another further refinement the pressure gradient includes a pressure gradient along the cavity in yet another further refinement the pressure gradient includes a pressure gradient normal to the cavity embodiments include a gas turbine engine comprising a compressor system a primary combustor a turbine system including a hot section component the hot section component including a flowpath structure configured for operation in a gas turbine engine flowpath downstream of a primary combustor of the gas turbine engine wherein the flowpath structure includes a body having a tip portion and a hub portion wherein the body includes means extending in a spanwise direction between the tip portion and the hub portion for receiving a reheat flow for distribution to the turbine system and means for uniformly distributing the reheat flow from the means for receiving into the gas turbine engine flowpath in a refinement the means for uniformly distributing the reheat flow has a width in a flowpath direction that varies with location in the spanwise direction based on a pressure gradient at the location in the spanwise direction in another refinement the means for receiving has a cross sectional area that varies with location in the spanwise direction based on a pressure gradient at the location in the spanwise direction in yet another refinement the means for uniformly distributing the reheat flow has a centerline.