Aircraft heating assembly with liquid cooled internal combustion engine and heating element using waste heat

1. An aircraft heating assembly comprising:

an internal combustion engine having a liquid coolant system distinct from both of a fuel system and a lubricating system of the internal combustion engine, the liquid cooling system including a plurality of cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet;

a coolant circulation path outside of the internal combustion engine, the coolant circulation path in fluid communication with the coolant inlet and the coolant outlet, the coolant circulation path extending through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant, the coolant circulation path distinct from the fuel system and distinct from the lubrication system of the engine;

a fluid circulation path having a portion running along an underside of a surface of an aircraft to be heated, the surface including a tailplane surface of the aircraft, the portion of the fluid circulation path in direct heat exchange relationship with the underside of the surface at locations of the surface susceptible to icing, the fluid circulation path in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom, the fluid circulation path distinct from both the fuel system and the lubrication system.

2. The assembly as defined in claim 1 , wherein the fluid circulation path is fluidly connected to the coolant circulation path, a fluid flowing in to the fluid circulation path being the liquid coolant.

3. The assembly as defined in claim 1 , wherein the coolant circulation path is in heat exchange relationship with the fluid circulation path through an additional heat exchanger.

4. The assembly as defined in claim 1 , further comprising a bypass conduit providing fluid communication between a first portion of the coolant circulation path upstream of the heat exchanger and a second portion of the coolant circulation path downstream of the heat exchanger, the bypass conduit including a valve modulated by a thermostat.

5. The assembly as defined in claim 1 , further comprising an electrical heating element in heat exchange relationship with the fluid circulation path.

6. The assembly as defined in claim 1 , further comprising at least one heating element in fluid communication with the fluid circulation path.

7. The assembly as defined in claim 1 , wherein the surface of the aircraft to be heated further includes at least a portion of at least one air inlet element of an air inlet communicating with the internal combustion engine.

8. The assembly as defined in claim 7 , wherein the at least one air inlet element is selected from the group consisting of: inlet door, inlet duct surface, flow splitter, acoustic panel, inlet plenum, and variable inlet guide vanes.

9. The assembly as defined in claim 1 , wherein the surface of the aircraft to be heated further includes an airfoil surface.

10. The assembly as defined in claim 1 , wherein the coolant circulation path is further in heat exchange relationship with one or both of engine oil and engine fuel of a main engine of the aircraft.

11. The assembly as defined in claim 1 , wherein the surface of the aircraft to be heated further includes a ram air inlet for a main engine of the aircraft.

12. The assembly as defined in claim 1 , wherein the coolant circulation path is further in heat exchange relationship with one or both of air and water in a passenger cabin of the aircraft.

13. The assembly as defined in claim 1 , wherein the coolant circulation path is further in heat exchange relationship with electronic or electrical equipment.

14. The assembly as defined in claim 1 , wherein the internal combustion engine is a Wankel rotary engine including a rotor having three apex portions mounted for eccentric revolutions within an internal cavity defined in a housing, the internal cavity having an epitrochoid shape with two lobes, the cooling passages being defined through the housing.

15. The assembly as defined in claim 1 , further comprising a compressor in fluid communication with an air inlet of the internal combustion engine, and a turbine in fluid communication with an exhaust of the internal combustion engine, the turbine compounded with the internal combustion engine.

16. An aircraft heating assembly comprising:

an internal combustion engine having a liquid coolant system distinct from both of a fuel system and a lubricating system of the internal combustion engine, the liquid cooling system including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, the internal combustion engine in driving engagement with a rotatable load;

a coolant circulation path outside of the internal combustion engine, the coolant circulation path in fluid communication with the coolant inlet and the coolant outlet, the coolant circulation path extending through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant;

a fluid circulation path having a portion running along an underside of a surface of an aircraft to be heated, the portion of the fluid circulation path in direct heat exchange relationship with the underside of the surface at locations of the surface susceptible to icing, the fluid circulation path in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom; and

a turbine in fluid communication with an exhaust of the internal combustion engine, the turbine in driving engagement with the rotatable load to compound power with the internal combustion engine in driving the rotatable load.