Active control flow system and method of cooling and providing active flow control

Patent metadata

Field	Value
Publication number	US-11525388-B2
Application number	US-201816210465-A
Country	US
Kind code	B2
Filing date	Dec 5, 2018
Priority date	Mar 18, 2016
Publication date	Dec 13, 2022
Grant date	Dec 13, 2022

Abstract

A method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.

First claim

The invention claimed is:

1. An active flow control system for an aircraft, comprising:
a flight control surface being movable for controlling the aircraft;
a boundary layer control system in fluid communication with a boundary layer region of the flight control surface, the flight control surface movable relative to the boundary layer control system;
a duct in fluid communication with the boundary layer control system;
a heat exchanger having air passages in fluid communication with the duct and fluid passages in heat exchange relationship with the air passages, the fluid passages for receiving a cooling fluid of the aircraft; and
a forced air driver in fluid communication with the duct for driving an airflow therethrough and through the boundary layer control system.

2. The system as defined in claim 1 , wherein the boundary layer control system includes a plurality of openings defined through the flight control surface in fluid communication with a portion of the duct extending upstream of the heat exchanger.

3. The system as defined in claim 1 , wherein the boundary layer control system includes a plurality of nozzles oriented to direct a flow on a surface of the flight control surface, the nozzles in fluid communication with a portion of the duct extending downstream of the heat exchanger.

4. The system as defined in claim 1 , further comprising an exhaust conduit communicating with the duct between the heat exchanger and the boundary layer control system, and a valve modulating the communication between the exhaust conduit and the duct.

5. The system as defined in claim 1 , wherein the fluid passages of the heat exchanger are configured to receive a liquid coolant.

6. An assembly comprising an engine core including at least one rotary internal combustion engine and the system as defined in claim 1 , each rotary internal combustion engine having a housing including cooling passages in fluid communication with the fluid passages of the heat exchanger.

7. An active flow control system for an aircraft, comprising:
a boundary layer control system in fluid communication with a surface in a low pressure recovery area of the aircraft;
a duct in fluid communication with the boundary layer control system;
a heat exchanger having air passages in fluid communication with the duct and fluid passages in heat exchange relationship with the air passages, the fluid passages for receiving a cooling fluid of the aircraft;
a forced air driver in fluid communication with the duct for driving an airflow therethrough and through the boundary layer control system;
an exhaust conduit having an exhaust conduit inlet communicating with the duct between the heat exchanger and the boundary layer control system and an exhaust conduit outlet communicating with an environment outside the aircraft, the exhaust conduit outlet distinct from an outlet of the duct; and
a valve modulating the communication between the exhaust conduit and the duct, the valve having a closed configuration in which the exhaust conduit inlet is disconnected from the duct and an open configuration in which the duct is fluidly connected to the exhaust conduit outlet and in which a portion of the airflow flows through the duct and through the exhaust conduit thereby bypassing the boundary layer control system.

8. The system as defined in claim 7 , wherein the low pressure recovery area includes a leading edge region extending from a leading edge of an airfoil.

9. The system as defined in claim 8 , wherein the airfoil is an airfoil of a wing of the aircraft, a tail of the aircraft and/or a control surface of the aircraft.

10. The system as defined in claim 7 , wherein the boundary layer control system includes a plurality of openings defined through the surface in fluid communication with a portion of the duct extending upstream of the heat exchanger.

11. The system as defined in claim 7 , wherein the boundary layer control system includes a plurality of nozzles oriented to direct a flow on the surface, the nozzles in fluid communication with a portion of the duct extending downstream of the heat exchanger.

12. The system as defined in claim 7 , wherein the fluid passages of the heat exchanger are configured to receive a liquid coolant.

13. The system as defined in claim 7 , wherein the forced air driver is a fan rotating within the duct.

14. The system as defined in claim 1 , wherein the forced air driver is a fan rotating within the duct.

15. The system as defined in claim 13 , wherein the fan is located downstream of the heat exchanger.

16. The system as defined in claim 14 , wherein the fan is located downstream of the heat exchanger.

17. An assembly for an aircraft comprising: an intermittent internal combustion engine being liquid cooled and having at least one cooling passage; a heat exchanger having at least one air passage and at least one fluid passage, the at least one fluid passage fluidly connected to the at least one cooling passage of the intermittent internal combustion engine; a duct fluidly connected to a boundary layer region of a surface of the aircraft, the duct fluidly connected to the at least one air passage of the heat exchanger, the duct having an inlet in fluid flow communication with an environment outside the aircraft and an outlet in fluid flow communication with the boundary layer region of the aircraft for injecting air into the boundary layer region; and a forced air driver in fluid communication with the duct for driving an airflow therethrough and from the boundary layer region of the aircraft.

18. The assembly as defined in claim 17 , wherein the duct is fluidly connected to the boundary layer region via a plurality of openings defined through the surface of the aircraft.

19. The assembly as defined in claim 17 , further comprising a plurality of nozzles oriented to direct a flow on the surface of the aircraft, the nozzles in fluid communication with a portion of the duct extending downstream of the heat exchanger.

Assignees

• Pratt & Whitney Canada

Inventors

• Thomassin Jean
• Meisels David
• Ullyott Richard

Classifications

• B64D33/10

  Radiator arrangement · CPC title

• Y02T50/40

  Weight reduction · CPC title

• F01P3/20

  Cooling circuits not specific to a single part of engine or machine (F01P3/22 takes precedence) · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F01P5/10

  Pumping liquid coolant; Arrangements of coolant pumps · CPC title