The cooling of gas turbine hot-gas-path components such as turbine blades and combustion chamber liner is essential for the continued safe operation of the engine. The present study focuses on the cooling aspects of an annular combustor liner. The cooling is generally achieved by a process known as film cooling, in which coolant gas is injected between the hot gas and the surface to be protected. In this study, two cooling configurations namely, three-dimensional slot and effusion configurations are combined in a single liner to form a hybrid cooling configuration and its cooling characteristics are investigated using commercial CFD software followed by experimental validation. The hybrid film cooling configuration has shown significant improvement in cooling effectiveness. In the subsequent study, the geometric parameters are optimized to enhance the film cooling performance at typical combustor operating conditions. The performance parameters like area-averaged film cooling effectiveness and its standard deviation are examined and compared between the baseline and the optimized configurations. The optimized geometry is also tested experimentally under laboratory conditions. In this seminar, the numerical and experimental results, and optimization methodology along with the key observations will be discussed in detail.