Liner Element of a Turbomachine and Correspoding Connection Assembly
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United States of America Patent
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app pub date -
Jul 19, 2017
filing date -
Jul 27, 2016
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Abstract
A liner element (10), in particular a heat shield element or casing element, of a turbomachine, in particular a gas turbine, including a fastening portion (12) having at least one bore (14-1, 14-2) through which a connection unit (42) having, in particular a pin-type or bolt-type form, is introducible along a bore axis (BA); a liner portion (16) that adjoins the fastening portion (12); the fastening portion (12) and the liner portion (16) being formed in one piece, and having an annular or ring segment shape. The bore (14-1, 14-2) is provided in a depression (24-1, 24-2) formed in the fastening portion (12), the depression (24-1, 24-2) being essentially formed concentrically about the bore (14-1, 14-2).
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