Aircraft propulsion system

Patent metadata

Field	Value
Publication number	US-12583596-B2
Application number	US-202418435629-A
Country	US
Kind code	B2
Filing date	Feb 7, 2024
Priority date	Feb 7, 2024
Publication date	Mar 24, 2026
Grant date	Mar 24, 2026

Abstract

A propulsion system for an aircraft includes an engine assembly and a turbocompressor. The engine assembly includes an engine and an interburner. The engine includes an engine output shaft. The engine is configured to drive rotation of a propulsor with the engine output shaft. The interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The turbine is connected in fluid communication with the interburner to receive the combustion gas. The compressor is connected in fluid communication with the engine to direct a compressed air to the engine. The rotational assembly is mechanically independent of the engine output shaft.

First claim

The invention claimed is:

1 . A propulsion system for an aircraft, the propulsion system comprising:
an engine assembly including an engine and an interburner,
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, and
the interburner is connected in fluid communication with the exhaust outlet, the interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas; and
a turbocompressor including a turbine and a compressor, 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 turbine is connected in fluid communication with the interburner to receive the combustion gas, the compressor is connected in fluid communication with the air inlet to direct a compressed air to the engine, and the rotational assembly is mechanically independent of the engine output shaft.

2 . The propulsion system of claim 1 , wherein the engine assembly further includes a gearbox, and the gearbox is configured to operably connect the engine output shaft to the propulsor.

3 . The propulsion system of claim 2 , further comprising an electrical assembly, the electrical assembly including an electric generator, the electric generator is operably connected to the rotational assembly, and the rotational assembly is configured to drive rotation of the electric generator to generate electrical power for one or more electrical aircraft loads of the aircraft.

4 . The propulsion system of claim 3 , wherein the electrical assembly further includes an electric motor electrically connected to the electric generator, and the gearbox is configured to operably connect the electric motor to the propulsor.

5 . The propulsion system of claim 4 , wherein the electric motor is operably connected to the gearbox by a one-way clutch.

6 . The propulsion system of claim 4 , wherein the electrical assembly further includes an energy storage device electrically connected to the electric generator and the electric motor.

7 . 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 compressor and the air inlet, and the intercooler is configured to cool the compressed air from the compressor.

8 . The propulsion system of claim 7 , further comprising an air intake, and the air intake is connected in fluid communication with the compressor and the intercooler to supply ambient air to the compressor and the intercooler.

9 . The propulsion system of claim 8 , further comprising the propulsor, and the propulsor is connected in fluid communication with and between the air intake upstream of the propulsor and the compressor and the intercooler downstream of the propulsor.

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

11 . An unmanned aerial vehicle (UAV) comprising:
a propulsor; an engine assembly including an engine and an interburner,
the engine including an air inlet, an exhaust outlet, and an engine output shaft, the engine output shaft is operably connected to the propulsor, and the engine is configured to drive rotation of the propulsor with the engine output shaft, and
the interburner is connected in fluid communication with the exhaust outlet, the interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas;
a turbocompressor including a turbine and a compressor, the turbine is connected in fluid communication with the interburner to receive the combustion gas, the compressor is connected in fluid communication with the air inlet to direct a compressed air to the engine, and the turbocompressor is mechanically independent of the engine output shaft; and an electrical assembly including an electric generator operably connected to the turbine, and the electrical assembly is electrically connected to one or more electrical aircraft loads of the UAV.

12 . The UAV of claim 11 , wherein the electrical assembly further includes an electric motor electrically connected to the electric generator, and the electric motor is operably connected to the engine output shaft and the propulsor.

13 . The UAV of claim 12 , wherein the electrical assembly further includes an energy storage device electrically connected to the electric generator and the electric motor.

14 . The UAV of claim 11 , wherein the engine assembly further includes an intercooler, the intercooler is connected in fluid communication with and between the compressor and the air inlet, and the intercooler is configured to cool the compressed air from the compressor.

15 . The UAV of claim 11 , wherein the engine is an intermittent combustion engine.

16 . A propulsion system for an aircraft, the propulsion system comprising:
an engine assembly including an intermittent combustion engine, the intermittent combustion 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 intermittent combustion engine is configured to drive rotation of the propulsor with the engine output shaft; a turbocompressor including a turbine and a compressor, the turbine is connected in fluid communication with the exhaust outlet, the compressor is connected in fluid communication with the air inlet to direct a compressed air to the engine, and the turbocompressor is mechanically independent of the engine output shaft; and an electrical assembly including an electric generator, an electric motor, and an electrical distribution system electrically connecting the electric generator and the electric motor, the electric generator is operably connected to the turbine, and the electric motor is operably connected to the engine output shaft.

17 . The propulsion system of claim 16 , wherein the engine assembly further includes an interburner, the interburner includes an interburner inlet and an interburner outlet, the interburner inlet is connected in fluid communication with the exhaust outlet, the interburner is configured to mix and burn an exhaust gas from the intermittent combustion engine with fuel to form a combustion gas and direct the combustion gas to the turbine through the interburner outlet.

18 . The propulsion system of claim 16 , wherein the engine assembly further includes a gearbox, and the gearbox is configured to operably connect the engine output shaft to the propulsor.

19 . The propulsion system of claim 18 , wherein the electric motor is operably connected to the engine output shaft by the gearbox.

20 . The propulsion system of claim 16 , wherein the engine assembly further includes an intercooler, the intercooler is connected in fluid communication with and between the compressor and the air inlet, and the intercooler is configured to cool the compressed air from the compressor.

Assignees

• Pratt & Whitney Canada

Inventors

• Tomes Nathan

Classifications

• F02C6/18

  using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants (using waste heat as source of energy for refrigeration plants F25B27/02; using the waste heat of a gasturbine for steam generation or in a steam cycle see F01K23/10) · CPC title

• F02C5/00

  Gas-turbine plants characterised by the working fluid being generated by intermittent combustion · CPC title

• F01D15/12

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title

• F01D15/10

  Adaptations for driving, or combinations with, electric generators · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title