Methods and apparatuses for controlling airflow proximate to engine/airfoil systems

• US 6,978,971 B1
• Filed: 06/15/2004
• Issued: 12/27/2005
• Est. Priority Date: 06/15/2004
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Dun, Roy
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US10/868,238
• Publication Number:
  US 20050274846A1
• Time in Patent Office: 560 Days
• Field of Search: 244/213, 244/216, 244218-219, 244/130, 244/54, 244/55
• US Class Current: 244/214
• CPC Class Codes: B64C 7/02 Nacelles
• CPC Class Codes: B64C 9/24 by single flap
• CPC Class Codes: B64D 27/18 within, or attached to, wings
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

Methods and apparatuses for controlling airflow proximate to engine/airfoil systems are disclosed. In one embodiment, an aircraft system includes an airfoil and an engine unit at least proximate to the airfoil with a gap between a portion of the airfoil and a portion of the engine unit. The system can further include a flow control device proximate to the gap and positionable among at least three stationary positions, including a retracted position in which the gap has a first area through which fluid can flow, a first extended position in which the gap is at least approximately aerodynamically sealed, and a second extended position in which the gap has a second smaller area through which fluid can flow. A control system can be coupled to the flow control device to move the flow control device among these positions.

Claims

1. An aircraft system comprising:

an airfoil;

an engine unit having a housing at least proximate to the airfoil with a gap extending between a portion of the airfoil and a portion of the housing of the engine unit; and

a flow control device proximate to the gap and positionable among at least three stationary positions, including;

a retracted position in which the gap has a first area through which fluid flows during flight;

a first extended position in which the gap is at least approximately aerodynamically sealed during flight; and

a second extended position in which the gap has a second area through which fluid flows during flight, the second area being smaller than the first area.

2. The system of claim 1 wherein the flow control device includes multiple flow surface sections movable relative to each other.

3. The system of claim 1 wherein the engine unit includes a pylon, the engine unit being coupled to the airfoil via the pylon, the engine unit being positioned under the airfoil with a portion of the engine unit extending forward of a leading edge of the airfoil.

4. The system of claim 1 wherein the flow control device is coupled to the airfoil.

5. The system of claim 1 wherein the engine unit includes a pylon and the flow control device is coupled to the pylon.

6. The system of claim 1 wherein the flow control device is coupled to the housing.

7. The system of claim 1 wherein the engine unit includes a thrust reverser, at least a portion of the engine housing being coupled to the thrust reverser to move when the thrust reverser is deployed, and wherein at least a portion of the flow control device moves with the engine housing when the flow control device is in the first extended position.

8. The system of claim 1, further comprising a control system coupled to the flow control device to position the flow control device among the retracted, first extended, and second extended positions.

9. The system of claim 1, further comprising a control system coupled to the flow control device to position the flow control device among the retracted, first extended, and second extended positions, the control system having at least one actuator, the at least one actuator including at least one hydraulic actuator.

10. The system of claim 1, further comprising a control system coupled to the flow control device to position the flow control device among the retracted, first extended, and second extended positions, the control system having at least one actuator, the at least one actuator including at least one electric actuator.

11. The system of claim 1, further comprising a control system coupled to the flow control device to position the flow control device among the retracted, first extended, and second extended positions, at least a portion of the control system including a computer.

12. The system of claim 1, further comprising a control system coupled to the flow control device to position the flow control device among the retracted, first extended, and second extended positions, the control system including:

a first actuator coupled to the flow control device to position the flow control device between the retracted and first extended positions; and

a second actuator coupled to the flow control device to position the flow control device between the first and second extended positions.

13. The system of claim 1, further comprising a control system coupled to the flow control device to position the flow control device among the retracted, first extended, and second extended positions, wherein the flow control device includes a first portion and a second portion and wherein only the second portion of the flow control device moves when the flow control device is positioned between the first extended position and the second extended position.

14. The system of claim 1 wherein the airfoil includes at least one leading edge device laterally disposed from the flow control device and wherein the flow control device is at least approximately aerodynamically sealed against a portion of a lateral edge of the leading edge device when the flow control device is in at least one of the first and second extended positions.

15. The system of claim 1 wherein the engine unit includes a pylon and wherein the flow control device is at least approximately aerodynamically sealed against at least a portion of the pylon.

16. The system of claim 1 wherein the engine unit includes a pylon, the engine unit being coupled to the airfoil via the pylon, the engine unit being positioned under the airfoil with a portion of the engine unit extending forward of the leading edge of the airfoil, a portion of the pylon being positioned behind the gap.

17. The system of claim 1 wherein the airfoil, engine unit, and flow control device are installed on an aircraft.

18. The system of claim 1 wherein the flow control device includes a Krueger flap.

19. The system of claim 1 wherein the flow control device includes a slat.

20. The system of claim 1 wherein the flow control device includes a variable camber leading edge device.

21. The system of claim 1, further comprising a control system coupled to the flow control device to position the flow control device among the retracted, first extended, and second extended positions, the control system including:

a first actuator coupled to the flow control device to position the flow control device between the retracted and first extended positions; and

a second actuator coupled to the flow control device to position the flow control device between the first and second extended positions; and

wherein;

the engine unit includes a pylon, the engine unit being coupled to the airfoil via the pylon, the engine unit being positioned under the airfoil with a portion of the engine unit extending forward of a leading edge of the airfoil, and

the flow control device depends from the airfoil and includes multiple flow surface sections movable relative to each other.

