Intermediate turbine casing for a gas turbine, in particular an aircraft gas turbine, comprising: a plurality of outer wall elements arranged consecutively in the circumferential direction; a plurality of inner wall elements arranged consecutively in the circumferential direction, the outer wall elements and the inner wall elements defining a flow channel for exhaust gas by means of the mutually facing inner sides; a plurality of strut fairing elements arranged in the radial direction between a particular outer wall element and a particular inner wall element, an outer casing which surrounds the outerwall elements and the innerwall elements, and an annular retaining structure which surrounds a mounting region for a shaft of the gas turbine, in particular the shaft of the high-pressure turbine, the strut fairing elements being designed such that they have a receiving space for receiving bearing elements which extend substantially in the radial direction from the annular retaining structure to the outer casing through the flow channel such that exhaust gas flowing through the flow channel is guided around the bearing elements by the strut fairing elements, the outer wall elements, the inner wall elements and the strut fairing elements being produced at least in part from ceramic matrix composites, the outer wall elements being designed such that they are coupled to the outer casing, and the inner wall elements being designed such that they are coupled to the annular retaining structure, at least some of the plurality of outer wall elements and at least some of the plurality of inner wall elements having fairing openings in which radial ends (54, 60a) of the strut fairing elements are received, characterized in that the strut fairing elements are floatingly mounted between the outer wall elements and the inner wall elements by means of respective fairing seal arrangements. a plurality of outer wall elements arranged consecutively in the circumferential direction; a plurality of inner wall elements arranged consecutively in the circumferential direction, the outer wall elements and the inner wall elements defining a flow channel for exhaust gas by means of the mutually facing inner sides; a plurality of strut fairing elements arranged in the radial direction between a particular outer wall element and a particular inner wall element, an outer casing which surrounds the outerwall elements and the innerwall elements, and an annular retaining structure which surrounds a mounting region for a shaft of the gas turbine, in particular the shaft of the high-pressure turbine, the strut fairing elements being designed such that they have a receiving space for receiving bearing elements which extend substantially in the radial direction from the annular retaining structure to the outer casing through the flow channel such that exhaust gas flowing through the flow channel is guided around the bearing elements by the strut fairing elements, the outer wall elements, the inner wall elements and the strut fairing elements being produced at least in part from ceramic matrix composites, the outer wall elements being designed such that they are coupled to the outer casing, and the inner wall elements being designed such that they are coupled to the annular retaining structure, at least some of the plurality of outer wall elements and at least some of the plurality of inner wall elements having fairing openings in which radial ends (54, 60a) of the strut fairing elements are received, characterized in that the strut fairing elements are floatingly mounted between the outer wall elements and the inner wall elements by means of respective fairing seal arrangements.