Abstract: A gas turbine includes a turbine and an axial-radial diffuser. The turbine includes a last stage airfoil section, which includes a first inner annular wall, a plurality of airfoils, a tip shroud including a first outer annular wall, and a stationary shroud including a second outer annular wall. The first inner annular wall is angled at a first inner angle average, the first outer annular wall is angled at a first outer angle average, and the second outer annular wall is angled at a second outer angle average. The axial-radial diffuser includes a third inner annular wall and a third outer annular wall, wherein the first diffuser section is disposed immediately downstream from the last stage airfoil section, wherein the third inner annular wall is angled at a third inner angle average, and the third outer annular wall is angled at a third outer angle average.