A COOLED BLADE OF GAS TURBINE

摘要

PURPOSE: A cooling blade of a gas turbine is provided to increase a heat transfer efficient by strengthening secondary flow by a lib because cold air flows into the inside by leaning to one side, by slantly installing multiple libs in an inner flow path and installing a structure on an inlet of the inner flow path. CONSTITUTION: A cooling blade of a gas turbine includes an airfoil (20) and an inner flow path (30). In the inner flow path of the airfoil, multiple libs (31) are slantly installed. On an inlet of the inner flow path, a structure (32) is installed to disturb the flow of cold air which flows into through an inlet port (11a). The structure is formed as multiple pins which are installed to make one side of the inlet of the inner flow path have higher density than the other side, or as a rectangular block shape which is installed to lean to one side of the inlet of the inner flow path, in order to make the inlet flow lean to one side. The inlet flow which leans to one side strengthens secondary flow by the libs in order to increase a heat transfer coefficient.