Aerodynamic Design and CFD Assessments of a Hydrogen Multistage Axial Compressor

Abstract Hydrogen compression presents unique challenges owing to the properties of hydrogen gas. As the need for energy storage and pipeline transportation network for hydrogen is increasing due to renewable energy transition, an ideal compression solution that could provide a combination of optimum compression ratio at high flow rates would be a giant step forward in hydrogen compression technology. Investigations previously have shown successful applications of centrifugal compressors in achieving required pressure ratios at high tip speeds, however, such compression technologies are limited to low flow rate applications. Axial flow compressors can effectively manage large flow rates in hydrogen; however, they require more stages than axial compressors designed for gases with heavier molecules. To address these challenges, In this paper, A detailed aerodynamic design methodology based on meanline design principles is presented for a multistage hydrogen axial flow compressor. The multistage axial flow compressor is designed for a high flow application and a compressor pressure ratio typical of hydrogen pipeline transportation applications, however with a much lower number of stages, allowing for a reduction in the overall length, and weight of the turbomachine. The presented design methodology uses free vortex design method for spanwise blade profile selection. The aerodynamic performance of the compressor in terms of aerodynamic polytropic efficiency and target pressure ratio is verified using numerical three-dimensional Reynolds Averaged Navier Stokes (3D RANS) CFD simulations. Menter’s SST-K Omega two equation eddy viscosity turbulence model is used for numerical CFD investigations.