Abstract: The present disclosure is directed to a combustion section for a gas turbine engine including a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. An inner liner and an outer liner are each extended at least partially along a lengthwise direction and at an acute angle. A dome assembly is extended between the inner liner and the outer liner, and the inner liner, and the outer liner together define a combustion chamber therebetween. A bulkhead assembly defining a plurality of walls is coupled to the inner liner and generally surrounding the outer liner and dome assembly. The outer casing surrounds the combustor assembly. The inner casing, the outer casing, and the combustor assembly together define a primary flowpath. An oxidizer flows through the primary flowpath in serial flow through the plenum and the fuel injector assembly into the combustion chamber.

Abstract: The present disclosure is directed to a combustion section for a gas turbine engine. The combustion section includes a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. The combustor assembly includes an inner liner and an outer liner each extended at least partially along a lengthwise direction and at an acute angle relative to the longitudinal centerline. The combustor assembly further includes a dome assembly extended between the inner liner and the outer liner. The dome assembly, the inner liner, and the outer liner together define a combustion chamber therebetween. The combustor assembly still further includes a bulkhead assembly defining a plurality of walls coupled to the inner liner and generally surrounding the outer liner and dome assembly. At least a portion of the bulkhead assembly is extended at least partially along a forward direction and defines a plenum between the bulkhead assembly and the dome assembly.