FRONT LIP OF A TURBOFAN ENGINE NACELLE COMPRISING HOT-AIR BORES UPSTREAM FROM ACOUSTIC PANELS

摘要

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.

主权项

1. A front lip of a turbojet engine nacelle, delimited at a rear portion by a partition wall, the front lip including a de-icing annular volume including a hot air supply tube for performing a de-icing of its external walls, the front lip further comprising acoustic panels, the front lip further comprising hot air outlet piercings disposed between a front end of the front lip and said acoustic panels, the hot air outlet piercings providing a hot air flow rate, from said annular volume, forming a substantially uniform film covering said acoustic panels with a boundary layer of air in order to heat the acoustic panels.