Small arrayed swirler system for reduced emissions and noise

Abstract

A combustor assembly employs an ejector assembly having an array of swirlers to influence the flow field, reduce unburned fuel emissions, enhance flame stabilization and reduce noise within a combustion chamber. The swirlers are located downstream of a premixing section and are designed to correct bias of fuel-air mixture residence times in the combustion chamber. The ejector assembly may be tuned to any particular configuration by varying the swirl number in order to produce recirculation zones that ensure out of phase nature of the heat release within the combustion chamber.

What is claimed is: 
     
         1 . A combustion apparatus comprising:
 a combustor liner;   an injector assembly including a primary combustion system and a secondary combustion system; and   a combustion chamber having an axis extending therethrough.   
     
     
         2 . The combustion apparatus according to  claim 1 , further comprising a gas turbine engine. 
     
     
         3 . The combustion apparatus according to  claim 1 , wherein the primary combustion system includes a mixing chamber, and a nozzle, the mixing chamber has ports for receiving air and fuel, the mixing chamber further has an exit located adjacent to the nozzle. 
     
     
         4 . The combustion apparatus according to  claim 1 , wherein the primary combustion system includes an injector ring, the injector ring is spaced apart from the combustor liner. 
     
     
         5 . The combustion apparatus according to  claim 1 , wherein the primary combustion system includes an injector member, the injector member has an inside diameter, an outside diameter, a body, a front face and a rear face, the front face has a plurality of passage openings, the passage openings extend through the body. 
     
     
         6 . The combustion apparatus according to  claim 5 , further comprising a swirler located within at least one passage opening. 
     
     
         7 . The combustion apparatus according to  claim 5 , further comprising a plurality of swirlers located around a circumference of the body of the injector member. 
     
     
         8 . The combustion apparatus according to  claim 5 , wherein the front face is not normal to the axis that extends through the combustor. 
     
     
         9 . The combustion apparatus according to  claim 5 , further comprising a swirler located at one portion of the injector member, and at least one slot located at another portion of the injector member. 
     
     
         10 . The combustion apparatus according to  claim 5 , further comprising an array of swirlers that are spaced apart from one another around at least a portion of the injector member. 
     
     
         11 . The combustion apparatus according to  claim 5 , wherein the injector member is ring shaped and has an array of spaced apart swirlers that are located downstream from a mixing channel. 
     
     
         12 . The combustion apparatus according to  claim 1 , wherein the secondary combustion system includes a mixing channel, a swirler, and a passageway in communication with the mixing channel. 
     
     
         13 . The combustion apparatus according to  claim 1 , wherein the secondary combustion system has a flow path that delivers combustible material to a secondary combustion zone, and the primary combustion system has a flow path that delivers combustible material to a primary combustion zone. 
     
     
         14 . A combustion member comprising:
 a combustor liner;   an injector assembly, the injector assembly includes a body having a plurality of spaced apart apertures circumferentially located around the body, a swirler is located within at least one aperture;   a primary combustion system, the primary combustion system includes a mixing space, the mixing space includes openings for receiving fuel and air; and   a secondary combustion system, the secondary combustion system includes a mixing space that has openings for receiving fuel and air.   
     
     
         15 . The combustion apparatus according to  claim 14 , wherein the injector assembly further includes an annular channel that is spaced upstream of the swirler. 
     
     
         16 . The combustion apparatus according to  claim 14 , further including a swirler located within each aperture that is located around the ring. 
     
     
         17 . The combustion apparatus according to  claim 14 , wherein the spaced apart apertures include a combination of slots and circular shaped openings, the swirler is located within the circular shaped opening, and the slot performs the function as a jet. 
     
     
         18 . The combustion apparatus according to  claim 14 , wherein the spaced apart further includes a swirler for introducing fuel particles or fuel-air mixtures to a secondary combustion zone that is located within a combustor. 
     
     
         19 . The combustion apparatus according to  claim 14 , further comprising a combustor shell. 
     
     
         20 . A combustion member comprising:
 a combustor liner, the liner has ports for facilitating the entry of air;   an injector assembly, the injector assembly includes an annular shaped ring having a plurality of spaced apart apertures circumferentially located around the ring, a swirler is located within each aperture;   a primary combustion system, the primary combustion system includes a mixing space, the mixing space includes openings for receiving fuel and air;   a primary combustion zone located downstream of the swirler;   a secondary combustion system, the secondary combustion system includes a second swirler and a mixing space that has openings for receiving fuel and air; and   a secondary combustion zone located downstream of the second swirler.