Aircraft power plant cooling system

Patent metadata

Field	Value
Publication number	US-11352885-B2
Application number	US-202016842981-A
Country	US
Kind code	B2
Filing date	Apr 8, 2020
Priority date	Apr 8, 2020
Publication date	Jun 7, 2022
Grant date	Jun 7, 2022

Abstract

A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.

First claim

The invention claimed is:

1. A cooling system for an aircraft power plant, comprising:
a ram air inlet duct;
a cooling plenum having an inlet fluidly connected to an outlet of the ram air inlet duct, a first outlet and a second outlet, the first outlet selectively closable;
a heat exchanger including at least one first conduit having an inlet fluidly connected to the cooling plenum 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 aircraft power plant, the at least one first conduit having an outlet fluidly connected to the first outlet and the second outlet of the cooling plenum; and
a flow inducing device operable for selectively inducing a flow of air from the inlet of the cooling plenum to the second outlet thereof when the first outlet of the cooling plenum is closed.

2. The cooling system as defined in claim 1 , wherein the ram air inlet duct has a ram air inlet located at a base of a vertical stabilizer of an aircraft, at a leading edge thereof.

3. The cooling system as defined in claim 2 , wherein the ram air inlet has a forward facing cross-section when taken along an aircraft longitudinal axis.

4. The cooling system as defined in claim 3 , wherein the forward facing cross-section is transverse to the aircraft longitudinal axis.

5. The cooling system as defined in claim 1 , wherein the flow inducing device includes a blower having a blower scroll and a blower rotor encased in the blower scroll.

6. The cooling system as defined in claim 1 , further comprising variable inlet guide vanes fluidly connected to the second outlet, upstream of the flow inducing device to control a volume of air flow entering the flow inducing device.

7. The cooling system as defined in claim 1 , wherein the cooling plenum has an aperture closing device to selectively close or open the first outlet.

8. The cooling system as defined in claim 7 , wherein the aperture closing device includes an actuated door.

9. The cooling system as defined in claim 8 , wherein the wall of the cooling plenum coincides with an external wall of a tail cone section of an aircraft.

10. The cooling system as defined in claim 1 , wherein the cooling plenum defines a selectively closable air inlet in a wall thereof upstream of the heat exchanger.

11. The cooling system as defined in claim 10 , wherein the cooling plenum has an aperture closing device to selectively close or open the selectively closable air inlet.

12. The cooling system as defined in claim 11 , wherein the aperture closing device of the cooling plenum includes an actuated door.

13. The cooling system as defined in claim 10 , wherein the selectively closable air inlet is fluidly connected to an inside area of a tail cone compartment, an external wall of the tail cone compartment including louver panels allowing outboard air to penetrate the inside area of the tail cone compartment.

14. The cooling system as defined in claim 1 , further comprising a discharge duct downstream of the flow inducing device and fluidly connected therewith, the discharged duct in fluid communication with an environment outside the aircraft to route an air outflow of the flow inducing device in the environment.

15. A method of cooling an aircraft power plant having a combustion engine, the aircraft power plant provided on an aircraft, the method comprising:
in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft; and
in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable outlet of the air conduit downstream of the heat exchanger.

16. The method as defined in claim 15 , wherein bypassing the cooling air from the flow inducing device in the second operating mode includes actuating an aperture closing device at the selectively closable outlet to open the selectively closable outlet.

17. The method as defined in claim 15 , wherein the air conduit defines a plenum fore section and a plenum aft section downstream of the plenum fore section, the method further comprising, in the first operating mode, opening a secondary selectively closable inlet defined in the plenum aft section and fluidly connected to an inside area of a tail cone compartment, and providing a flow path from the inside area of a tail cone compartment to the air conduit.

18. The method as defined in claim 15 , wherein bypassing the cooling air from the flow inducing device in the second operating mode includes preventing the cooling air flow from passing through the flow inducing device by closing variable guide vanes located upstream of an inlet of the flow inducing device.

19. The method as defined in claim 15 , further comprising in the second a mode, inducing the cooling air flow through the heat exchanger via a ram air inlet duct of the air conduit, including ingesting cooling air at a ram air inlet located at a base of a vertical stabilizer of the aircraft, at a leading edge of said vertical stabilizer.

20. A method of cooling a power plant of an aircraft, the method comprising:
in a first operating mode, driving a flow inducing device to induce a flow of cooling air through a heat exchanger connected in heat exchange relationship with the power plant of the aircraft; and
in a second, in flight, operating mode, bypassing the flow inducing device and instead of using an airflow induced by the flow inducing device, using ram air to provide cooling air to the heat exchanger.

Assignees

• Pratt & Whitney Canada

Inventors

• Dionne Luc

Classifications

• Y02T10/12

  Improving ICE efficiencies · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• F01P2003/006

  the liquid being oil · CPC title

• F01P7/10

  by throttling amount of air flowing through liquid-to-air heat exchangers · CPC title

• F01P3/18

  Arrangements or mounting of liquid-to-air heat-exchangers (such arrangements on cylinders or cylinder heads F01P3/04; relative to vehicles B60K11/04) · CPC title