| 摘要 |
<p>The cooling performance of cooling blades of a gas turbine is enhanced by devising the arrangement of turbuletors on the leading edge section. The round part on the leading edge section of each cooling blade of a gas turbine is formed into a triangular cooling passage (1) as shown in Fig. 1(a), within which orthogonal turbuletors (11, 12) are disposed. The rear part is formed into a rectangular cooling passage (2) as shown in Fig. 1(b), within which oblique turbuletors (12, 13) are arranged. The passages are similar to a cooling passage (3) of the leading edge section. These tubuletor arrangements of Figs. 1(a), 1(b) are combined into the cooling passage (3) of the leading edge section as shown in Fig. 1(c), in which an orthogonal turbuletor (21) and oblique turbuletors (22, 23) are arranged. The heat transfer characteristics of the leading edge section is improved since the turbuletors are so arranged in the passage (3) that the round part and the part behind the round part have good heat transfer characteristics.</p> |
