Aircraft power plant

Patent metadata

Field	Value
Publication number	US-11866181-B2
Application number	US-202117475848-A
Country	US
Kind code	B2
Filing date	Sep 15, 2021
Priority date	Sep 15, 2021
Publication date	Jan 9, 2024
Grant date	Jan 9, 2024

Abstract

Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

First claim

What is claimed is:

1. An aircraft power plant comprising:
an internal combustion (IC) engine using intermittent combustion during operation, the IC engine being drivingly connected to a load via a gearbox to transfer motive power from the IC engine to the load, the IC engine having an exhaust outlet for discharging a flow of first exhaust gas;
a combustor including:
a combustor inlet in fluid communication with the exhaust outlet of the IC engine to receive the flow of first exhaust gas from the IC engine into the combustor;
a fuel injector for injecting fuel into the combustor in which the fuel is mixed with the first exhaust gas and ignited to generate a flow of second exhaust gas; and
a combustor outlet for discharging the flow of second exhaust gas;

a turbocharger associated with the IC engine, the turbocharger including:
a turbine in fluid communication with the combustor outlet and driven by the flow of second exhaust gas, the turbine being drivingly connected to the load to transfer motive power from the turbine to the load; and
a compressor drivingly connected to the turbine and driven by the turbine to compress combustion air for the IC engine; and

a continuously variable transmission, the turbine being drivingly connected to the load via the continuously variable transmission and the gearbox.

2. The aircraft power plant as defined in claim 1 , comprising a shaft drivingly connecting the turbine and the compressor, the turbine being drivingly connected to the load via the shaft.

3. The aircraft power plant as defined in claim 1 , wherein:
the IC engine includes a combustion chamber; and
the exhaust outlet of the IC engine is configured to discharge the flow of first exhaust gas from the combustion chamber of the IC engine.

4. The aircraft power plant as defined in claim 1 , wherein the IC engine is a Wankel engine.

5. The aircraft power plant as defined in claim 1 , comprising a liquid cooling system for cooling the IC engine, the liquid cooling system including:
a heat exchanger to promote heat transfer from a coolant fluid carrying heat from the IC engine to ambient air; and
a fan mechanically driven by the IC engine via a variable speed transmission to drive the ambient air through the heat exchanger.

6. The aircraft power plant as defined in claim 1 , wherein:
the IC engine is a first IC engine; and
the aircraft power plant includes a second IC engine drivingly connected to the load.

7. A helicopter comprising the aircraft power plant as defined in claim 6 , wherein the load includes a main rotor of the helicopter.

8. An aircraft comprising the aircraft power plant as defined in claim 1 .

9. The aircraft power plant as defined in claim 1 , comprising variable-orientation guide vanes configured to guide a flow of ambient air being delivered to the compressor.

10. The aircraft power plant as defined in claim 1 , comprising a muffler in fluid communication with the turbine to permit the flow of second exhaust gas flowing through the turbine to be discharged via the muffler.

11. The aircraft power plant as defined in claim 1 , comprising an intercooler disposed between the compressor and the IC engine to remove heat added to the combustion air by the compressor.

12. The aircraft power plant as defined in claim 5 , comprising variable-orientation guide vanes guiding a flow of ambient air being delivered to the fan.

Assignees

• Pratt & Whitney Canada

Inventors

• Dussault Serge

Classifications

• B64D27/04 Primary

  of piston type · CPC title

• F02B3/10

  with intermittent fuel introduction · CPC title

• F02B37/001

  using exhaust drives arranged in parallel · CPC title

• F02B53/10

  Fuel supply; Introducing fuel to combustion space · CPC title

• F02B53/14

  Adaptations of engines for driving, or engine combinations with, other devices · CPC title