Patent ID: 8127526

Claim:
A gas turbine engine comprising: an exhaust liner including axially adjoining hot sheets radially spaced from one another at a joint that provides cooling slots arranged radially between the adjoining hot sheets; a cold sheet spaced radially outwardly from the hot sheets and connected to at least one of the hot sheets by a band arranged in a cavity secured between the hot and cold sheets, wherein the hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space, the slots are arranged radially between the portions; wherein the hot sheets provide first and second hot sheets each having first and second end portions, first end portion of the first hot sheet arranged radially outwardly of the second end portion of the second hot sheet; and wherein a portion of the band is secured at the joint in a location in which the first and second end portions respectively of the first and second hot sheets axially overlap, and the band is discrete from either the hot sheets or the cold sheet.