compressor rotor; and

a flow control assembly including an engine exhaust diverter subassembly and at least one compressor outlet diverter subassembly,

the engine exhaust diverter subassembly connected in fluid communication with and between the exhaust outlet, the interburner inlet, and the turbine inlet, and

the at least one compressor outlet diverter subassembly connected in fluid communication with and between the compressor outlet, the air inlet, and the interburner inlet, the at least one compressor outlet diverter subassembly selectively configurable in a first condition, a second condition, and a closed condition:

in the first condition, the at least one compressor outlet diverter subassembly connecting the compressor outlet in fluid communication with the air inlet,

in the second condition, the at least one compressor outlet diverter subassembly connecting the compressor outlet in fluid communication with the interburner inlet, and

in the closed condition, the at least one compressor outlet diverter subassembly isolating the compressor outlet from the air inlet and the interburner inlet.

14 . The propulsion system of claim 13 , wherein the engine assembly further includes an intercooler, the intercooler is connected in fluid communication with and between the at least one compressor outlet diverter subassembly and the air inlet.

15 . The propulsion system of claim 13 , further comprising an electrical assembly including at least one electric generator, and the at least one electric generator is operably connected to the rotational assembly of one or more turbocompressors of the at least one turbocompressor.

16 . The propulsion system of claim 15 , wherein the turbocompressor assembly further includes a first gearbox, and the first gearbox is operably connected to and between the at least one generator and the rotational assembly of the one or more turbocompressors of the at least one turbocompressor.

17 . The propulsion system of claim 16 , wherein the engine assembly further includes a second gearbox, the electrical assembly includes a first electric motor electrically connected to the at least one electric generator, and the engine output shaft and the first electric motor are operably connected to the second gearbox.

18 . The propulsion system of claim 17 , wherein the electrical assembly further includes an energy storage device electrically connected to the at least one electric generator and the first electric motor.

19 . The propulsion system of claim 17 , wherein the engine output shaft is operably connected to the second gearbox by a one-way clutch.

20 . A propulsion system for an aircraft, the propulsion system comprising:

an engine assembly including an engine, the engine including an air inlet, an exhaust outlet, and an engine output shaft, the engine output shaft is configured to be operably connected to a propulsor of the aircraft, and the engine is configured to drive rotation of the propulsor with the engine output shaft;

an interburner including an interburner inlet and an interburner outlet, the interburner is configured to mix and burn a gas from the interburner inlet with fuel to form a combustion gas;

a turbocompressor assembly including at least one turbocompressor, the at least one turbocompressor including a turbine and a compressor, the turbine including a turbine inlet and a turbine outlet, the compressor including a compressor inlet and a compressor outlet, the turbine and the compressor forming a rotational assembly, the rotational assembly including a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor, the shaft interconnecting the bladed turbine rotor and the bladed compressor rotor, the at least one turbocompressor including a first turbocompressor and a second turbocompressor; and

a flow control assembly including an engine exhaust diverter subassembly and at least one compressor outlet diverter subassembly,

the engine exhaust diverter subassembly connected in fluid communication with and between the exhaust outlet, the interburner inlet, and the turbine inlet, and

the at least one compressor outlet diverter subassembly including a first compressor outlet diverter subassembly and a second compressor outlet diverter subassembly, the first compressor outlet diverter subassembly connected in fluid communication with and between the compressor outlet of the first turbocompressor, the air inlet, and the interburner inlet, the second compressor outlet diverter subassembly connected in fluid communication with and between the compressor outlet of the second turbocompressor, the air inlet, and the interburner inlet.