Recoatable exhaust liner cooling arrangement
AssigneeUnited Technologies Corporation
InventorsMichael Joseph Murphy, Jeffrey R. Lavin
Life of this patent
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Abstract
A gas turbine engine includes an exhaust liner having cold and hot sheets radially spaced from one another and interconnected by a band arranged in a cavity between the hot and cold sheets. In one example, the band is Z-shaped to permit thermal growth of the hot sheets relative to the cold sheets in the axial and radial directions. The hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space. Cooling fluid is provided to the cavity through impingement jets in the cold sheet. The slots are arranged radially between the hot sheet portions.
Claims10
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.
Dependencies are inferred from the claim text.