Two spool gas turbine engine with interdigitated turbine section

A gas turbine engine, wherein the gas turbine engine defines a longitudinal direction, a radial direction, and a circumferential direction, and an axial centerline, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction, the gas turbine engine comprising:

• a combustion section;
• a turbine section comprising a first rotating component and a second rotating component, wherein the first rotating component defines a lower speed spool than the second rotating component, wherein the first rotating component includes an inner shroud and an outer shroud outward of the inner shroud in the radial direction, wherein the outer shroud defines a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction, and wherein the first rotating component further includes at least one connecting airfoil coupling the inner shroud and the outer shroud, and wherein the second rotating component is upstream of the one or more connecting airfoils of the first rotating component along the longitudinal direction, the second rotating component includes a plurality of second airfoils extended outward in the radial direction, and wherein the first rotating component defines at least one stage of the plurality of outer shroud airfoils upstream of the second rotating component, the first rotating component comprising a first stage airfoil immediately downstream of the combustion section.