Ice protection system for a component of an aerodynamic system

Patent metadata

Field	Value
Publication number	US-2020017223-A1
Application number	US-201816176443-A
Country	US
Kind code	A1
Filing date	Oct 31, 2018
Priority date	Jul 11, 2018
Publication date	Jan 16, 2020
Grant date	—

Abstract

Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.

First claim

What is claimed is:

1 . An ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system comprising:
a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.

2 . The component of claim 1 , wherein the heating source is integral with the perforated sheet.

3 . The component of claim 2 , wherein the heating source includes a drain hole extending between the perforated sheet and the suction source.

4 . The component of claim 3 , wherein the ice protection system comprises a honeycomb support structure on an inward side of the perforated sheet.

5 . The component of claim 4 , wherein the ice protection system comprises a water collector on an inwardly facing side of the honeycomb support structure.

6 . The component of claim 5 , wherein the suction source is a pump fluidly connected to the water collector.

7 . The component of claim 6 , wherein the ice protection system includes a rigid shell on an inward facing side of the water collector.

8 . The component of claim 7 , wherein the ice protection system is coupled to a leading edge thereof.

9 . The component of claim 8 , wherein the component is a nacelle or an aircraft control surface on a wing and empennage.

10 . The component of claim 8 , wherein the component is a wing and empennage.

11 . A method of preventing ice formation with an ice protection system on a surface of a component of an aerodynamic system, the surface having a flow facing side and an inwardly facing side that opposes the flow facing side,
the method comprising:
heating the surface with a heating source of the ice protection system, and
providing suction on an inwardly facing side of the heating source with a suction source to draw water melted by heating the surface through the heating source into a water collector.

12 . The method of claim 11 , wherein a flow facing side of the heating source comprises a perforated sheet.

13 . The method of claim 12 , wherein the heating source includes a drain hole extending between the perforated sheet and the suction source.

14 . The method of claim 13 , wherein the ice protection system comprises a honeycomb support structure on an inward side of the perforated sheet.

15 . The method of claim 14 , wherein the ice protection system comprises a water collector on an inwardly facing side of the honeycomb support structure.

16 . The method of claim 15 , wherein the suction source is a pump fluidly connected to the water collector.

17 . The method of claim 16 , wherein the ice protection system comprises a rigid shell on an inward facing side of the water collector.

18 . The method of claim 17 , wherein the ice protection system is coupled to a leading edge of the component.

19 . The method of claim 18 , wherein the component is a nacelle.

20 . The method of claim 18 , wherein the component is a wing.

Assignees

• Goodrich Corp

Inventors

• Selvaraj Sugumaran
• Thangavel Sathish

Classifications

• B64D15/12 Primary

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

• B64D15/02

  by ducted hot gas or liquid · CPC title

• B64D15/00

  De-icing or preventing icing on exterior surfaces of aircraft · CPC title

• F02C7/047

  Heating to prevent icing · CPC title

• B64D15/04

  Hot gas application · CPC title