| 摘要 |
A tip shroud for moving blades, provided in a rear stage of a gas turbine, wherein cooling air is supplied thereto effectively to increase the creep life thereof. The tip shroud (11) is provided with cutout portions (12, 13) allowing a high-temperature combustion gas to pass therethrough, receiving the influence of thermal stress and constituting portions in which creep is liable to occur, grooves (31, 32; 33, 34) formed in a shroud surface, and cooling guide covers (21, 22) each for each set of grooves, the covers (21, 22) being closed at one end portion of each thereof with members (21a, 22a) and opened at the other end portions of each thereof, covering air holes (17), and supplying cooling air to the cutout portions (12, 13) so as to cool the same, whereby it is rendered possible to prevent the rise of the temperature of the metal of the cutout portions (12, 13) which receive the influence of the hightemperature combustion gas, and prolong the creep life of the tip shroud. |
