FIELD: engines and pumps.
SUBSTANCE: invention is related to labyrinth seals for gas-turbine engines. Gas-turbine engine comprises from inlet to outlet end downstream the following components - high pressure compressor with rotor, diffuser and fixed element of wall, which forms at least one part of internal shell of combustion chamber. Design of labyrinth seal for gas-turbine engine includes stator part installed on wall element by means of fastening facility with flanges and bearing circular wearing part. Wearing part operates together with rotor element having at least one peripheral tooth and is arranged as a whole with compressor rotor to create labyrinth seal. One of fastening facility flanges is arranged as massive, so that degree of stator part expansion is matched with degree of rotor element expansion during engine speed-ups.
EFFECT: makes it possible to increase durability of labyrinth seal due to maintenance of minimum clearance in seal at transition modes of gas-turbine engine operation.
7 cl, 1 dwg
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