Aircraft anti-icing system

Patent metadata

Field	Value
Publication number	US-10655539-B2
Application number	US-201715785003-A
Country	US
Kind code	B2
Filing date	Oct 16, 2017
Priority date	Oct 16, 2017
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

Various embodiments of the present disclosure provide an aircraft anti-icing system that includes an aircraft engine inlet component, a pressurized air source, and a heat source operable to: (1) heat the leading edge of the aircraft engine inlet component via the heat source to prevent ice formation on the outer surface of the leading edge; and (2) direct pressurized air from the pressurized air source so that it forces water off of the outer surface of the inlet components (and into the external air flow) as the water travels downstream from the leading edge outer surface downstream toward the trailing edge, which prevents runback ice formation.

First claim

The invention claimed is:

1. A method for melting ice or preventing ice formation on a leading edge of an aircraft engine inlet component, the method comprising:
heating the leading edge of the aircraft engine inlet component so that aerodynamic forces effect a flow of water along an exterior surface of the leading edge to an area downstream of an apex of the leading edge; and
directing air from a plenum within an interior of the aircraft engine inlet component to the area downstream of the apex to force the water away from the exterior surface of the leading edge.

2. The method of claim 1 , further comprising heating the air before directing the air from the plenum to the area downstream of the apex.

3. The method of claim 2 , wherein heating the leading edge of the aircraft engine inlet component comprises directing the air to impinge upon an interior surface of the leading edge after heating the air.

4. The method of claim 3 , wherein the air comprises engine bleed air heated by an aircraft engine, further comprising directing the engine bleed air from the engine to the plenum.

5. The method of claim 2 , further comprising directing the air from a pressurized air source to the plenum.

6. The method of claim 1 , further comprising heating the leading edge via a heating device in thermal communication with the leading edge.

7. The method of claim 6 , further comprising directing the air from a pressurized air source to the plenum.

8. The method of claim 1 , wherein directing the air from the plenum to the area downstream of the apex comprises directing the air through a conduit that defines a fluid flowpath between the plenum and the atmosphere.

9. The method of claim 8 , wherein the conduit comprises an axially forward surface that forms an acute angle with the exterior surface of the leading edge where the conduit intersects the exterior surface of the leading edge.

10. The method of 8 , wherein the conduit is defined between the leading edge and a side wall.

11. The method of claim 1 , wherein directing the air from the plenum to the area downstream of the apex comprises directing the air through multiple conduits that each define a fluid flowpath between the plenum and the atmosphere.

12. The method of claim 11 , wherein the conduits each terminate in an exit aperture through which the air flows to exit the conduit, wherein the exit apertures collectively form an array in the leading edge.

13. A method for melting ice or preventing ice formation on a leading edge of an aircraft engine inlet component, the method comprising:
heating the leading edge, which comprises a leading edge outer surface and a leading edge inner surface, so that aerodynamic forces effect a flow of water along the leading edge outer surface to an exit aperture of a conduit, the exit aperture positioned downstream of an apex of the leading edge;
directing pressurized air into a plenum within the leading edge; and
directing the pressurized air from the plenum through the conduit and out of the exit aperture to force the water away from the exterior surface of the leading edge.

14. The method of claim 13 , further comprising heating the pressurized air before directing the pressurized air from the plenum through the conduit and out of the exit aperture.

15. The method of claim 14 , wherein heating the leading edge of the aircraft engine inlet component comprises directing the pressurized air to impinge upon the interior surface of the leading edge after heating the pressurized air.

16. The method of claim 15 , wherein the pressurized air comprises engine bleed air heated by an aircraft engine, further comprising directing the engine bleed air from the engine to the plenum.

17. The method of claim 13 , further comprising heating the leading edge via a heating device in thermal communication with the interior surface of the leading edge.

18. The method of claim 13 , wherein the conduit comprises an axially forward surface that forms an acute angle with the outer surface of the leading edge where the conduit intersects the exterior surface of the leading edge.

19. The method of 18 , wherein the conduit is defined between the leading edge and a side wall.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce North America Tech Inc

Inventors

• Sutterfield David Levi
• Bies Christopher J
• O'Leary Mark

Classifications

• B64D2033/0233

  comprising de-icing means · CPC title

• B64D15/04

  Hot gas application · CPC title

• F05D2260/602

  Drainage · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• B64D15/12

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title