Conceptual design of axial flow gas turbines for helium-cooled reactors

The conceptual design tools for axial flow gas turbines were developed using mean-line analysis and meridional flow analysis methods. And it is validated by comparing with the turbomachinery design data of MPBR designed by the industry design tool. The conceptual design tools have ability to produce design point performance within the range of ±1% error comparing with the reference. It turns out that the high-pressure compressor and the high-pressure turbine consist of 8 stages and 4 stages. The analysis of the off-design of gas turbines show that constant speed lines are not steep as the mass flow increases mainly due to the high sonic velocity of helium and low flow coefficient, and the efficiency of the high-pressure is relatively constant over the wide range of pressure ratio. The results of the scaling analysis with 1/2 scale-down gas turbines indicate that the effects of the non-dimensional mass flow and the non-dimensional speed are stronger than the effect of the Reynolds number in subsonic flow regime