DE-ICING SYSTEM WITH THERMAL MANAGEMENT

• US 20150291284A1
• Filed: 04/14/2014
• Published: 10/15/2015
• Est. Priority Date: 04/14/2014
• Status: Active Grant

• Current Assignee: ROHR Incorporated (Rtx Corporation)
• Original Assignee: ROHR Incorporated (Rtx Corporation)
• Inventors: Victor, Jared, Franks, Chad
• Granted Patent: US 10,144,520 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 15/04 Hot gas application
• CPC Class Codes: B64D 2033/0233 comprising de-icing means

Abstract

An aircraft component assembly has a structural body and a thermal management de-icing system for minimizing or preventing ice build-up on leading edges of the body. The system includes a supply line for flowing heated fluid to the leading edges and a cooling device that interposes the supply line to prevent overheating of the leading edges thus protecting bodies that may be made of composite materials that are more susceptible to heat.

Claims

1. An aircraft component assembly comprising:

a structural body; and

a thermal management system for the prevention of ice build-up on the structural body, the thermal management system having a first line for the flow of heated supply air and located upstream from and communicating with the structural body to heat it and prevent or remove ice build-up, and a cooling device interposed with the first line to reduce supply air temperature.

2. The aircraft component assembly set forth in claim 1, wherein the structural body is made of a composite material.

3. The aircraft component assembly set forth in claim 2, wherein the composite material is epoxy based.

4. The aircraft component assembly set forth in claim 2, wherein the composite material is polyimide based.

5. The aircraft component assembly set forth in claim 1, wherein the heated supply air is compressed air from a compressor section of an engine.

6. The aircraft component assembly set forth in claim 1, wherein the cooling device includes a second line communicating with the first line for the flow of cooling air that mixes with the heated supply air.

7. The aircraft component assembly set forth in claim 1, wherein the cooling device is a heat sink that cools the heated supply air to a temperature safe for the structural body.

8. The aircraft component assembly set forth in claim 7, wherein the heatsink is an elongated portion of the first line in an area where heat will conduct out of the first line to cool the heated supply air temperature.

9. The aircraft component assembly set forth in claim 8 wherein the elongated portion is attached to a metallic plate that is exposed on one side to the ambient air flow.

10. The aircraft component assembly set forth in claim 6 further comprising:

a Venturi tube joining the first and second lines.

11. The aircraft component assembly set forth in claim 2, wherein the composite material is bismaleimide based.

12. The aircraft component assembly set forth in claim 10, wherein the heated supply air is compressed air from a compressor section of an engine.

13. The aircraft component assembly set forth in claim 12, wherein the cooling device includes a control valve in the second line.

14. The aircraft component assembly set forth in claim 13, wherein the first line is interposed by a control valve.