A fuel injection system includes an outer support defining a fuel manifold and an inner support, with a feed arm extending radially between the inner support and the outer support. A plurality of outlet openings extending in an axial direction from the feed arm for feeding respective injection nozzles. The feed arm defines a plurality of fuel passages therethrough in fluid communication with the fuel manifold and outlet openings to supply fuel from the fuel manifold to the outlet openings. A heat shield extends from the outer support to the inner support and extends about the outer support and the feed arm to provide heat shielding to the fuel manifold and the fuel passages.

A gas turbine engine includes: a compressor section including a compressor mean radius; a combustor section fluidly coupled downstream of the compressor section and include a combustor mean radius; and a turbine section fluidly coupled downstream of the combustor section and a turbine mid-span radius. The combustor mean radius is greater than each of the compressor mean radius and the turbine mid-span radius.

A gas turbine engine includes: a compressor section including a compressor mean radius; a combustor section fluidly coupled downstream of the compressor section and include a combustor mean radius; and a turbine section fluidly coupled downstream of the combustor section and a turbine mid-span radius. The combustor mean radius is greater than each of the compressor mean radius and the turbine mid-span radius.

A combustion system with surface-less heat energy exchange for efficient heat energy capture and lower pollutant emission, comprising: a first line feeding an oxygen-rich reactive; a second line feeding a hydrogen fuel; a vessel containing feed-water, a combustion enclosure without a bottom wall submersed into the feed water contained in a vessel, the combustion enclosure configured to receive the feed from each of the first and second line and combust a mixture of the two feeds in a pocket formed between an inner top and side walls of the combustion enclosure and a top surface of the feed-water contained in the vessel; and the combustion within the pocket yielding a high temperature and pressure combustion product and by-product directly into the feed-water of the vessel.

A combustion system with surface-less heat energy exchange for efficient heat energy capture and lower pollutant emission, comprising: a first line feeding an oxygen-rich reactive; a second line feeding a hydrogen fuel; a vessel containing feed-water, a combustion enclosure without a bottom wall submersed into the feed water contained in a vessel, the combustion enclosure configured to receive the feed from each of the first and second line and combust a mixture of the two feeds in a pocket formed between an inner top and side walls of the combustion enclosure and a top surface of the feed-water contained in the vessel; and the combustion within the pocket yielding a high temperature and pressure combustion product and by-product directly into the feed-water of the vessel.

A combustor arrangement, the combustor arrangement being annular and being arranged about an axis, the axis defining an axial direction, having an annular housing to house a plurality of burners and an annular combustion chamber, the burners arranged circumferentially about the axis inside the annular housing, wherein an annular space is defined between the housing, the burners and the annular combustion chamber, the annular space arranged to guide a compressed fluid. A plurality of stiffening plates, each arranged within the annular housing, wherein two adjacent ones of the burners are separated by one of the stiffening plates. A combustor separating wall arrangement separates the annular space from the annular combustion chamber provides openings for the burners. The stiffening plates are arranged angled and connected to the combustor separating wall arrangement and two boundary walls of the housing, and further plates extend into the annular space.

A system includes an internal manifold ring defining at least one circumferentially extending flow channel. A plurality of feed arms extends outward from the manifold ring. A circumferentially segmented outer ring can be supported from the feed arms, outboard of the feed arms. Each feed arm can include a plurality of branches extending therefrom, wherein each branch is in fluid communication with the manifold ring through a respective one of the feed arms. A plurality of nozzles can be included, each nozzle connected to a respective one of the branches, wherein the system is devoid of nozzles radially inward from the manifold ring.

A system includes an internal manifold ring defining at least one circumferentially extending flow channel. A plurality of feed arms extends outward from the manifold ring. A circumferentially segmented outer ring can be supported from the feed arms, outboard of the feed arms. Each feed arm can include a plurality of branches extending therefrom, wherein each branch is in fluid communication with the manifold ring through a respective one of the feed arms. A plurality of nozzles can be included, each nozzle connected to a respective one of the branches, wherein the system is devoid of nozzles radially inward from the manifold ring.

A turbine including a turbine rotor, a turbine casing, a plurality of turbine rotor cascades, a plurality of turbine stator cascades, and a diffuser forming an exhaust gas flow path through which exhaust gas flows from one side in the axial direction toward another side, and which is provided on the other side in the axial direction from a last stage rotor cascade. The diffuser has an inner cylinder, an outer cylinder forming the exhaust gas flow path between the outer cylinder and the inner cylinder, and a strut which connects the inner cylinder and the outer cylinder in the radial direction. The outer cylinder has a first inclined surface extending outward from the inside in the radial direction from an inlet of the exhaust gas flow path toward the other side in the axial direction. The first inclined surface forms an angle of 16 to 24 with the axis.

A turbine including a turbine rotor, a turbine casing, a plurality of turbine rotor cascades, a plurality of turbine stator cascades, and a diffuser forming an exhaust gas flow path through which exhaust gas flows from one side in the axial direction toward another side, and which is provided on the other side in the axial direction from a last stage rotor cascade. The diffuser has an inner cylinder, an outer cylinder forming the exhaust gas flow path between the outer cylinder and the inner cylinder, and a strut which connects the inner cylinder and the outer cylinder in the radial direction. The outer cylinder has a first inclined surface extending outward from the inside in the radial direction from an inlet of the exhaust gas flow path toward the other side in the axial direction. The first inclined surface forms an angle of 16 to 24 with the axis.