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A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectio

A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) arranged to deliver a flow of reactants into the downstream combustion stage to be mixed with the cross-flow of combustion gases. Disclosed injector assemblies are arranged in expanding cross-sectional area (24) to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.

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1. A ducting arrangement in a combustion stage downstream of a main combustion stage of a gas turbine engine, the ducting arrangement comprising: a flow-accelerating structure defining a flow-accelerating cone between an inlet of the flow-accelerating structure and an outlet of the flow-accelerating

1. A ducting arrangement in a combustion stage downstream of a main combustion stage of a gas turbine engine, the ducting arrangement comprising: a flow-accelerating structure defining a flow-accelerating cone between an inlet of the flow-accelerating structure and an outlet of the flow-accelerating structure, the inlet fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage, wherein a circular cross-sectional profile of the flow-accelerating cone narrows in diameter from the inlet towards the outlet;a duct fluidly coupled to receive the cross-flow of combustion gases from the flow-accelerating structure, wherein the duct comprises a duct segment comprising an expanding cross-section profile in the downstream combustion stage, wherein the expanding cross-sectional profile expands in cross-sectional area in a direction towards a turbine section of the gas turbine engine, wherein the duct segment comprises a circular cross-sectional area;an injector assembly disposed in the duct segment, wherein said injector assembly comprises a plurality of circumferentially arranged reactant-guiding structures disposed about the duct segment, each circumferentially arranged reactant-guiding structure arranged to deliver a flow of reactants along an axis of an injection orifice, the axis of the injection orifice disposed at an injection angle with respect to the cross-flow of combustion gases, and into the downstream combustion stage to be mixed with the cross-flow of combustion gases;wherein the injector assembly comprises a fuel manifold and an air plenum, the fuel manifold being disposed within the air plenum, wherein the plurality of circumferentially arranged reactant-guiding structures are connected to, and between, the duct segment and a wall of the air plenum;wherein the injector assembly is configured to mix fuel from the fuel manifold and air from the air plenum to generate the respective flows of reactants delivered by the plurality of circumferentially arranged reactant-guiding structures;wherein an outlet of the fuel manifold delivers fuel into the injector assembly in a direction substantially aligned with a respective axis of an injection orifice of a respective circumferentially arranged reactant-guiding structure; andwherein the duct segment includes a circumferentially-extending passageway located along a downstream periphery of the duct segment to inject a peripheral stream of air downstream from the injector assembly. 2. The ducting arrangement of claim 1, wherein the injection angle is in a range from 10° to 80°. 3. The ducting arrangement of claim 1, wherein the plurality of circumferentially arranged reactant-guiding structures are disposed in a circular row. 4. The ducting arrangement of claim 1, wherein the plurality of circumferentially arranged reactant-guiding structures are spaced apart, each circumferentially arranged reactant-guiding structure forming a respective radially-extending slot. 5. The ducting arrangement of claim 4, wherein each respective radially-extending slot has an increasing width as the slot extends from a radially inward location to a radially outward location. 6. The ducting arrangement of claim 1, wherein the plurality of circumferentially arranged reactant-guiding structures are arranged in a plurality of concentric circular rows, each concentric circular row arranged at different axial locations in the duct segment. 7. The ducting arrangement of claim 6, wherein respective injection orifices of circumferentially arranged reactant-guiding structures in a first row of the plurality of concentric circular rows comprise respective injection areas that are larger in size relative to respective injection areas of respective injection orifices of circumferentially arranged reactant-guiding structures located in rows of the plurality of concentric circular rows located upstream from the first row. 8. The ducting arrangement of claim 6, further comprising a larger number of respective injection orifices of circumferentially arranged reactant-guiding structures in a first row of the plurality of concentric circular rows than a number of respective injection orifices of circumferentially arranged reactant-guiding structures located in rows of the plurality of concentric circular rows located upstream relative to the first row. 9. The ducting arrangement of claim 1, wherein the plurality of circumferentially arranged reactant-guiding structures is arranged along a spiral path in the duct segment, wherein respective injection orifices of the circumferentially arranged reactant-guiding structures comprise relatively larger injection areas as the spiral path extends from a radially inward location to a radially outward location. 10. The ducting arrangement of claim 1, wherein the plurality of circumferentially arranged reactant-guiding structures is arranged along a spiral path in the duct segment, wherein respective injection orifices of the circumferentially arranged reactant-guiding structures comprise substantially constant injection areas, and wherein a spacing between the circumferentially arranged reactant-guiding structures comprises substantially uniform spacing as the spiral path extends from a radially inward location to a radially outward location. 11. The ducting arrangement of claim 3, wherein injection orifices of the plurality of circumferentially arranged reactant-guiding structures each comprise a cross-sectional profile selected from the group consisting of a circular cross-sectional profile, a non-circular cross-sectional profile, a star-shaped cross-sectional profile, a cross-shaped cross-sectional profile, a multi-lobe cross-sectional profile, an airfoil-shaped cross-sectional profile, and a slotted cross-sectional profile having a major axis of the slotted cross-sectional profile aligned parallel or perpendicular relative to a direction of the cross-flow. 12. A ducting arrangement for a combustion stage downstream from a main combustion stage of a gas turbine engine, the ducting arrangement comprising: a duct fluidly coupled to receive a cross-flow of combustion gases from a flow-accelerating cone fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage, wherein the duct comprises a duct segment comprising an expanding cross-sectional profile, wherein a cross-sectional area of the expanding cross-sectional profile expands in a direction toward a turbine section of the gas turbine engine;an injector assembly disposed in the duct segment, wherein said injector assembly comprises a plurality of circumferentially arranged reactant-guiding structures disposed about the duct segment, each circumferentially arranged reactant-guiding structure arranged to deliver a flow of reactants along an axis of an injection orifice, the axis of the injection orifice disposed at an injection angle with respect to the cross-flow of combustion gases, into the downstream combustion stage to be mixed with the cross-flow of combustion gases;wherein the expanding cross-sectional profile in the duct segment and the plurality of circumferentially arranged reactant-guiding structures are arranged to reduce total pressure loss in the downstream combustion stage of the gas turbine engine without substantially affecting a subsonic speed of the cross-flow of combustion gases passing through the downstream combustion stage of the gas turbine engine;wherein the injector assembly comprises a fuel manifold and an air plenum, the fuel manifold being disposed within the air plenum, wherein the plurality of circumferentially arranged reactant-guiding structures are connected to, and between, the duct segment and a wall of the air plenum;wherein the injector assembly is configured to mix fuel from the fuel manifold and air from the air plenum to generate the respective flows of reactants delivered by the plurality of circumferentially arranged reactant-guiding structures;wherein an outlet of the fuel manifold delivers fuel into the injector assembly in a direction substantially aligned with a respective axis of an injection orifice of a respective circumferentially arranged reactant-guiding structure;wherein the duct segment includes a circumferentially-extending passageway located along a downstream periphery of the duct segment to inject a peripheral stream of air downstream from the injector assembly; andwherein at least one of the duct, the plurality of reactant-guiding structures, the fuel manifold and the air plenum comprises a unitized structure.