In order to achieve the core engine with high performance parameters and high-tech equipment

based on the ideas of structural fusion and thermal process fusion

the core engine of traditional micro-turbine was integrated through innovation. Based on the 3D printing design and manufacturing technology foundation

a double-sided composite impeller structure was designed

with a radial connection of a double-sided conventional impeller and an axial-flow turbine

making it possible to become a type of high-efficiency impeller with great potential in the future. Specifically

the principle

structural scheme and expected performance of the micro gas turbine were analyzed. Numerical investigation of aerodynamic compression performance of a double-sided composite impeller and backward pipe heat transfer characteristics was primarily studied. Results show that compared with the conventional impeller

the aerodynamic compression performance of the double-sided composite impeller can meet the expectation perfectly. The total pressure ratio

flow rate and isentropic efficiency have been greatly improved; the recovery of 4.4 K exhaust gas temperature in the rear intake pipe can improve the thermal efficiency. It has laid the foundation for the development of gas turbines with high aerodynamic performance and high cycle parameters.