Nacelles for aircraft engines with de-icing systems using a two-phase fluid
Nacelles are provided having a tubular casing, open at its opposite axial ends, with an inner wall and an outer wall which are connected to each other at the front end along a leading edge and at the rear end along a trailing edge and which enclose, together with the leading edge and the trailing edge, a cavity. To prevent the formation of ice at least in the zone of the leading edge of the nacelle, a separating member made of porous material is arranged inside the cavity to divide the cavity into an inner cavity, between the inner wall and the porous separating member, and an outer cavity, between the outer wall and the porous separating member, and to put the inner cavity in fluid communication with the outer cavity only in a front zone of the cavity in contact with the leading edge, and a two-phase fluid is contained in the cavity.
1. An engine nacelle for an aircraft engine, comprising a tubular casing open at its opposite front and rear ends, with an inner wall and an outer wall which are connected to each other at the front end along a leading edge and at the rear end along a trailing edge and which enclose, along with the leading edge and the trailing edge, a cavity where a two-phase fluid is contained,
wherein the nacelle is also provided with a de-icing system arranged to heat the walls of the nacelle at least in the zone of the leading edge to avoid the formation of ice, and
wherein said de-icing system comprises a separating member of porous material arranged inside the cavity so as to divide the cavity into an inner cavity, between the inner wall and the separating member, and an outer cavity, between the outer wall and the separating member, and so as to put the inner cavity in open communication with the outer cavity only in a front zone of the cavity in contact with the leading edge, and
wherein the separating member is configured to allow the fluid to pass through the porous material between the inner and outer cavities only in a liquid phase.
2. The engine nacelle of claim 1 , wherein the inner cavity and the outer cavity, as well as the separating member, extend continuously in a circumferential direction.
3. The engine nacelle of claim 1 , further comprising a plurality of separating elements arranged between the inner wall and the outer wall so as to divide the inner cavity and the outer cavity into a corresponding plurality of sectors not directly communicating with each other and so as to divide the separating member into a corresponding plurality of separating member sectors.