An inertial particle separator (40), having: an inlet duct (42) defining an intake (48); an intermediate duct (44) extending from the inlet duct (42) to an engine inlet (12); a bypass duct (46) in fluid communication with and extending downstream from the inlet duct (42), the bypass duct (46) defining an outlet (56) communicating with the environment (E) of the aircraft engine (10), a splitter (50) defined at an intersection of a wall (46) of the bypass duct (46a) and a wall (44d) of the intermediate duct (44); a splitter vane (52) within the intermediate duct (44) and having a leading edge (52a) located upstream of the splitter (50) relative to a flow (F) circulating through the separator (40), the splitter vane (52) and the wall (44d) of the intermediate duct (44) defining a channel (60) therebetween; and a porous plate (62) extending across the channel (60) and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.
INERTIAL PARTICLE SEPARATOR FOR AIRCRAFT ENGINE
TRÄGHEITSPARTIKELABSCHEIDER FÜR FLUGZEUGTRIEBWERK
SÉPARATEUR DE PARTICULES À INERTIE POUR MOTEUR D'AÉRONEF
2021-03-24
Patent
Electronic Resource
English