FIELD: aviation.
SUBSTANCE: the invention relates to an abradable element (29, 36) of a labyrinth seal located in a gas turbine engine around the axis (X) of the gas turbine engine and containing an outer layer (55) located opposite the combs (4, 5) installed on the first part of the gas turbine engine. The abradable element of the labyrinth seal is mounted on the second part of the gas turbine engine, the first part and the second part being rotatable relative to each other around the axis (X). At the same time, in the specified outer layer (55), which has partitions (31, 32; 47; 64, 65), bounding cells, at least three areas (33, 34, 35; 43, 44, 45, 46; 61, 62, 63) formed by annular strips of the labyrinth seal abradable element, which are located side by side, follow each other along the axis (X ) and have wear resistance values that gradually change along the axis. The cells are rectangular, with all said baffles oriented at an angle of 30 to 60 degrees with respect to the (X) axis. EFFECT: the invention increases the wear resistance of the abradable element.
11 cl, 8 dwg
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Authors
Dates
2022-08-18—Published
2018-11-20—Filed