The present disclosure is directed to a gas turbine engine 10 including a turbine section 90 including a first rotating component 110 interdigitated along a longitudinal direction with a second rotating component 120. The first rotating component 110 and the second rotating component 120 are each coupled to a speed reduction assembly 45 in counter-rotating arrangement. The first rotating component 110 comprising an outer shroud 114 and a plurality of outer shroud airfoils 118 extended inward along a radial direction from the outer shroud (114). A connecting member 116 couples the outer shroud 114 to a radially extended first rotor 113. The second rotating component 120 comprising an inner shroud (112) and a plurality of inner shroud airfoils 119 extended outward along the radial direction from the inner shroud 112, the plurality of inner shroud airfoils 119 in alternating arrangement along the longitudinal direction with the plurality of outer shroud airfoils 118. The gas turbine engine 10 defines a radius per unit thrust defined by a maximum radius (RR) at the turbine section 90 over a maximum thrust output between approximately .0004 to approximately .0010 inches per pound thrust.