Aircraft power plant

Patent metadata

Field	Value
Publication number	US-10967983-B2
Application number	US-201916432118-A
Country	US
Kind code	B2
Filing date	Jun 5, 2019
Priority date	Jun 5, 2019
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

There is disclosed a cooling system for a liquid cooled internal combustion power plant housed in an engine compartment in a tail cone of an aircraft. The cooling system has: a tail cone inlet defined through a wall of the tail cone and fluidly communicating with an environment; a wall inlet defined through a firewall of the engine compartment; a blower within the engine compartment and having a blower inlet and a blower outlet, the blower inlet fluidly communicating with the environment via the tail cone inlet, via the wall inlet, and via an interior of the engine compartment; a blower outlet defined through a wall of the aircraft and fluidly communicating with the environment; and a cooling flow path extending from the tail cone inlet to the air outlet and across the wall inlet, the cooling flow path in heat exchange relationship with the power plant.

First claim

The invention claimed is:

1. A cooling system for a liquid cooled internal combustion power plant housed in an engine compartment in a tail cone of an aircraft, the cooling system comprising: a tail cone inlet defined through a wall of the tail cone and fluidly communicating with an environment outside the aircraft, the tail cone inlet located at an end of the tail cone; a wall inlet defined through a firewall of the engine compartment; a blower within the engine compartment and having a blower inlet and a blower outlet, the blower inlet fluidly communicating with the environment via the tail cone inlet, via the wall inlet, and via an interior of the engine compartment; an outlet defined through a wall of the aircraft and fluidly communicating with the environment, the blower outlet fluidly connected to a shroud duct extending within the tail cone from the firewall to the outlet; a cooling flow path extending from the tail cone inlet to the air outlet and across the wall inlet, the cooling flow path in heat exchange relationship with the liquid cooled internal combustion power plant; and an exhaust duct fluidly connected to an exhaust of the liquid cooled internal combustion aircraft power plant and to the environment, the exhaust duct extending within the shroud duct.

2. The cooling system of claim 1 , wherein the exhaust duct is angled relative to the shroud duct.

3. The cooling system of claim 1 , further comprising an air exhaust conduit fluidly connected to the blower and to the shroud duct, the air exhaust conduit having a top wall and a bottom wall opposed to the top wall, the bottom wall converging toward the top wall along a direction of an airflow circulating within the air exhaust conduit.

4. The cooling system of claim 1 , further comprising a heat exchanger having at least one first conduit fluidly connected to the environment via the tail cone inlet and the wall inlet and at least one second conduit in heat exchange relationship with the at least one first conduit and fluidly connectable to a coolant circuitry of the liquid cooled internal combustion aircraft power plant.

5. The cooling system of claim 4 , wherein the blower is located within a blower conduit having a conduit inlet fluidly connected to the environment via the tail cone inlet and a conduit outlet fluidly connected to the environment via the outlet, the heat exchanger disposed upstream of the conduit inlet, the at least one first conduit of the heat exchanger fluidly connected to the conduit inlet.

6. The cooling system of claim 1 , wherein a plenum is defined between the wall of the tail cone and the shroud duct, the blower inlet fluidly connected to the environment via the tail cone inlet, the plenum, and the wall inlet defined through the firewall.

7. The cooling system of claim 1 , wherein the blower is in driving engagement with a shaft of the liquid cooled internal combustion aircraft power plant.

8. The cooling system of claim 1 , further comprising an annular wall extending from the shroud duct to the wall of the tail cone, the annular wall in a sealing engagement with the shroud duct and with the wall of the tail cone.

9. The cooling system of claim 1 , wherein the tail cone inlet is defined by louvers defined by the wall of the tail cone.

10. The cooling system of claim 9 , wherein the louvers define openings facing away from an apex of the tail cone.

11. A method of operating a cooling system for a liquid cooled internal combustion aircraft power plant located within an engine compartment of a tail cone of an aircraft, comprising: driving a rotatable load with the liquid cooled internal combustion aircraft power plant and expelling exhaust gases of the liquid cooled internal combustion aircraft power plant to the environment via an exhaust duct; decreasing a pressure within the engine compartment relative to a pressure in the environment with a blower to draw cooling air from the environment into the engine compartment via a tail cone inlet and through a firewall of the engine compartment, the tail cone inlet located at an end of the tail cone; and cooling the liquid cooled internal combustion aircraft power plant using the cooling air by heating the drawn cooling air and expelling the heated drawn cooling air to the environment via a shroud duct extending from the firewall to the environment and disposed around the exhaust duct.

12. The method of claim 11 , wherein expelling the exhaust gases and expelling the heated drawn cooling air includes expelling the exhaust gases along a direction different than that of the heated drawn cooling air.

13. The method of claim 11 , wherein expelling the heated drawn cooling air includes accelerating the heated drawn cooling air downstream of the blower.

14. The method of claim 11 , wherein cooling the liquid cooled internal combustion aircraft power plant includes transferring heat from a liquid coolant circulating within a coolant circuitry of the liquid cooled internal combustion aircraft power plant to the drawn cooling air.

15. An aircraft power plant configured to be located within an engine compartment of a tail cone of an aircraft, comprising: an intermittent internal combustion engine; a tail cone inlet defined through a wall of the tail cone at an end of the tail cone and fluidly connected to an environment outside the aircraft; a wall inlet defined through a firewall of the engine compartment; a blower within the engine compartment and having a blower inlet and a blower outlet, the blower inlet fluidly connected to the environment via the tail cone inlet, via the wall inlet, and via an interior of the engine compartment; an outlet defined through a wall of the aircraft, the blower outlet fluidly connected to environment via a shroud duct extending within the tail cone from the firewall to the outlet; a cooling flow path extending from the tail cone inlet to the air outlet and across the wall inlet, the cooling flow path in heat exchange relationship with the intermittent internal combustion engine; and an exhaust duct fluidly connecting an exhaust of the liquid cooled internal combustion aircraft power plant to the environment, the shroud duct extending around the exhaust duct.

Assignees

• Pratt & Whitney Canada

Inventors

• Dionne Luc

Classifications

• B64D33/08 Primary

  of power plant cooling systems · CPC title

• B64C27/12 Primary

  Rotor drives · CPC title

• F02B53/14

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

• F01P5/06

  Guiding or ducting air to, or from, ducted fans · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title