The invention relates to a turbine center frame for an aircraft gas turbine, with a plurality of first components and a plurality of second components, which, in the peripheral direction, are arranged alternately next to one another and, in a radial direction, bound a flow duct conveying hot gas, wherein the first components each have two first overlapping segments and the second components each have two second overlapping segments with a respective region of the transitioning from a first component to a second component or vice versa, a first overlapping segment and a second overlapping segment are arranged overlapping, and with at least one centering element, at which the first components and the second components are supported along the peripheral direction and in a radial direction with the first components and the second components essentially centered with respect to a central axis of the turbine center frame.