A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials configured to redirect air moving through a primary gas path of the gas turbine engine, the turbine assembly comprising: a turbine case arranged around a central reference axis; a vane stage including the turbine vane comprising ceramic matrix composite materials shaped to form an airfoil that extends across the primary gas path of the gas turbine engine and an inner vane seal land located radially inward of the turbine vane, the inner vane seal land configured to be engaged by a rotating component to create a seal separating pressure zones (P1, P2) within the gas turbine engine when the turbine assembly is used in the gas turbine engine; and a vane-stage support comprising metallic materials that is configured to hold the turbine vane and the inner vane seal land in place relative to the turbine case, the vane-stage support includes a case mount that extends radially through the turbine case and a spar that extends from the case mount radially through the airfoil of the turbine vane to the inner vane seal land, wherein the turbine vane and the inner vane seal land are coupled to the spar so that forces applied to the vane stage are carried by the spar to the case mount and the turbine case during use of the turbine assembly in the gas turbine engine; wherein the case mount includes a coupling flange engaged with the turbine case, wherein the coupling flange extends along a radially-outwardly facing surface of the turbine case, the coupling flange includes a spar fixture that extends radially-inwardly from the coupling flange through a mount aperture formed in the turbine case, and the spar is coupled to the spar fixture inside the turbine case; wherein the spar fixture defines a radially-inwardly opening spar-receiver space inside the turbine case and the spar arranged in part within the spar-receiver space, characterised in that the spar fixture of the vane-stage support is engaged directly by the turbine vane of the vane stage so that forces applied to the turbine vane are carried by the case mount to the turbine case during use of the assembly in the gas turbine engine. a turbine case arranged around a central reference axis; a vane stage including the turbine vane comprising ceramic matrix composite materials shaped to form an airfoil that extends across the primary gas path of the gas turbine engine and an inner vane seal land located radially inward of the turbine vane, the inner vane seal land configured to be engaged by a rotating component to create a seal separating pressure zones (P1, P2) within the gas turbine engine when the turbine assembly is used in the gas turbine engine; and a vane-stage support comprising metallic materials that is configured to hold the turbine vane and the inner vane seal land in place relative to the turbine case, the vane-stage support includes a case mount that extends radially through the turbine case and a spar that extends from the case mount radially through the airfoil of the turbine vane to the inner vane seal land, wherein the turbine vane and the inner vane seal land are coupled to the spar so that forces applied to the vane stage are carried by the spar to the case mount and the turbine case during use of the turbine assembly in the gas turbine engine; wherein the case mount includes a coupling flange engaged with the turbine case, wherein the coupling flange extends along a radially-outwardly facing surface of the turbine case, the coupling flange includes a spar fixture that extends radially-inwardly from the coupling flange through a mount aperture formed in the turbine case, and the spar is coupled to the spar fixture inside the turbine case; wherein the spar fixture defines a radially-inwardly opening spar-receiver space inside the turbine case and the spar arranged in part within the spar-receiver space, characterised in that the spar fixture of the vane-stage support is engaged directly by the turbine vane of the vane stage so that forces applied to the turbine vane are carried by the case mount to the turbine case during use of the assembly in the gas turbine engine.