Aircelle Limited

Safran Nacelles

Laurence Lemains

Guy Bernard Vauchel

David Pereira

Arnaud Delehouze

Marc Versaevel

Marc Gerome

Pierre-François Behaghel

Pascal Mer

A front lip of a turbofan engine nacelle is provided, defined at the rear by a partition wall, the lip comprising an annular de-icing space including a tube for supplying hot air in order to de-ice the outer walls thereof, said lip also including acoustic panels arranged on the wall thereof substantially radially facing the axis of the nacelle. The front lip includes hot-air outlet bores/piercings which are arranged between the front end of the lip and said acoustic panels, which allow a flow of hot air, from said annular space, forming a substantially regular film which covers said acoustic panels with a boundary layer in order to heat said acoustic panels.

Front lip of a turbofan engine nacelle comprising hot-air bores upstream from acoustic panels

A turbojet engine nacelle includes a rear section having an internal structure. The internal structure surrounds a rear part of an engine compartment and delimits, with an ejection jet pipe, an outlet cross section for the ventilation of the engine compartment. The engine nacelle includes a moving element associated with a corresponding controller. The moving element is able to move between a withdrawn position in which the outlet cross section for ventilation is at a maximum and an engaged position in which the moving element partially reduces the outlet cross section for ventilation by comparison with the retracted position. The controller is capable of moving the moving element between the retracted and engaged positions.

Turbojet engine nacelle with variable ventilation outlet cross section

The present invention relates to a method for commanding and controlling at least one resistive heating element () belonging to an aircraft turbojet engine nacelle deicing set, characterized in that it involves the steps aimed at: obtaining, from a central control unit () of the aircraft, parameters representative of the exterior flight conditions; determining a thermal model corresponding to the flight conditions obtained; as a function of the thermal model, delivering the appropriate corresponding electrical power () to the resistive heating element.

Method for controlling an electrical deicing system

The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source () and thus defining an assembly () of resistant mats, characterized in that the assembly of resistant mats includes one or more subassemblies of resistant mats, each subassembly in turn including one or more resistant mats of the assembly, and each subassembly of resistive mats having a different ohmic value.

Electric de-icing device and related monitoring system

The invention relates to a method for making a deicing system on a panel () of a nacelle comprising an outer skin () having at least one hole and an inner skin (), characterized in that it comprises the following steps: A. a grid of resistive elements is positioned on the outer skin () with respect to the hole(s) by a positioning means; B. the grid of resistive elements is applied by an application means to the location determined in step A to form the deicing system; C. a surface coating is applied to the resulting deicing system. The present invention also relates to an air inlet lip and to a nacelle comprising a deicing system produced by such method.

Growing community of inventors

St. Laurent de Brevedent, France

Laurence Lemains