Inertial particle separator for aircraft engine
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United States of America Patent
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May 24, 2022
Grant Date -
Mar 18, 2021
app pub date -
Sep 17, 2019
filing date -
Sep 17, 2019
priority date (Note) -
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Abstract
An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.
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