Leading edge ice-protection system

Patent metadata

Field	Value
Publication number	US-10569888-B2
Application number	US-201715845298-A
Country	US
Kind code	B2
Filing date	Dec 18, 2017
Priority date	Dec 20, 2016
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

An ice-protection system for an aerodynamic structure for an aircraft comprising: an outer skin defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin, an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet, and at least one air heater provided within the chamber in proximity to the inlet, wherein during use, a pressure differential exists between the inlet and the outlet that causes external air to flow through the chamber from the inlet to the outlet, and wherein the heater is configured to heat the air passing through the inlet such that the temperature of the air in the chamber is sufficiently increased so as to prevent ice accretion on the outer skin.

First claim

The invention claimed is:

1. An ice-protection system for an aerodynamic structure for an aircraft comprising:
an outer skin defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin;
an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet; and,
at least one air heater provided within the chamber in proximity to the inlet.

2. The ice-protection system according to claim 1 , configured such that, during use, a pressure differential exists between the inlet and the outlet that causes external air to flow through the chamber from the inlet to the outlet, and wherein the heater element is configured to heat the external air passing through the inlet such that the temperature of the air in the chamber is sufficiently increased to prevent ice accretion on the outer skin.

3. The ice-protection system according to claim 1 , further comprising an internal baffle configured to define a passage between the inlet and the outlet.

4. An ice-protection system according to claim 3 , wherein the internal baffle is configured to define a throttling passage that extends substantially along the leading edge and upper skin.

5. An ice-protection system according to claim 3 , wherein the internal baffle is configured to define a throttling passage for air flowing through the internal baffle.

6. The ice-protection system according to claim 1 , wherein the heater element is housed in a thermally insulated mount configured to prevent excessive heat energy being conducted directly from the heating element to the surrounding structure.

7. The ice-protection system according to claim 1 , further comprising a temperature sensor positioned in proximity to the outlet and a control unit, wherein the control unit and sensor are connected to the heater element and are configured to maintain the temperature of the air passing through the chamber according to a preset temperature.

8. An aerodynamic structure for an aircraft having an ice-protection system, the system comprising:
an outer skin of the aerodynamic structure defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin;
an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet; and,
at least one air heater provided within the chamber in proximity to the inlet.

9. The aerodynamic structure according to claim 8 , comprising a leading edge slat.

10. The aerodynamic structure according to claim 8 , comprising a wing leading edge.

11. The aerodynamic structure according to claim 8 , comprising a wing tip device leading edge.

12. The aerodynamic structure according to claim 8 , comprising a horizontal tail plane leading edge.

13. The aerodynamic structure according to claim 8 , comprising a vertical tail plane leading edge.

14. The aerodynamic structure according to claim 8 , comprising an engine nacelle leading edge.

15. An aircraft comprising an aerodynamic structure and an ice-protection system according to claim 8 .

Assignees

• Airbus Operations Gmbh

Inventors

• Lorenz Florian

Classifications

• B64D15/04 Primary

  Hot gas application · CPC title

• B64C9/24

  by single flap · CPC title

• B64C21/02

  by use of slot, ducts, porous areas or the like · CPC title

• B64C2230/10

  by influencing fluid flow by heating using other means than combustion · CPC title

• Y02T50/10

  Drag reduction · CPC title