Abstract: A fuel distribution manifold for a gas turbine engine is disclosed herein. The fuel distribution manifold includes a manifold body, a stage divider, and a plurality of manifold outlet ports. The stage divider subdivides an internal volume of the manifold body into a primary stage volume and a secondary stage volume. A majority of the plurality of manifold outlet ports extends from the manifold body between the primary inlet port and the stage divider, each being fluidly connected to the primary stage volume. A remainder of the plurality of manifold outlet ports extends from the manifold body between the secondary inlet port and the stage divider, each being fluidly connected to the secondary stage volume.

Abstract: A fuel distribution manifold for a gas turbine engine is disclosed herein. The fuel distribution manifold includes a manifold body, a stage divider, and a plurality of manifold outlet ports. The stage divider subdivides an internal volume of the manifold body into a primary stage volume and a secondary stage volume. A majority of the plurality of manifold outlet ports extends from the manifold body between the primary inlet port and the stage divider, each being fluidly connected to the primary stage volume. A remainder of the plurality of manifold outlet ports extends from the manifold body between the secondary inlet port and the stage divider, each being fluidly connected to the secondary stage volume.

Abstract: This invention relates to a combustor heat shield assembly for a containment ring for use in a radial inflow turbine engine having a compressed air supply and a combustor. The combustor heat shield assembly includes a turbine nozzle assembly which is adapted for receiving a mixture of compressed air and combustion by-products delivered by the combustor to drive a turbine impeller of the radial inflow turbine engine about an axis of rotation. The turbine nozzle assembly is integrally connected with and in close radial proximity to the containment ring. A heat shield, provided with slots, is coupled to the turbine nozzle assembly and thermally adapted for providing a circumferentially uniform seal between the turbine nozzle assembly and the heat shield during operation of the radial inflow turbine engine.