Fire extinguishing agent nozzle structure

Abstract

An aircraft engine fire extinguishing system includes a supply housing for containing a fire extinguishing agent. Also included is a line for routing the fire extinguishing agent from the supply housing. Further included is a nozzle structure operatively coupled to the line, the nozzle structure having a non-circular opening for expelling the fire extinguishing agent.

What is claimed is: 
     
         1 . An aircraft engine fire extinguishing system comprising:
 a supply housing for containing a fire extinguishing agent;   a line for routing the fire extinguishing agent from the supply housing; and   a nozzle structure operatively coupled to the line, the nozzle structure having a non-circular opening for expelling the fire extinguishing agent.   
     
     
         2 . The aircraft engine fire extinguishing system of  claim 1 , wherein at least a portion of the fire extinguishing agent is in a non-gaseous state. 
     
     
         3 . The aircraft engine fire extinguishing system of  claim 1 , wherein the nozzle structure is located within an annular space defined by an engine core and a nacelle. 
     
     
         4 . The aircraft engine fire extinguishing system of  claim 1 , wherein the non-circular opening is an arc shaped slot. 
     
     
         5 . The aircraft engine fire extinguishing system of  claim 4 , wherein the arc shaped slot is a semi-circular opening. 
     
     
         6 . The aircraft engine fire extinguishing system of  claim 1 , wherein the non-circular opening is an L-shaped opening. 
     
     
         7 . The aircraft engine fire extinguishing system of  claim 1 , wherein the non-circular opening is a T-shaped opening. 
     
     
         8 . The aircraft engine fire extinguishing system of  claim 1 , wherein the non-circular opening comprises a first linear segment, a second linear segment oriented perpendicularly to the first linear segment, and an arc shaped segment extending from one of the first linear segment and the second linear segment. 
     
     
         9 . The aircraft engine fire extinguishing system of  claim 1 , wherein the non-circular opening comprises a first linear segment and a second linear segment oriented at a non-parallel angle to the first linear segment. 
     
     
         10 . The aircraft engine fire extinguishing system of  claim 1 , wherein the non-circular opening is one of a plurality of apertures formed within the nozzle structure. 
     
     
         11 . The aircraft engine fire extinguishing system of  claim 2 , wherein the non-gaseous fire extinguishing agent is at least one of a dry chemical or aerosol agent. 
     
     
         12 . The aircraft engine fire extinguishing system of  claim 1 , wherein the nozzle structure is located within an auxiliary power unit compartment or bay. 
     
     
         13 . The aircraft engine fire extinguishing system of  claim 1 , wherein energy losses are reduced when the fire extinguishing agent contacts surfaces of the non-circular opening compared to a circular opening. 
     
     
         14 . A method of distributing a fire extinguishing agent in an aircraft engine comprising:
 routing a fire extinguishing agent from a supply housing to a nozzle structure; and   expelling the fire extinguishing agent from the nozzle structure through a non-circular opening of the nozzle structure.   
     
     
         15 . The method of  claim 14 , wherein at least a portion of the fire extinguishing agent is in a non-gaseous state. 
     
     
         16 . The method of  claim 14 , wherein the non-circular opening is one of a plurality of non-circular openings defined by the nozzle structure.