Canted combustor for gas turbine engine

The present disclosure is directed to a combustion section (26) for a gas turbine engine. The combustion section (26) includes a combustor assembly (50), an outer casing (110), a fuel injector assembly (70), and an inner casing (120). The combustor assembly (50) includes an inner liner (52) and an outer liner (54) each extended at least partially along a lengthwise direction and at an acute angle relative to the longitudinal centerline. The combustor assembly (50) further includes a dome assembly (57) extended between the inner liner (52) and the outer liner (54). The dome assembly (57), the inner liner (52), and the outer liner (54) together define a combustion chamber (62) therebetween. The combustor assembly (50) still further includes a bulkhead assembly (56) defining a plurality of walls coupled to the inner liner (52) and generally surrounding the outer liner (54) and dome assembly (57). At least a portion of the bulkhead assembly (56) is extended at least partially along a forward direction and defines a plenum (71) between the bulkhead assembly (56) and the dome assembly (57). The outer casing (110) surrounds the combustor assembly (50) and is extended at least partially co-directional to the combustor assembly (50). The fuel injector assembly (70) is extended through the outer casing (110), the bulkhead assembly (56), and the dome assembly (57). The inner casing (120), the outer casing (110), and the combustor assembly (50) together define a primary flowpath (105) in direct fluid communication with the combustion chamber (62). The primary flowpath (105) is extended at least along a forward direction and an aft direction defined by inner casing (120), the outer casing (110), and the combustor assembly (50). An oxidizer flows through the primary flowpath (105) in serial flow through the plenum (71) and the fuel injector assembly (70) into the combustion chamber (62).