22. An aircraft system comprising:

an airfoil;

an engine unit at least proximate to the airfoil, the engine unit including a pylon and a housing, the engine unit being coupled to the airfoil via the pylon, the engine unit being positioned under the airfoil with a portion of the engine unit extending forward of a leading edge of the airfoil, a gap extending between a portion of the housing and a portion of the leading edge of the airfoil;

a flow control device coupled to the airfoil and having multiple flow surface sections movable relative to each other, the flow control device being positionable among at least three stationary positions, including;

a retracted position in which the gap has a first area through which fluid can flow;

a first extended position in which the gap is at least approximately aerodynamically sealed; and

a second extended position in which the gap has a second area through which fluid can flow, the second area being smaller than the first area; and

a control system coupled to the flow control device to position the flow control device among the retracted, first extended, and second extended positions, the control system including;

a first actuator coupled to the flow control device to position the flow control device between the retracted and first extended positions; and

a second actuator coupled to the flow control device to position the flow control device between the first and second extended positions.

23. The system of claim 22 wherein the airfoil, engine unit, and flow control device are installed on an aircraft.

24. An aircraft system comprising:

an airfoil;

an engine unit at least proximate to the airfoil with a gap between a portion of the airfoil and a portion of the engine unit; and

a flow control means for controlling the flow of fluid through the gap, the flow control means having at least three stationary positions, including;

a retracted position in which the gap has a first area through which fluid can flow;

a first extended position in which the gap is at least approximately aerodynamically sealed; and

a second extended position in which the gap has a second area through which fluid can flow, the second area being smaller than the first area.

25. The system of claim 24 wherein the airfoil, engine unit, and flow control means are installed on an aircraft.

26. A method for making an aircraft system comprising:

installing a flow control device at least proximate to an airfoil and an engine unit having a housing;

coupling a control system to the flow control device; and

configuring the control system to position the flow control device among at least three stationary positions, including;

a retracted position in which a gap extending between a portion of the airfoil and a portion of the housing of the engine unit has a first area through which fluid flows during flight;

a first extended position in which the gap is at least approximately aerodynamically sealed during flight; and

a second extended position in which the gap has a second area through which fluid flows during flight, the second area being smaller than the first area.

27. The method of claim 26 wherein installing a flow control device includes installing a flow control device having multiple flow surface sections that are movable relative to each other.

28. The method of claim 26 wherein installing a flow control device at least proximate to an airfoil and an engine unit includes installing a flow control device proximate to an airfoil and an engine unit on an aircraft, the engine unit having a pylon, the engine unit being coupled to the airfoil via the pylon, the engine unit being positioned under the airfoil with a portion of the engine unit extending forward of a leading edge of the airfoil.

29. The method of claim 26 wherein installing a flow control device includes coupling a flow control device to the airfoil.

30. The method of claim 26 wherein installing a flow control device includes coupling a flow control device to a portion of the engine unit.

31. The method of claim 26 wherein configuring a control system includes configuring a computer.

32. The method of claim 26 wherein configuring the control system to position the flow control device includes configuring the control system to position the flow control device in the second extended position to increase at least one of a maximum lift coefficient or a lift to drag ratio of a portion of the airfoil.

33. The method of claim 26 wherein configuring the control system to position the flow control device includes configuring the control system to position the flow control device in the first extended position to increase at least one of a maximum lift coefficient or a lift to drag ratio of a portion of the airfoil.

34. The method of claim 26 wherein configuring the control system to position the flow control device includes configuring the control system to position the flow control device in the first extended position to decrease the drag coefficient of a portion of the airfoil.

35. The method of claim 26 wherein configuring the control system to position the flow control device includes configuring the control system to position the flow control device in the second extended position to decrease the drag coefficient of a portion of the airfoil.

36. The method of claim 26 wherein installing a flow control device at least proximate to an airfoil and an engine unit includes coupling a flow control device to an airfoil on an aircraft, the flow control device having multiple flow surface sections that are movable relative to each other, the engine unit having a pylon, the engine unit being coupled to the airfoil via the pylon, the engine unit being positioned under the airfoil with a portion of the engine unit extending forward of a leading edge of the airfoil.

37. A method for operating an aircraft comprising:

positioning a flow control device of the aircraft in a first extended position in which a gap extending between a portion of an airfoil and a portion of a housing of an engine unit is at least approximately aerodynamically sealed during flight;

flying the aircraft with the flow control device in the first extended position;

positioning the flow control device of the aircraft in a retracted position in which the gap has a first area through which air flows during flight;

flying the aircraft with the flow control device in the retracted position;

positioning the flow control device of the aircraft in a second extended position in which the gap has a second area through which air flows during flight, the second area being smaller than the first area; and

flying the aircraft with the flow control device in the second extended position.

38. The method of claim 37 wherein flying the aircraft with the flow control device in the retracted position includes flying the aircraft during a cruise phase of flight with the flow control device in the retracted position.

39. The method of claim 37 wherein flying the aircraft with the flow control device in the first extended position includes flying the aircraft during a takeoff phase of flight with the flow control device in the first extended position.

40. The method of claim 37 wherein flying the aircraft with the flow control device in the second extended position includes flying the aircraft during a landing phase of flight with the flow control device in the second extended position.