Film-Cooling Techniques at the End of Combustor and Inlet of Turbine in a Gas Turbine Engine: A Review

This study was done to extend database knowledge about the film cooling holes function at the end of combustor and inlet of turbine. Using the well-known Brayton cycle, rising the turbine inlet temperature, is the key to get higher engine efficiency in gas turbine engines. But the high temperature of the combustor exit flow causes non-uniformities. These non-uniformities lead to a reduction in the expected life of critical components. Therefore a cooling technique should be designed to protect these parts. Film cooling is one of the most effective external cooling methods. In this system, a low temperature thin boundary layer such as buffer zone is formed and attached on the protected surface. In this study, a literature survey was done on the limited surveys.