A turbine of a turbomachine, comprising: opposing endwalls (201, 202) defining a pathway for a fluid flow; and a plurality of interleaved blade stages (21, 23, 25) and nozzle stages (22, 24, 26) arranged axially along the pathway, the plurality of the blade stages (21, 23, 25) including a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage, the plurality of the nozzle stages (22, 24, 26) including a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage, and at least one of the next-to-last blade stage and the next-to-last nozzle stage including aerodynamic elements configured to interact with the fluid flow and to define a radial throat distribution, wherein a throat is the narrowest region between adjacent nozzles or blades in a given stage, and the radial throat distribution is representative of throat measurements of the area of the region between adjacent nozzles or blades at various span, i.e. radial, locations; wherein adjacent nozzles of the next-to-last nozzle stage are arranged to exhibit the following non-dimensional characteristics wherein the area measurements are shown relative to a normalized value of 1.00 at relative span value 50.0 in the following table: Span Throat 100 1.20 ±10% 90.0 1.16 ±10% 70.0 1.08 ±10% 50.0 1.00 30.0 0.92 ±10% 10.0 0.84 ±10% 0.0 0.81 ±10% wherein adjacent blades of the next-to-last blade stage are arranged to exhibit the following non-dimensional characteristics wherein the area measurements are shown relative to a normalized to value of 1.00 at relative span value 50.0 in the following table: Span Throat 100 1.18 ±10% 90.0 1.15 ±10% 70.0 1.08 ±10% 50.0 1.00 30.0 0.93 ±10% 10.0 0.85 ±10% 0.0 0.80 ±10% wherein said non-dimensional characteristics exhibited by the adjacent nozzles of the next-to-last nozzle stage and said non-dimensional characteristics exhibited by the adjacent blades of the next-to-last blade stage achieve a substantially flat exit total pressure profile; wherein at least one of the next-to-last blade stage and the next-to-last nozzle stage include aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow at the last blade stage and the last nozzle stage. opposing endwalls (201, 202) defining a pathway for a fluid flow; and a plurality of interleaved blade stages (21, 23, 25) and nozzle stages (22, 24, 26) arranged axially along the pathway, the plurality of the blade stages (21, 23, 25) including a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage, the plurality of the nozzle stages (22, 24, 26) including a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage, and at least one of the next-to-last blade stage and the next-to-last nozzle stage including aerodynamic elements configured to interact with the fluid flow and to define a radial throat distribution, wherein a throat is the narrowest region between adjacent nozzles or blades in a given stage, and the radial throat distribution is representative of throat measurements of the area of the region between adjacent nozzles or blades at various span, i.e. radial, locations; wherein adjacent nozzles of the next-to-last nozzle stage are arranged to exhibit the following non-dimensional characteristics wherein the area measurements are shown relative to a normalized value of 1.00 at relative span value 50.0 in the following table: Span Throat 100 1.20 ±10% 90.0 1.16 ±10% 70.0 1.08 ±10% 50.0 1.00 30.0 0.92 ±10% 10.0 0.84 ±10% 0.0 0.81 ±10% wherein adjacent blades of the next-to-last blade stage are arranged to exhibit the following non-dimensional characteristics wherein the area measurements are shown relative to a normalized to value of 1.00 at relative span value 50.0 in the following table: Span Throat 100 1.18 ±10% 90.0 1.15 ±10% 70.0 1.08 ±10% 50.0 1.00 30.0 0.93 ±10% 10.0 0.85 ±10% 0.0 0.80 ±10% wherein said non-dimensional characteristics exhibited by the adjacent nozzles of the next-to-last nozzle stage and said non-dimensional characteristics exhibited by the adjacent blades of the next-to-last blade stage achieve a substantially flat exit total pressure profile; wherein at least one of the next-to-last blade stage and the next-to-last nozzle stage include aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow at the last blade stage and the last nozzle stage.