Aircraft propulsion system and method for operating same

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.

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.