COMBUSTOR FOR GAS TURBINE ENGINE AND METHOD OF MANUFACTURE

A combustor (200) for a gas turbine engine includes an outer liner (202) having a first end interconnected to an opposite second end by an outer liner wall (214) composed of a plurality of outer segments. The inner liner (204) has a first inner end interconnected to an opposite second inner end by an inner liner wall (304) composed of a plurality of inner segments. The outer liner wall (214) and the inner liner wall define a combustion chamber (206), and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments include a first segment (218), a second segment (220) that extends at a second angle relative to the first segment (218), which is less than a third angle defined between the second segment (220) and a third segment (222) and is substantially the same as a fourth angle defined between the third segment (222) and a fourth segment (224).