| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine cooling structure suppressing the lowering of a turbine performance and a gas turbine. SOLUTION: This turbine cooling structure includes a turbine disk 31R supported rotatably about the axis, a plurality of cooling holes 33R, 34R disposed inside the turbine disk 31R, a partition part 61S which divides a first inlet space 41C into which a cooling medium is supplied from the outside, from a second inlet space 42C communicating with the plurality of cooling holes 33R, 34R, a nozzle part 62S provided inside the partition part 61S, a rim seal space 43C axially adjacent to the turbine disk 31R and communicating with the gap between a stationary blade 11S and a moving blade 21R, and a communication flow passage 64S which extends through the inside of the partition part 61S from a bypass space 44C which bypasses the nozzle part 62S and joins the first inlet space 41C and the second inlet space 42C toward the rim seal space 43C. COPYRIGHT: (C)2010,JPO&INPIT
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