To provide an anti-icing device for a front edge part in an aircraft, configured to reliably and efficiently prevent icing at the front edge of the aircraft with a simple structure.
An anti-icing device 40 includes an extraction air nozzle 41 where extraction air to be supplied to a main-wing front edge part 22 flows, and a rear wall 32 that is provided on a flow passage of the extraction air and with which the extraction air collides. The extraction air nozzle 41 is provided on the side closer to the main-wing front edge 22 than the rear wall 32. The extraction air nozzle 41 has a blow hole 41a formed opposite the rear wall 32 to blow the extraction air to the rear opposite a tip part 22a of the main-wing front edge part 22. The extraction air blown from the blow hole 41a collides with the rear wall 32 and flows from the rear of the main-wing front edge part 22 toward the tip part 22a along an inner wall surface 31, thereby preventing local overheating of the inner wall surface 31 of the tip part 22a, and heating the main-wing front edge part 22 entirely and more uniformly.
KAMIFUJI YOICHI
SAKATA NOBUYASU
SATO KEIICHI
Horikawa Miyuki
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