Patent ID: 8757547

Claim:
An air intake of an aircraft nacelle, comprising: an inlet lip connected to a front frame, thereby forming a channel, wherein the channel extends around a circumference of said inlet lip; at least one localized injector located within the channel and configured to provide circulation of hot air in the channel, the injector comprising: a toroidal pipe having a hollow interior; a tube connected to the toroidal pipe interior at one end, passing through or attached to the front frame, and configured to be connected to a hot air supply at an opposite end; and at least one injection opening arranged on the toroidal pipe; wherein the toroidal pipe surrounds/forms a boundary for at least one passage hole; wherein the hot air supply is configured to send heated air through the tube into the interior of the toroidal pipe, throughout the interior of the pipe, out of the at least one injection opening, and into the inlet channel; wherein the heated air exiting the at least one injection opening causes ambient air within the inlet channel to circulate in either a clockwise or counterclockwise direction; wherein the circulating air within the inlet channel passes over an outer circumference of the at least one toroidal pipe and through the at least one passage hole and mixes with the heated air exiting the at least one injection opening.