CPC B05B 1/3405 (2013.01) [A62C 3/08 (2013.01); B05B 1/26 (2013.01)] | 20 Claims |
1. A fire suppression system in an aircraft that includes a plurality of adjacent regions, wherein in each region of the plurality of regions, the system comprises:
a plurality of nozzles disposed within the region, including:
a first nozzle within the region, the first nozzle being configured to perform discharge of a fire suppression agent in a first direction within the region; and
a second nozzle within the region, the second nozzle being configured to perform discharge of the fire suppression agent in a second direction within the region,
wherein:
the discharge in the first direction by the first nozzle and the discharge in the second direction by the second nozzle generate and maintain a vortex of the fire suppression agent that occupies the region with rotational flow; and
within the region, the discharge from each nozzle of the plurality of nozzles is between a normal line to the center of the vortex in the region and a perpendicular line that is perpendicular to the normal line,
wherein the vortices in adjacent ones of the regions are generated to rotate in opposite directions.
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