The fields of this project are power engineering and engineering thermophysics, as well as advanced manufacturing of gas turbines. Gas turbines are the core power equipment in the aviation and naval propulsion and clean power generation industries. Gas turbine technology represents the country's overall scientific and technological and industrial strength. The improvement of thermal efficiency of gas turbines mainly relies on continuously increasing the turbine inlet temperature (while appropriately increasing the total pressure ratio). The existing turbine blade cooling technology is approaching its limit, so it is necessary to develop more advanced and efficient internal composite cooling technology for turbine blades. Surface recessed vortices have the advantages of low flow resistance, high heat transfer enhancement capabilities, and easy combination with existing cooling structures. However, due to the complexity of vortex generated by surface recesses, there is a lack of clear understanding of their flow control and heat transfer enhancement mechanisms and local performance optimization internationally. The flow and heat transfer mechanisms under the combined condition of surface recessed vortices and various turbulence ribs are unclear, so it is difficult to accurately predict and design high-performance composite cooling of turbine blades based on surface recessed vortices. In response to the above problems, with the support of the National Natural Science Foundation of China, the Shanghai City Science and Technology Commission, the following main research results have been achieved after ten years of research: (1) An innovative structure of the surface recessed vortex was proposed and the dynamic control of the recessed vortex was improved., achieving a significant improvement in the intensity and uniformity of the enhanced heat transfer of the surface recessed vortex. The innovative mechanism of multiple vortices to enhance heat transfer in the vortex motion of surface depressions, and the influence of surface depressions structural parameters on vortex control and heat transfer characteristics were discovered, breaking through the limitation that the heat transfer enhancement of air flow must be less than the increase of flow resistance; A micro-structured rib-recessed vortex composite cooling structure is innovatively proposed, which solves the problem of serious uneven heat transfer caused by the flow separation of the boundary layer at the leading edge of the recessed vortex, and realizes the synergistic effect of the micro-rib induced vortex and the surface recessed vortex to significantly improve the heat transfer. Enhance the ability, and build the composite cooling heat transfer and flow resistance model. (2) A high-efficiency composite cooling technology for the trailing edge of turbine blades is proposed, which improves the cooling performance of the trailing edge of turbine blades. Innovatively combining the arrangement of concave vortex on the end wall surface with the flow velocity distribution characteristics of the pin-fin array reveals the mechanism of the interaction between the vortex generated by the surface concave and the pin-fin wake vortex to improve the heat transfer of the end wall, achieving significant improvement while maintaining the same flow resistance. It improves the convective enhanced heat transfer capacity and heat transfer uniformity of the end wall of the blade trailing edge, reduces the thermal resistance of the blade wall and reduces the weight of the blade. (3) A matrix rib-depressed vortex composite cooling technology for turbine blades is proposed, which achieves better heat transfer performance than traditional matrix rib cooling. A matrix rib-recessed vortex compound cooling combining U-section sub-channels and surface recessed vortices was innovatively proposed, which overcomes the problem of thermal stress concentration in traditional matrix ribs; it was discovered that the interaction of staggered flow shear forces in the matrix fin cooling channels generates longitudinal vortex. The mechanism law, and the U-section sub-channels and surface recessed vortices are used to achieve vortex enhancement and significant improvement in heat transfer performance. The research results have been applied in the efficient cooling design of turbine blades for heavy gas turbines and aeroengines in my country, and the internal cooling performance of turbine blades has been significantly improved. He cited 8 representative papers 144 times, including SCI 128 times. The paper collaborators include academicians of the German Academy of Sciences, and the citation authors include academicians of the Russian and China Academies of Sciences, famous American aeroengine heat transfer/cooling researchers, Chairman of the Heat Transfer Committee of the International Gas Turbine Society and other experts in the same field; authorized and applied for 10 national invention patents; Won 1 software copyright, won the Outstanding Paper Award of the International Heat Transfer Academic Conference and the Outstanding Paper Award of the China Aviation Society. The applicant Rao Yu was selected as a member of the Heat Transfer Committee of the International Gas Turbine Society. The research results provide a theoretical basis and design reference for the application of efficient composite cooling technology based on surface recessed vortices to the cooling of high-temperature turbine blades of gas turbines and aeroengines in my country, and have important industrial application value.