Jet impingement cooling is an important way to cool turbine blades. Ribbed channels are widely used in the chord region of turbine blades and are an important internal cooling structure. In the design process of the internal cooling structure of the conventional turbine blade, it is the primary consideration of the designer to improve the heat transfer coefficient at the surface of the inner cooling passage. With the development of the design of the inner cooling structure of the turbine blade, the pressure loss caused by the inner cooling passage has been paid more and more attention. Therefore, many studies have begun to comprehensively consider the potential of various rib structures in enhancing heat transfer and reducing flow resistance. In the design process of the internal cooling structure of the conventional turbine blade, the rib is placed on the blade, which increases the blade burden. In this paper, the classic rib structure is changed, and the rib is placed on the impingement plate to research its heat transfer characteristics. In this study, the effects of ribs of different structures on heat transfer were tested. Calculate the working conditions of Reynolds number Re = 15000, 20000, 25000, 30000. The numerical calculation of the SST k-w model is used to evaluate the average Nusselt number of the target plate and the flow coefficient of the channel, and the heat transfer distribution and flow field are analyzed. This study is expected to achieve better coordination between improved heat transfer and reduced flow resistance.