Abstract: To obtain an experiment scheme for full-scale static modelling comprehensive cooling efficiency under high-temperature and high-pressure in the first-stage rotating blades of an F-class heavy-duty gas turbine, and simultaneously acquire comprehensive cooling efficiency test data of the rotating blades under conditions close to real-world scenarios based on the high-temperature nozzle cascade test rig of the efficient and low-carbon gas turbine test facility, researches were conducted on the modelling method for the inlet conditions of rotating blades, and the key structural design of the transition section-first-stage stationary blade integrated adapter section and the test section. Subsequently, the validity of the scheme was verified by a combined approach of numerical simulation and experimental validation. Experiment results indicate that the experiment scheme and simulation method are reasonable and feasible, with good repeatability and high reliability of experiment results. This test scheme can provide a reference for subsequent similar comprehensive cooling efficiency experiments of rotating blades in the field of heavy-duty gas turbines.