3d non-axisymmetric combustor liner

Abstract

A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.

1 . A combustor liner with an input end and an output end, the liner comprising:
 an annular inner wall; and   an annular outer wall; wherein at least one of the inner wall and outer wall is three-dimensionally contoured, and together the inner wall and outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.   
     
     
         2 . The combustor liner of  claim 1 , wherein both the inner wall and outer wall are three-dimensionally contoured to form alternating expanding and constricting regions inside the chamber. 
     
     
         3 . The combustor liner of  claim 1 , wherein the contoured wall is contoured around the circumference and contoured axially through the length of the combustion chamber from input to output. 
     
     
         4 . The combustor liner of  claim 1 , wherein the contoured inner wall and contoured outer wall are contoured around the circumference and contoured axially through the length of the combustion chamber from input to output. 
     
     
         5 . The combustor liner of  claim 1 , wherein the three-dimensional contours promote localized mixing of gasses flowing from the input to the output of the combustion chamber. 
     
     
         6 . The combustor liner of  claim 1 , wherein the inner and outer walls contain dilution holes. 
     
     
         7 . The combustor liner of  claim 1 , wherein the combustion chamber has a variation in volume along the axial length of the combustor from input to output. 
     
     
         8 . The combustor liner of  claim 1 , wherein the distance between the inner wall and the outer wall in a region of constriction is about ⅓ to about ⅗ of the distance from the inner wall to the outer wall in a region of expansion. 
     
     
         9 . A generally cylindrical combustor to receive air and fuel at an input end, mix the air and fuel axially through the length of the combustor and distribute the mixture to a turbine at an output end, the combustor comprising:
 a combustor liner with an annular inner wall and an annular outer wall forming a combustion chamber, with at least one of the walls having three-dimensional contours creating alternating expanding and constricting regions inside the chamber to cause combustion gases to flow in the circumferential and axial directions; and   a plurality of nozzles in an annular shape to distribute the fuel and air into the combustion chamber at the input end of the combustor.   
     
     
         10 . The combustor of  claim 9 , wherein the inner wall and outer wall of the combustor line have three-dimensional contours creating alternating expanding and constricting regions inside the chamber. 
     
     
         11 . The combustor of  claim 10 , wherein the three-dimensional contours are in a wavelike pattern on the inner and outer walls and are located circumferentially around the walls and axially through the length of the liner walls from input to output. 
     
     
         12 . The combustor of  claim 11 , wherein at the input of the combustor, the contours around the circumference of liner inner wall and outer wall form regions of constriction at locations between the nozzles, the contours around the circumference of liner inner wall and outer wall form regions of expansion at nozzles. 
     
     
         13 . The combustor of  claim 9 , wherein the three-dimensional contours are designed to promote localized mixing of the air and fuel in the combustor. 
     
     
         14 . The combustor of  claim 9 , wherein the liner further includes a plurality of dilution holes or jets. 
     
     
         15 . The combustor of  claim 9 , wherein at the output end of the combustor, the mixing has created a generally uniform distribution of temperature and pressure in the mixture. 
     
     
         16 . The combustor of  claim 9 , wherein the distance between liner inner wall and liner outer wall is larger in regions of expansion at the input end of the combustor than in regions of expansion at the output end of the combustor. 
     
     
         17 . The combustor of  claim 9 , wherein the combustion chamber has a variation in volume from the input end than at the output end. 
     
     
         18 . The combustor of  claim 9 , wherein the distance between the inner wall and the outer wall in a region of constriction is about ⅓ to about ⅗ of the distance from the inner wall to the outer wall in a region of expansion. 
     
     
         19 . A method comprising:
 injecting fuel and air into an annular combustion chamber between inner and outer liner walls of the combustion chamber at an input end; and   creating localized mixing of the fuel and air in the combustion chamber with three-dimensional contours on at least one of the inner and outer liner walls around the circumference and axially through the length of the combustion chamber, with the contours forming alternating regions of expansion and constriction within the combustion chamber.   
     
     
         20 . The method of  claim 19 , wherein the step of creating localized mixing of the fuel and air with three dimensional contours further comprises:
 injecting additional air into the combustor through a plurality of dilution holes or jets in the liner.