| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustor for preventing deformation and crack in a transition piece flow sleeve of the gas turbine combustor and improving reliability of the transition piece flow sleeve, while improving cooling characteristics of the transition piece. <P>SOLUTION: The gas turbine combustor comprises: a fuel nozzle for injecting a mixed gas of fuel and air; a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber; a transition piece which is a flow path for guiding a combustion gas generated in the liner to turbine blades; and a transition piece flow sleeve for wrapping the outside surface of the transition piece. In the gas turbine combustor, a plurality of air introduction holes for introducing air into the transition piece flow sleeve are formed in regions of the transition piece flow sleeve excluding regions that are corner portions of the transition piece flow in the cross-sectional direction thereof. <P>COPYRIGHT: (C)2012,JPO&INPIT |
