| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a gas turbine that can suppress an increase of heat loads of divided rings. <P>SOLUTION: The gas turbine comprises: a turbine movable blade 33; a turbine static blade 32; the divided rings 52 surrounding the turbine movable blade 33 in the circumferential direction; shrouds 51 surrounding the turbine static blade 32 in the circumferential direction; and a combustion gas flow passage R1 which is formed inside the divided rings 52 and the shrouds 51, and in which a combustion gas flows. The outer shroud 51 (51a) is located at the upstream side of the divided ring 52 (52a) in the direction of a gas flow of the combustion gas, a seal gas lower in temperature than the combustion gas is supplied toward the combustion gas flow passage R1 from a gap between the divided ring 52a and the outer shroud 51a, the outer shroud 51a is arranged at the internal periphery of the downstream side of the gas flow direction and has a guide face 61 for guiding the combustion gas flowing therein toward the internal peripheral surface of the divided ring 52a, and the guide face 61 is formed so that a flow passage area of the combustion gas flow passage R1 may be expanded. <P>COPYRIGHT: (C)2013,JPO&INPIT |
