[1] SUPER CRITICAL FLUID GAS COOLING GAS TURBINE DEVICE, US Patent #
[2] Internal structure of a gas turbine blade for trailing edge cooling, Korea Patent #
[3] Shapes of pin and dimple structures for enhancing the heat transfer in the pin-fin array, Korea Patent #10-1396905
[4] Modified internal passages of rotating turbine blade to enhance cooling performance, Korea Patent #10-1411347
[5] Cooling Pipe, Korea Patent #10-1405014
[6] Gas Turbine Combustor, Korea Patent #10-1344373
[7] Design for improving maintenance and cooling performance of after part in a combustion liner, Korea Patent #10-1123243
[8] Internal cooling passage of gas turbine blade using helical coil, Korea Patent #10-1107451
[9] Backward injections and arrangement of film cooling holes with backward injections, Application #10-2014-0142500, Korea Patent Pending
[10] SUPER CRITICAL FLUID GAS COOLING GAS TURBINE DEVICE, Application # PCT/KR2014/003547, PCT
[11] Expanded film cooling holes with compound curves, Application # 10-2014-0099256, Korea Patent Pending