Patent ID: 7296415
Filing Date: 2007-11-20
Classification: F01D

Abstract:
1. A labyrinth sealing device for gas turbine engine including, from the upstream to the downstream end, a high-pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the inside envelope of a combustion chamber, said labyrinth sealing device comprising: a stator part mounted on the fixed wall element by an attaching device with flanges and supporting an annular wearing part, said annular wearing part working together with a rotor element, provided with at least one circumferential tooth and integral with the rotor of the high-pressure compressor to form a labyrinth seal, wherein at least one of said flanges of said attaching device has a thermal inertia such that the dilation response time of the stator part is increased with respect to the dilatation of the rotor during engine accelerations in order to reduce a leakage flow rate of said labyrinth seal.