US 12,109,445 B2
Fire extinguishing system and method
John A. Weidler, Lynnwood, WA (US); George A. McEachen, Mukilteo, WA (US); Robert S. Wright, Seattle, WA (US); Daniel W. Baisley, Lynnwood, WA (US); Sarah M. Wickham, Renton, WA (US); and Mark D. Byers, Long Beach, CA (US)
Assigned to The Boeing Company, Arlington, VA (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Jun. 14, 2022, as Appl. No. 17/806,910.
Prior Publication US 2023/0398388 A1, Dec. 14, 2023
Int. Cl. A62C 31/00 (2006.01); A62C 3/08 (2006.01); A62C 35/02 (2006.01); A62C 35/68 (2006.01); B64D 45/00 (2006.01)
CPC A62C 31/005 (2013.01) [A62C 3/08 (2013.01); A62C 35/023 (2013.01); A62C 35/68 (2013.01); B64D 45/00 (2013.01); B64D 2045/009 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft, comprising:
a turbofan engine having:
a fan duct outer wall surrounding rotatable fan blades and configured to receive an air flow;
a fan duct inner wall surrounding an engine core located downstream of the fan blades, the fan duct inner wall and the engine core defining an annular gap configured to receive a core flow as a portion of the air flow;
a storage vessel configured to contain a fire extinguishing agent in a liquid form; and
a fluidic oscillator configured to receive the fire extinguishing agent from the storage vessel, and discharge a continuous jet of the fire extinguishing agent into the core flow passing through the annular gap while oscillating the jet back and forth through a sweep angle.