A combustor for a gas turbine engine, comprising: an outer liner having a first end and a second end opposite the first end, the first end interconnected to the second end by an outer liner wall composed of a plurality of outer wall segments, wherein the outer wall segments are straight; and an inner liner having a first inner end and a second inner end opposite the first inner end, the second inner end coupled to the second end of the outer liner, the first inner end interconnected to the second inner end by an inner liner wall composed of a plurality of inner wall segments, wherein the inner wall segments are straight, wherein each of the outer liner wall and the inner liner wall cooperate to define a combustion chamber , and wherein the plurality of outer wall segments comprises a first wall segment at the first end of the outer liner , the first wall segment extending at an angle of about 90 degrees relative to a build direction of the combustor, wherein the build direction extends in an axial direction A and is perpendicular to a radial direction R, a second wall segment connected to or integrally formed with the first wall segment , the second wall segment extending at an angle of about 45 degrees relative to the build direction of the combustor, a third wall segment connected to or integrally formed with the second wall segment , the third wall segment extending substantially parallel to the build direction of the combustor, a fourth wall segment connected to or integrally formed with the third wall segment , the fourth wall segment extending at an angle of about 45 degrees relative to the build direction of the combustor, and a fifth wall segment connected to or integrally formed with the further wall segment , the fifth wall segment extending substantially parallel to the build direction of the combustor and terminating at the second end of the outer liner. an outer liner having a first end and a second end opposite the first end, the first end interconnected to the second end by an outer liner wall composed of a plurality of outer wall segments, wherein the outer wall segments are straight; and an inner liner having a first inner end and a second inner end opposite the first inner end, the second inner end coupled to the second end of the outer liner, the first inner end interconnected to the second inner end by an inner liner wall composed of a plurality of inner wall segments, wherein the inner wall segments are straight, wherein each of the outer liner wall and the inner liner wall cooperate to define a combustion chamber , and wherein the plurality of outer wall segments comprises a first wall segment at the first end of the outer liner , the first wall segment extending at an angle of about 90 degrees relative to a build direction of the combustor, wherein the build direction extends in an axial direction A and is perpendicular to a radial direction R, a second wall segment connected to or integrally formed with the first wall segment , the second wall segment extending at an angle of about 45 degrees relative to the build direction of the combustor, a third wall segment connected to or integrally formed with the second wall segment , the third wall segment extending substantially parallel to the build direction of the combustor, a fourth wall segment connected to or integrally formed with the third wall segment , the fourth wall segment extending at an angle of about 45 degrees relative to the build direction of the combustor, and a fifth wall segment connected to or integrally formed with the further wall segment , the fifth wall segment extending substantially parallel to the build direction of the combustor and terminating at the second end of the outer liner. <EOS>