Combustor with a dilution passage

Abstract

A combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and a set of dilution passages. The compressed air passageway being formed between the casing, the inner liner and the outer liner. The combustion chamber being at least partially defined by the inner liner and the outer liner. The set of dilution passages extending through at least one of the inner liner or the outer liner. Each dilution passage of the set of dilution passages extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.

What is claimed is: 
     
         1 . A combustor for a gas turbine engine, the combustor comprising:
 a casing;   an inner liner and an outer liner;   a compressed air passageway formed between the casing, the inner liner and the outer liner;   a combustion chamber at least partially defined by the inner liner and the outer liner, the combustion chamber having a mean centerline extending through the combustion chamber, the mean centerline being equidistant between the inner liner and the outer liner;   a set of dilution passages extending through at least one of the inner liner and the outer liner, each dilution passage of the set of dilution passages extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber; and   a baffle provided within the compressed air passage, the baffle having a range of movement in at least an axial direction, with respect to the mean centerline, between a first position and a second position relative to the inlet of at least one dilution passage of the set of dilution passages to control a degree of occlusion of compressed airflow to the inlet of the at least one dilution passage.   
     
     
         2 . The combustor of  claim 1 , wherein the set of dilution passages include a first dilution passage and a second dilution passage, with the baffle being movable to control the degree of occlusion to both of the first dilution passage and the second dilution passage. 
     
     
         3 . The combustor of  claim 2 , wherein the inlet of the first dilution passage is axially spaced from the inlet of the second dilution passage, with respect to the mean centerline. 
     
     
         4 . The combustor of  claim 3 , wherein:
 a straight line extends between a first center point of the inlet of the first dilution passage and a second center point of the inlet of the second dilution passage; and   the baffle comprises a major body axis when viewed along a plane extending circumferentially about the mean centerline and intersecting the baffle, with the major body axis being parallel to the straight line.   
     
     
         5 . The combustor of  claim 3 , wherein the inlet of the first dilution passage is circumferentially spaced from the inlet of the second dilution passage, with respect to the mean centerline. 
     
     
         6 . The combustor  claim 3 , wherein the inlet of the first dilution passage is circumferentially aligned with the inlet of the second dilution passage, with respect to the mean centerline. 
     
     
         7 . The combustion of  claim 6 , wherein the baffle includes a circumferential baffle angle when viewed along a plane extending circumferentially about the mean centerline and intersecting the baffle, with the circumferential baffle angle being variable during operation of the combustor. 
     
     
         8 . The combustor of  claim 5 , wherein the baffle is oriented such that the inlet of the first dilution passage and the inlet of the second dilution passage can be fully occluded at the same time. 
     
     
         9 . The combustor of  claim 1 , wherein the baffle includes a circumferential baffle angle when viewed along a plane extending circumferentially about the mean centerline and intersecting the baffle, with the circumferential baffle angle having an absolute value of less than 90 degrees. 
     
     
         10 . The combustor of  claim 1 , wherein the baffle includes a circumferential baffle angle when viewed along a plane extending circumferentially about the mean centerline and intersecting the baffle, with the circumferential baffle angle being variable during operation of the combustor. 
     
     
         11 . The combustor of  claim 1 , wherein the range of movement has a degree of freedom in a radial direction, with respect to the mean centerline. 
     
     
         12 . The combustor of  claim 1 , wherein the baffle includes a major body axis oriented at a radial baffle angle with respect to the mean centerline, the radial baffle angle being non-zero. 
     
     
         13 . The combustor of  claim 1 , wherein the baffle is operably coupled to an arm. 
     
     
         14 . The combustor of  claim 13 , wherein the baffle includes a pair of opposing baffles and wherein the pair of opposing baffles extend from opposing circumferential sides of the arm. 
     
     
         15 . The combustor of  claim 14 , wherein the pair of opposing baffles are provided at varying radial heights from the mean centerline. 
     
     
         16 . The combustor of  claim 14 , further comprising:
 a first fuel cup extending through a dome wall at least partially defining the combustion chamber; and   a second fuel cup extending through the dome wall and being circumferentially spaced from the first fuel cup, with respect to the mean centerline;   wherein a first baffle of the pair of opposing baffles extends circumferentially across the first fuel cup and a second baffle of the pair of opposing baffles extends circumferentially across the second fuel cup.   
     
     
         17 . The combustor of  claim 1 , wherein the set of dilution passages includes a plurality of dilution passages provided on both the inner liner and the outer liner, with the dilution passages of the plurality of dilution passages provided on the inner liner and the dilution passages of the plurality of dilution passages provided on the outer liner being occluded by separate baffles. 
     
     
         18 . The combustor of  claim 1 , wherein the combustor is defined by a combustor centerline and the baffle is movable at least one of either axially or radially, with respect to the combustor centerline. 
     
     
         19 . The combustor of  claim 18 , wherein the combustor centerline is non-parallel to the mean centerline at the inlet. 
     
     
         20 . The combustor of  claim 1 , further comprising at least one fuel cup provided on a dome wall at least partially defining the combustion chamber, the at least one fuel cup receiving a flow of hydrogen containing fuel.