| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a technology effectively preventing a gap between a tail pipe and stationary blade shrouds of a combustor from being damaged by burn when the pressure of combustion gas in the circumference direction of a stationary blade row is uneven. <P>SOLUTION: This gas turbine includes the combustor which ejects combustion gas 3a from the tail pipe 4, and a turbine to which the combustion gas 3a is supplied from the tail pipe 4. The turbine includes stationary blades 5 and the stationary blade shrouds 6 which are positioned on the downstream side of the tail pipe 4 and support the stationary blades 5. Openings 4c for jetting cooling air toward the upstream side ends of the stationary blade shrouds 6 are provided at the downstream side end of the tail pipe 4. Cooling air passages 4b-4 which are provided on the upstream sides of the stagnation points at the leading edges of the stationary blades for supplying cooling air to the openings 4c, and cooling air passages 4b-3 which are provided in the middle of the stagnation points for supplying cooling air to the openings 4c, are formed in the tail pipe 4. A turbulent flow generating means which generates turbulent flow in the cooling air is formed in the cooling air passage 4b-3. <P>COPYRIGHT: (C)2012,JPO&INPIT |
