GAS TURBINE SEAL APPARATUS

摘要

The invention relates to a gas turbine seal structure between end portions of a moving blade platform and a stationary blade inside shroud, in which a sealing performance is improved by increasing a resistance of a flow. A seal plate (21, 31) is mounted to an end portion of a platform (2, 2') of a moving blade (1) and a seal portion is constituted by a seal fin (22, 32) and a honeycomb seal (16, 17) disposed to a lower surface of an end portion (12a, 12b) of an inside shroud (12) of a stationary blade (11). A sealing air from the stationary blade (11) produces a high temperature in a cavity (14) and is flown into a space (18, 19), and also an air leaked from a cooling air of the moving blade (11) is going to escape to a high temperature combustion gas passage from the space (18, 19) through a seal portion, however, since three seal fins (22, 32) of the seal plate (21, 31) are inclined in such a manner as to oppose to the air flow, the air resistance is increased and the flowing-out of the air is prevented. Accordingly, a sealing performance is improved in comparison with the conventional structure having no seal fin (22, 32).