| 摘要 |
FIELD: aircraft engineering. ^ SUBSTANCE: invention to sealing devices of gas-turbine engines of aircraft and ground application. Proposed sealing device of gas-turbine engine includes working part consisting of labyrinth with sealing lips and mating stator flange, and deflector forming slot space together with flange. According to invention, device contains regulating part installed at outlet of working part which consists of labyrinth with lips and stator flange and is separated from working part by ring space connected at outlet by channels with low-pressure space and at inlet, with interlip spaces of working and regulating parts. Slot space at outlet is connected with interlip space of regulating part, labyrinths and stator flanges of working and regulating parts, respectively, are made integral or are connected by fixed unit at F1/F2=1/20 and H/delta2=2/50 where F1 is are of channels; F2 is area of ring clearance between lip of labyrinth and stator of working part of sealing device; H is minimum height of slot space; delta2 is radial clearance between first lip of labyrinth and stator of regulating part. ^ EFFECT: improved efficiency of sealing device owing to control of flow rate of cooling air, provision and constant minimum value of radial clearance to be sealed. ^ 1 dwg |
