In a gas turbine with a blade carrier (2) coaxially suspended in a turbine casing (3), both the turbine casing and the blade carrier are provided with a horizontal parting plane. An exhaust casing (5), the limiting walls of which essentially comprise an annular inner part on the hub side and an annular outer part (7), is connected gas-tight by way of an annular flange (7A) to an annular flange (3A) of the turbine casing (3). A two-part separating ring (13) with at least one tapering end face (13A) is arranged between the annular flanges. The angle of the tapering end face (13A) is designed for self-locking. <IMAGE>
