Based on the successful experience of applying low-speed modeling technology to high pressure compressor of aero-engine

the aerodynamic design method of turbine with similar technology was investigated

and an improved blade redesign method was illustrated.Referring to an adjusted similarity principle

a low-speed turbine research facility was established

which was aerodynamically and thermally represented by the first stage of prototype high pressure turbine of E3 core.In the design process

identical structural parameters between the prototype and the expected facility

such as solidity

span-to-chord ratio

and tip clearance-to-span ratio

were assured while similar aerodynamic performance was verified;besides

acceptable similarity of non-dimensional blade surface isentropic Mach number distribution was ascertained.Numerical simulation results shows that flow coefficient and blade surface pressure distribution are not suitable in the modeling of turbine for the distinction of total pressure and total temperature.According to the similarity parameters

the modeling shows a good correspondence in aerodynamic performance

proving that the low-speed facility will provide an appropriate test platform for aerothermodynamics research of turbine.