Injector assembly and ducting arrangement including such injector assemblies in a combustion system for a gas turbine engine

A ducting arrangement in a combustion stage of a gas turbine engine, the ducting arrangement comprising:

• a flow-accelerating structure having an inlet and an outlet, the inlet of the flow-accelerating structure fluidly coupled to receive a flow of combustion gases from a combustor outlet;
• and
• at least one injector assembly disposed between the inlet and the outlet of the flow-accelerating structure, the injector assembly comprising:
• a reactant-guiding structure having an inlet side and an outlet side, the reactant-guiding structure defining a curvilinear flow path to route a flow of reactants from a first flow direction at the inlet side to a second flow direction at the outlet side toward the cross-flow of combustion gases, wherein the second flow direction is arranged to achieve a desired injection angle of the flow of reactants relative to the cross-flow of combustion gases;
• and
• a cross-flow guiding structure having an inlet side and an outlet side, the cross-flow guiding structure defining a generally axially-extending flow path to route through the injector assembly a portion of cross-flow of combustion gases received at the inlet side of the cross-flow guiding structure toward the outlet side of the cross-flow guiding structure, wherein a flow direction of the portion of the cross-flow of combustion gases exiting at the outlet side of the reactant-guiding structure is arranged to achieve a desired injection angle relative to the flow direction of the flow of reactants at the outlet side of the reactant-guiding structure.