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, the turbine case including an annular shell and a locating hanger that extends radially inwardly from the annular shell; a vane stage including the turbine vane comprising ceramic matrix composite materials shaped to form an airfoil that is configured to extend 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 including a case mount that couples to the annular shell and engages the locating hanger to axially and radially align the vane-stage support relative to 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; characterised in that the case mount includes a coupling flange that extends along a radially-inwardly facing surface of the turbine case, and a retainer ring spaced axially from the locating hanger with the coupling flange sandwiched axially therebetween, and the case mount further includes a clamp fastener configured to clamp a portion of the coupling flange between the annular shell and the retainer ring. a turbine case arranged around a central reference axis, the turbine case including an annular shell and a locating hanger that extends radially inwardly from the annular shell; a vane stage including the turbine vane comprising ceramic matrix composite materials shaped to form an airfoil that is configured to extend 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 including a case mount that couples to the annular shell and engages the locating hanger to axially and radially align the vane-stage support relative to 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; characterised in that the case mount includes a coupling flange that extends along a radially-inwardly facing surface of the turbine case, and a retainer ring spaced axially from the locating hanger with the coupling flange sandwiched axially therebetween, and