AIRCRAFT ANTI-ICING SYSTEMS HAVING DEFLECTOR VANES

• US 20150198061A1
• Filed: 01/14/2014
• Published: 07/16/2015
• Est. Priority Date: 01/14/2014
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Johnson, Rick A., Pham, Victor D., Gally, Daniel H., Seydel, Joseph James, Natsui, Edward Charles
• Granted Patent: US 9,488,067 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 15/04 Hot gas application
• CPC Class Codes: F01D 25/02 De-icing means for engines having icing phenomena
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Apparatus and methods to lower peak temperatures and improve performance of aircraft anti-icing systems are described herein. One described example apparatus includes a skin on an inlet side of a nacelle of an aircraft defining an annular chamber, a gas delivery system disposed within the annular chamber to provide a first gas to mix with and entrain a second gas in the annular chamber to define a flow through the annular chamber, and a deflector vane disposed within the annular chamber to redirect the flow through the annular chamber. The second gas is at a different temperature from the first gas.

Claims

1. An apparatus comprising:

a skin on an inlet side of a nacelle of an aircraft defining an annular chamber;

a gas delivery system disposed within the annular chamber to provide a first gas to mix with and entrain a second gas in the annular chamber to define a flow through the annular chamber, wherein the second gas is at a different temperature from the first gas; and

a deflector vane disposed within the annular chamber to redirect the flow through the annular chamber.

2. The apparatus as defined in claim 1, further comprising a second deflector vane to further redirect the flow.

3. The apparatus as defined in claim 2, further comprising a bulkhead further defining the annular chamber and coupled to the first and second deflector vanes.

4. The apparatus as defined in claim 3, further comprising a stiffener coupled to the bulkhead to support the first and second deflector vanes.

5. The apparatus as defined in claim 1, wherein the first gas is provided by an engine in the nacelle.

6. The apparatus as defined in claim 1, further comprising a bulkhead further defining the annular chamber and coupled to the nozzle.

7. The apparatus as defined in claim 6, further comprising a c-channel coupled to the bulkhead to support the first and second deflector vanes.

8. The apparatus as defined in claim 1, wherein the deflector vane comprises a t-flange for reinforcement.

9. An apparatus comprising:

a chamber in an outboard structure of an aircraft, the chamber on a fore side of the outboard structure;

a gas delivery system disposed within the chamber having an outlet to provide a gas to the chamber, the gas to define a flow through the chamber; and

a deflector vane disposed within the chamber to redirect the flow through the chamber.

10. The apparatus as defined in claim 9, further comprising a second deflector vane to further redirect the flow.

11. The apparatus as defined in claim 10, further comprising a bulkhead defining the chamber and coupled to the first and second deflector vanes.

12. The apparatus as defined in claim 9, wherein the gas is provided by an engine.

13. The apparatus as defined in claim 12, wherein the engine is in the outboard structure.

14. The apparatus as defined in claim 9, further comprising a bulkhead defining the chamber and coupled to the nozzle.

15. The apparatus as defined in claim 14, further comprising a c-channel coupled to the bulkhead to support the deflector vane.

16. The apparatus as defined in claim 9, wherein the deflector vane comprises a t-flange stiffener for reinforcement.

17. A method comprising:

receiving a gas into an inlet duct of an aircraft, the gas to define a flow through the inlet duct in a first flow path direction; and

redirecting the flow in a second flow path direction within the inlet duct.

18. The method as defined in claim 17, further comprising mixing the flow within the chamber.

19. The method as defined in claim 17, further comprising redirecting the flow in a third flow path direction within the inlet duct.

20. The method as defined in claim 17, further comprising reinforcing a vane to redirect the flow in the second flow path direction.