Patent ID: 8651925

Claim:
A ventilating air intake arrangement of an aircraft nacelle that houses a turbine engine, comprising: at least one air duct in a structural wail of a front portion of the nacelle, wherein the at least one air duct connects to an air intake orifice; at least one confined zone between the nacelle and an outer casing of the turbine engine, wherein the at least one confined zone is connected to the at least one air duct and the air intake orifice, and the at least one confined zone is configured for outside air to enter upstream of the at least one air duct, through said air intake orifice, into said at least one air duct, and exit downstream of the at least one air duct toward said at least one confined zone; controllable flap configured to modify the flow of air entering the at least one confined zone by varying a cross section of the at least one air duct; and a control unit for controlling said controllable mobile element to vary the cross section of said at least one air duct, wherein said control unit comprises a variable volume reservoir: connected to said controllable flap, and in communication, by way of a conduit, with a pressure intake orifice on a forward facing surface of the nacelle that receives total pressure exerted by the outside air on said aircraft, with the control unit controlling the controllable mobile element to vary the cross section of said at least one air duct as a function of speed and altitude of said aircraft by fluidly transferring the pressure at the pressure intake orifice to the variable volume reservoir, thereby affecting the volume of the variable volume reservoir.