GAS TURBINE COMBUSTION LINER WITH LAMINATED COMPLEX STRUCTURE INTEGRATING HOLLOW PIN AND SUCTION STRUCTURE CAPABLE OF IMPINGEMENT AND EFFUSION COOLING

摘要

The present invention relates to a combustor liner of a gas turbine. The present invention relates to multi-layer gas turbine combustor liner including an impingement hole through which the cooling fluid initially flows, an effusion hole through which the cooling fluid is ultimately discharged, and a suction hole through which the cooling fluid can move between the multi-layered structures, which is divided into a first region in which a hollow pin for forming the impingement hole is disposed and in which a space through which the fluid can flow and a second region in which a hollow pin for forming the effusion hole is disposed and in which a space through which the fluid can flow. A cooling fluid flows into the space of the second zone through the impingement hole, moving from the second zone to the space of the first zone, after flowing from the first zone to the second zone through the suction holes, it is discharged through the effusion holes formed in the first region. Through this configuration, it is possible to increase the heat exchange area between the cooling fluid and the combustor wall, and thus by promoting heat transfer, it is possible to maximize the cooling efficiency and improve the pressure drop characteristic.;COPYRIGHT KIPO 2018