| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a gas turbine in which a seal air amount can be reduced by unifying the pressure distribution of the seal air. <P>SOLUTION: A corrugated unevenness 30 which is continuous in the circumferential direction is formed on inner and outer circumferential walls of a tail pipe 4 of a combustor. The flow speed of combustion gas to be supplied from the tail pipe 4 to a stationary blade shroud 6 is increased at a part of a convex section 30a, and its pressure is decreased more than that in a part of a concave section 30b. The flow speed is lower and the pressure is higher in the part of the concave section 30b than in the part of the convex section 30a. Thus, the combustion gas of low pressure passing through the convex section 30a hits a leading edge of a stationary blade 5 on the first stage, and combustion gas 3a of high pressure passing through the concave section 30b is supplied in an intermediate section between the stationary blades 5, 5 of the first stage which are adjacent to each other. As a result, the pressure distribution of the combustion gas around the stationary blades 5, 5, ... of the first stage is unified. <P>COPYRIGHT: (C)2013,JPO&INPIT</p> |
