An anti-icing system according to the present invention includes: a piccolo tube (11) that includes a flow path through which heated gas flows in the longitudinal direction from a rear end to a front end, and a plurality of ejection holes (16) provided along the longitudinal direction to make the flow path communicate with an outside; and an engine serving as a supply source (18) that supplies the heated gas toward the piccolo tube. The piccolo tube is decreased in an area of the flow path in a stepwise manner or in a continuous manner in the longitudinal direction, and has a continuous side surface provided with the ejection holes.
ANTI-ICING SYSTEM AND AIRCRAFT
ENTEISUNGSSYSTEM UND FLUGZEUG
SYSTÈME ANTIGIVRAGE ET AÉRONEF
2022-09-21
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |