METHOD AND APPARATUS FOR AIRCRAFT ANTI-ICING

• US 20100163677A1
• Filed: 12/31/2008
• Published: 07/01/2010
• Est. Priority Date: 12/31/2008
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Karvountzi, Georgia C., Hummel, Daniel S., Rocklin, Mark
• Granted Patent: US 8,061,657 B2
• Time in Patent Office: Days
• US Class Current: 244/134.B
• CPC Class Codes: B64D 15/04 Hot gas application
• CPC Class Codes: B64D 2033/0233 comprising de-icing means
• CPC Class Codes: B64D 2033/0286 for turbofan engines

Abstract

An aircraft anti-icing system includes a source of high temperature gas, a housing, at least one conduit to carry the high temperature gas from the source to the housing, the at least one conduit coupled to the housing and the source, at least one nozzle coupled to the at least one conduit, at least one nozzle configured to impart a rotational motion to the high temperature gas before exhausting the high temperature gas into the housing, and a port for exhausting air from the housing.

Claims

1. An aircraft anti-icing system comprising:

a source of high temperature gas;

a housing;

at least one conduit configured to carry the high temperature gas from the source to the at least one conduit coupled to the housing and the source;

at least one nozzle coupled to said at least one conduit, said at least one nozzle configured to impart a rotational motion to the high temperature gas before exhausting the high temperature gas into the housing; and

a port for exhausting air from the housing.

2. A system in accordance with claim 1 wherein said at last one nozzle comprises a longitudinal axis and a plurality of tubes wrapped around the longitudinal axis of the at least one nozzle to form a helix.

3. A system in accordance with claim 1 wherein the source of high temperature gas is one of an environmental bleed air manifold and a compressor discharge bleed air manifold.

4. A system in accordance with claim 1 wherein the at least one nozzle comprises a plurality of internal vanes.

5. A system in accordance with claim 1 wherein the housing comprises one of a nose cowl and a wing.

6. A system in accordance with claim 1 wherein the high temperature gas mixes with air from the housing after the high temperature gas exits the at least one nozzle.

7. A system in accordance with claim 1 wherein the at least one nozzle is configured to increase a speed of the high temperature gas exiting the at least one nozzle.

8. A method of anti-icing a jet airplane housing, said method comprising:

directing heated gasses from an engine to the housing;

imparting both a rotational and translational movement to the heated gasses;

channeling the heated gasses into the housing; and

exhausting the heated gasses from the housing.

9. A method in accordance with claim 8 wherein directing heated gasses from the engine to the housing comprises thermally connecting a conduit to a hot high pressure region of the engine.

10. A method in accordance with claim 8 wherein exhausting the heated gasses into the housing comprises accelerating the heated gasses through a nozzle outlet.

11. A method in accordance with claim 8 wherein imparting both a rotational and a translational movement to the heated gasses comprises directing the heated gasses through a plurality of flow tubes wrapped about each other in a helical configuration.

12. A method in accordance with claim 8 wherein exhausting the heated gasses from the housing comprises locating an exhaust port in a wall of the housing.

13. A method in accordance with claim 12 wherein directing heated gasses from an engine to the housing comprises directing heated gasses from an engine to at least one of an engine nose cowl and a wing.

14. A jet aircraft anti-icing system comprising:

a source of high temperature gas;

a housing;

at least one conduit to carry the high temperature gas from the source to the housing, the at least one conduit coupled to the housing and the source of high temperature gas;

at least one nozzle coupled to said at least one conduit, said at least one nozzle configured to impart a rotational motion to the high temperature gas before exhausting the high temperature gas into the housing; and

a port for exhausting air from the housing

15. A jet aircraft anti-icing system in accordance with claim 14 wherein the at least one nozzle comprises a longitudinal axis and said at least one nozzle further comprises a plurality of tubes wrapped around the longitudinal axis of the at least one nozzle to form a helix.

16. A jet aircraft anti-icing system in accordance with claim 14 wherein the source of high temperature gas is one of an environmental bleed air manifold and a compressor discharge bleed air manifold.

17. A jet aircraft anti-icing system in accordance with claim 14 wherein the at least one nozzle comprises a plurality of internal vanes.

18. A jet aircraft anti-icing system in accordance with claim 14 wherein the at least one nozzle is bent about a central axis of the at least one conduit.

19. A jet aircraft anti-icing system in accordance with claim 14 wherein the high temperature gas mixes with air from the housing after the high temperature gas exits the at least one nozzle.

20. A jet aircraft anti-icing system in accordance with claim 14 wherein the housing comprises one of an engine cowl and a wing.