GAS TURBINE ENGINE STAGE PROVIDED WITH A LABYRINTH SEAL
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United States of America Patent
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Issued Date -
May 11, 2017
app pub date -
Nov 10, 2016
filing date -
Nov 11, 2015
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Abstract
In a gas turbine engine stage, a labyrinth seal has a layer of abradable material arranged on a static part and radially delimited by a cylindrical surface, which is continuous and has a constant diameter in an initial assembly configuration; the seal has at least three tabs, which are arranged on the rotating part, radially facing the abradable material, and are constituted by two side tabs and an intermediate tab having a smaller radial height; this height still allows the abradable material to be engraved, due to the effect of thermal expansion and of the relative rotation during operation; the tabs are positioned axially in such a way that, in the running operational configuration, the layer of abradable material has two seats, which have been fretted by the tips of the two side tabs during operation, and are axially separated by a step, while the intermediate tab is arranged at said step.
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