Piezoelectric de-icing of an air inlet

• US 8,793,970 B2
• Filed: 09/29/2008
• Issued: 08/05/2014
• Est. Priority Date: 10/22/2007
• Status: Active Grant

• Current Assignee: Safran Nacelles
• Original Assignee: Aircelle Ltd (Safran SA)
• Inventors: Le Docte, Thierry
• Primary Examiner(s): Wongwian, Phutthiwat
• Application Number:
  US12/738,960
• Publication Number:
  US 20110011056A1
• Time in Patent Office: 2,136 Days
• Field of Search: 60/390.93, 244/134.D, 244/134.R
• US Class Current: 60/39.093
• CPC Class Codes: B64D 15/163 using electro-impulsive devices
• CPC Class Codes: B64D 2033/0233 comprising de-icing means
• CPC Class Codes: B64D 33/02 of combustion air intakes air intakes for gas-turbine plants or jet-propulsion plants per se F02C7/04; air intakes for combustion engines in general F02M35/00

Abstract

A lip assembly for an air inlet of a turbojet engine nacelle includes an inner surface, an external surface. A portion of the external surface is covered by an ice-repellent coating. In particular, the ice-repellent coating includes a piezoelectric actuator which vibrates the external surface and is combined into a matrix of the ice-repellent coating.

Claims

1. An air-inlet lip assembly of a turbojet engine nacelle comprising

an internal surface,

an external surface and

de-icing means,

wherein the de-icing means comprise an ice-repellent coating covering at least part of the external surface, said ice-repellent coating comprising at least one piezoelectric actuator in a matrix of said ice-repellent coating to cause the external surface to vibrate, the at least one piezoelectric actuator being combined into said matrix of said ice-repellent coating,

wherein a thickness of the ice-repellent coating is between 20 μ

m and 100 μ

m.

2. The air-inlet lip assembly as claimed in claim 1, wherein the at least one piezoelectric actuator comprises an electrical power supplier.

3. The air-inlet lip assembly as claimed in claim 1, wherein the at least one piezoelectric actuator is in contact with the internal surface.

4. The air-inlet lip assembly as claimed in claim 1, wherein the ice-repellent coating is selected from polyurethane paints, fluoro polyurethane paints, resins, or plastics containing TEFLON.

5. The air-inlet lip assembly as claimed in claim 1, wherein at least part of the lip assembly is made of a material containing at least one of a composite, a metal and nanoparticles able to make a surface of the lip assembly ice repellent.

6. A turbojet engine nacelle comprising a lip assembly as claimed in claim 1.

7. The air-inlet lip assembly as claimed in claim 1, wherein the ice-repellent coating comprises resins containing polydimethylsiloxane.