Fuel Nozzle With Multiple Flow Divider Air Inlet

Abstract

The present invention discloses a novel apparatus and way for directing a supply of compressed air into a fuel nozzle assembly for mixing with a fuel source. The apparatus comprises a fuel nozzle assembly having one or more coaxial flow dividers and radially-extending swirler vanes for directing a supply of fuel to a mixing tube. Compressed air is directed to flow in a primarily axial direction by passing through one or more coaxial flow dividers spaced axially and radially about the air inlet region of the fuel nozzle assembly so as to form a non-uniform radial distribution of compressed air to the inlet region of the fuel nozzle assembly.

1 . A fuel nozzle assembly comprising:
 a first tube extending along a center axis and having a first passageway therein;   a second tube coaxial to and radially outward of the first tube and forming a second passageway between the first tube and the second tube;   a third tube coaxial to and radially outward of the second tube and forming a third passageway between the second tube and a portion of the third tube and a portion of the first tube and the third tube;   a premix tube coaxial to and radially outward of the third tube, the premix tube having an inlet end and an opposing outlet end, the premix tube having a plurality of swirler vanes positioned between the third tube and premix tube, the plurality of swirler vanes configured to inject fuel and induce a swirl into a passing flow of fuel and air; and,   one or more coaxial flow dividers, each of the coaxial flow dividers having a cylindrical portion and an inlet region portion, where the inlet region portion is turned radially outward from the center axis;   wherein the one or more coaxial flow dividers split and direct a passing airflow into the premix tube.   
     
     
         2 . The fuel nozzle assembly of  claim 1 , wherein the first tube contains a cartridge for supplying purge through a first passageway. 
     
     
         3 . The fuel nozzle assembly of  claim 2 , wherein the first passageway contains either liquid, gas, air, or a mixture thereof. 
     
     
         4 . The fuel nozzle assembly of  claim 3 , wherein the second passageway contains air, fuel, or a mixture thereof. 
     
     
         5 . The fuel nozzle assembly of  claim 4 , wherein the third passageway is divided into a first portion and a second portion, the first portion extending from proximate a base of the fuel nozzle assembly to proximate the plurality of swirler vanes, while the second portion extends from proximate the plurality of swirler vanes to proximate a tip region of the fuel nozzle assembly, where the first portion is not in fluid communication with the second portion. 
     
     
         6 . The fuel nozzle assembly of  claim 5 , wherein the first portion of the third passageway contains gas and the second portion of the third passageway contains air, gas, or a mixture thereof. 
     
     
         7 . The fuel nozzle assembly of  claim 1 , wherein the inlet end of the premix tube tapers radially outward from the center axis. 
     
     
         8 . The fuel nozzle assembly of  claim 1 , further comprising a plurality of struts extending between and secured to the one or more coaxial flow dividers and the premix tube. 
     
     
         9 . The fuel nozzle assembly of  claim 8 , wherein the plurality of struts extend through a portion of the coaxial flow dividers and a portion of the premix tube. 
     
     
         10 . The fuel nozzle assembly of  claim 8 , wherein the plurality of struts extend across the inlet region of each of the coaxial flow dividers. 
     
     
         11 . An air conditioning flow device for use in a fuel nozzle assembly comprising:
 a premix tube having an inlet end turned radially outward from a center axis of the fuel nozzle assembly; and,   one or more coaxial flow dividers positioned at an air inlet region of the fuel nozzle assembly, each coaxial flow divider having a cylindrical portion extending an axial length and an air inlet portion turned radially outward, the one or more coaxial flow dividers spaced axially and radially so as to form a plurality of annular air inlet areas therebetween, so as to form an unequal radial air flow distribution between the coaxial flow dividers.   
     
     
         12 . The air conditioning flow device of  claim 11 , wherein the plurality of coaxial flow dividers comprise a first and second flow divider. 
     
     
         13 . The air conditioning flow device of  claim 12 , wherein a first air inlet area is formed between a third tube of the fuel nozzle assembly and the first flow divider, a second air inlet flow area is formed between the first and second flow dividers, and a third air inlet area is formed between the second flow divider and the inlet end of the premix tube. 
     
     
         14 . The air conditioning flow device of  claim 13 , wherein the first air inlet area has a different radial air flow distribution than the second air inlet area. 
     
     
         15 . The air conditioning flow device of  claim 14 , wherein the first air inlet area has a similar radial air flow distribution to the third air inlet area. 
     
     
         16 . The air conditioning flow device of  claim 15 , wherein the first air inlet area and third air inlet area each have a radial air flow distribution that is greater than the second air inlet area. 
     
     
         17 . The air conditioning flow device of  claim 13  further comprising a plurality of struts extending between and secured to the one or more coaxial flow dividers and the premix tube. 
     
     
         18 . A method of conditioning an incoming air stream entering a fuel nozzle assembly comprising:
 providing the fuel nozzle assembly having one or more coaxial flow dividers positioned at an air inlet region of the fuel nozzle assembly and spaced axially and radially at the air inlet region;   providing a flow of compressed air to the air inlet region of the fuel nozzle assembly; and,   directing the compressed air through each of a plurality of areas formed by the one or more coaxial flow dividers and in a direction coaxial to a center axis of the fuel nozzle assembly;   wherein the plurality of areas provide a non-uniform radial distribution of compressed air to the air inlet region of the fuel nozzle assembly.   
     
     
         19 . The method of  claim 18 , wherein the coaxial flow dividers further comprise a plurality of radially extending support pins positioned radially between adjacent coaxial flow dividers. 
     
     
         20 . The method of  claim 18 , wherein the compressed air is oriented in primarily an axial direction upon exiting the coaxial flow dividers and entering the premix tube of the fuel nozzle assembly.