Reduced flow field velocity for a propulsor

Patent metadata

Field	Value
Publication number	US-10040559-B2
Application number	US-201113189545-A
Country	US
Kind code	B2
Filing date	Jul 24, 2011
Priority date	Jul 24, 2011
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A system and methods for reducing flow field velocity into a propeller is disclosed. An aerodynamic structure is enhanced to provide a reduced velocity flow field region, and a propeller is positioned in the reduced velocity flow field region.

First claim

The invention claimed is:

1. A method for reducing flow field velocity into a fan or propeller, the method comprising:
shaping an aircraft wing to include an aerodynamic structure enhancement that is shaped to provide a reduced flow field velocity deviation region below the aerodynamic structure enhancement, wherein the reduced flow field velocity deviation region comprises a region having flow field velocities with a substantially uniform speed that is lower than a freestream velocity; and
positioning the fan or propeller at least partially within the reduced flow field velocity deviation region below the aerodynamic structure enhancement of the aircraft wing such that the fan or propeller is aft of a leading edge of the aircraft wing and forward of a trailing edge of the aircraft wing.

2. The method according to claim 1 , wherein the fan or propeller comprises at least one member selected from the group consisting of: a propeller, a turbofan, a propfan, and an unducted fan.

3. The method according to claim 1 , further comprising changing at least one physical property of an aerodynamic structure coupled to the aircraft wing to control the reduced flow field velocity deviation region.

4. The method according to claim 3 , wherein the step of changing the aerodynamic structure comprises at least one member selected from the group consisting of: changing a shape of the aerodynamic structure, changing a position of a flap, and changing a position of the aerodynamic structure.

5. The method of claim 1 , wherein the aerodynamic structure enhancement is on an undersurface of the aircraft wing.

6. A flow field velocity reduction system comprising:
an aircraft wing having an aerodynamic structure enhancement that is shaped to provide a reduced flow field velocity deviation region below the aerodynamic structure enhancement, wherein the reduced flow field velocity deviation region comprises a region having flow field velocities with a substantially uniform speed that is lower than a freestream velocity; and
a fan or propeller configured to operate in the reduced flow field velocity deviation region below the aerodynamic structure enhancement of the aircraft wing such that the fan or propeller is aft of a leading edge of the aircraft wing and forward of a trailing edge of the aircraft wing.

7. The flow field velocity reduction system according to claim 6 , wherein the fan or propeller comprises at least one member selected from the group consisting of: a propeller, a turbofan, a propfan, and an unducted fan.

8. The flow field velocity reduction system according to claim 6 , further comprising an aerodynamic structure coupled to the aircraft wing.

9. The flow field velocity reduction system according to claim 8 , wherein the aerodynamic structure is operable to change a first physical property to control the reduced flow field velocity deviation region.

10. The flow field velocity reduction system according to claim 9 , wherein the first physical property comprises at least one member selected from the group consisting of: a shape of the aerodynamic structure, a position of a flap, and a position of the aerodynamic structure.

11. The flow field velocity reduction system according to claim 6 , further comprising:
a strut coupled to a body of the aircraft configured to increase the size of the reduced flow field velocity deviation region or reduce the flow field velocities in the reduced flow field velocity deviation region.

12. The flow field velocity reduction system according to claim 11 , wherein the strut is configured to generate a negative lift.

13. The flow field velocity reduction system of claim 6 , wherein the aerodynamic structure enhancement is on an undersurface of the aircraft wing.

14. A method for providing a flow field velocity reduction system comprising:
providing an aircraft wing having an aerodynamic stucture enhancement that is shaped to provide a reduced flow field velocity deviation region below the aerodynamic structure enhancement of the aircraft wing, and wherein the reduced flow field velocity deviation region comprises a region having flow field velocities with a substantially uniform speed that is lower than a freestream velocity; and
providing a fan or propeller configured to operate in the reduced flow field velocity deviation region below the aerodynamic structure enhancement of the aircraft wing such that the fan or propeller is aft of a leading edge of the aircraft wing and foward of a trailing edge of the aircraft wing.

15. The flow field velocity reduction system according to claim 11 , wherein the strut is coupled to the fan or propeller and configured to reduce swirl in a wake of the fan or propeller.

16. The method of claim 14 , wherein the aerodynamic structure enhancement is on an undersurface of the aircraft wing.

Assignees

• Hoisington Zachary C
• Boeing Co

Inventors

• Hoisington Zachary C

Classifications

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title

• B64D27/12 Primary

  within, or attached to, wings · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• Y02T50/10

  Drag reduction · CPC title

• Y02T50/40

  Weight reduction · CPC title