Translating turning vanes for a nacelle inlet

Patent metadata

Field	Value
Publication number	US-10436112-B2
Application number	US-201715633579-A
Country	US
Kind code	B2
Filing date	Jun 26, 2017
Priority date	Jun 26, 2017
Publication date	Oct 8, 2019
Grant date	Oct 8, 2019

Abstract

A flow control system on an aircraft engine nacelle incorporates a plurality of translating turning vanes each having a body. An equal plurality of actuators is coupled to a trailing edge of the body of an associated one of the translating turning vanes. The actuator translates the body from a retracted position to an extended position.

First claim

What is claimed is:

1. A flow control system on an aircraft engine nacelle, the system comprising:
a cascade of translating turning vanes configured to extend from a leading edge of the nacelle; and
at least one actuator coupled to translate the cascade of translating turning vanes from a retracted position to an extended position.

2. The flow control system as defined in claim 1 wherein the cascade of translating turning vanes are engaged by a plurality of longitudinal ribs forming translating turning vane segments.

3. The flow control system as defined in claim 1 wherein the cascade of translating turning vanes comprises between 2 and 10 vanes.

4. The flow control system as defined in claim 1 wherein the cascade of translating turning vanes includes a nose vane having an outer contour matching a contour of the leading edge of the nacelle.

5. The flow control system as defined in claim 1 wherein the cascade of translating turning vanes is translated through a slotted opening in the leading edge of the nacelle, the slotted opening having an outer edge located at or radially inward from a cruise condition stagnation point relative to a nacelle inlet centerline.

6. The flow control system as defined in claim 1 wherein the cascade of translating turning vanes includes a closing vane having an outer contour matching a contour of the leading edge of the nacelle, said closing vane being aligned with the outer contour when in the extended position.

7. The flow control system as defined in claim 1 wherein a length of the cascade of translating turning vanes in the extended position comprises between about 2.5% to 20% of a nacelle length.

8. The flow control system as defined in claim 2 wherein each translating turning vane segment of the cascade of translating turning vanes is separately translatable.

9. The flow control system as defined in claim 8 wherein the at least one actuator comprises a plurality of actuators engaged to translate associated translating turning vane segments.

10. The flow control system as defined in claim 9 wherein selectable groups of the translating turning vane segments are simultaneously extendible.

11. The flow control system as defined in claim 10 wherein at least one of the selectable groups is located in a lower quadrant of a circumference of a nacelle inlet, wherein the at least one of the selectable groups is adapted to accommodate a high angle of attack of the nacelle inlet.

12. The flow control system as defined in claim 10 wherein at least two of the selectable groups are located in outboard quadrants of a circumference of a nacelle inlet, wherein the at least two of the selectable groups are adapted to accommodate outboard crosswinds at the nacelle inlet.

13. The flow control system as defined in claim 10 wherein at least one of the selectable groups is located in an inboard quadrant of a circumference of a nacelle inlet, wherein the at least one of the selectable groups is adapted to accommodate inboard crosswinds at the nacelle inlet.

14. A method for inlet flow control on an engine nacelle comprising:
extending a cascade of translating turning vanes on the engine nacelle by translating the cascade through a slot in a leading edge of a nacelle inlet in at least one lower quadrant of a nacelle inlet circumference accommodating a high angle of attack of the engine nacelle.

15. The method of claim 14 further comprising extending a plurality of translating turning vane segments in at least one outboard quadrant of the nacelle inlet circumference accommodating a predetermined outboard wind component.

16. The method of claim 14 further comprising extending a plurality of translating turning vane segments in at least one inboard quadrant of the nacelle inlet circumference accommodating a predetermined inboard wind component.

17. The method of claim 14 further comprising extending a plurality of translating turning vane segments in a lower inboard quadrant of the nacelle inlet circumference accommodating a predetermined inboard wind component with a plurality of translating turning vane segments in an upper inboard quadrant remaining retracted.

18. The method of claim 14 further comprising retracting all translating turning vanes upon exceeding a predetermined speed or operation of the engine nacelle at a lower angle of attack.

19. An aircraft engine nacelle comprising:
a leading edge of a nacelle defining an inlet opening for air flow into an engine housed in the nacelle; and
a flow control system located on the leading edge, the system comprising:
a cascade of translating turning vanes arranged about a circumference of the leading edge, the cascade of translating turning vanes being movable between a stowed position and an extended position in which the cascade of translating turning vanes extend forward from the leading edge of the nacelle; and
at least one actuator coupled to translate the cascade of translating turning vanes between the stowed position and the extended position.

20. The aircraft engine nacelle of claim 19 , wherein the cascade of translating turning vanes is housed in a recess formed in the nacelle when the cascade of translating turning vanes is moved to the stowed position.

Assignees

• Boeing Co

Inventors

• Hoisington Zachary C
• Palacios Francisco D
• Hoffman' Drew C
• Dorsey Andrew M
• Sequeira Kevin J
• Frazier Romar C
• Chapel Steven E

Classifications

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F02K3/068

  being characterised by a short axial length relative to the diameter · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title