A Preliminary Flow Path Design Tool for Advanced Aero-Engine

A flow path design tool for the advanced aero-engine is developed, which contains the mean-line design model for rotating components and the size design models for non-rotating components including the annular S-shape duct, combustor, splitter, nozzle and the Variable Area Bypass Injector (VABI). The rotating component mean-line model could obtain the component pressure ratio, efficiency, and flow path size. Validation calculations are performed using the developed tool for the PW Energy Efficient Engine (E3) rotating components. The results show that the calculated maximum deviation of the rotating components’ flow path size and performance parameters are less than 7.8% and 3.3%, respectively. Based on the developed tool, a comparative flow path design of the Variable Cycle Engine (VCE) with Core Drive Fan Stage (CDFS) and the VCE with Variable Fan Stage (VFS) is performed with the aid of the genetic algorithm. On the premise of the pressure ratios of the two VCEs’ compression components are almost the same, due to the CDFS on the high-pressure spool, the high-pressure spool rotational speed (NH) of VCE with CDFS is 6800r/min and the NH of VCE with VFS is 8000 r/min. Compared to the VCE with VFS, the stage number of the high-pressure compressor and high-pressure turbine of the VCE with CDFS has increased by 2 and 1, respectively, the HPC average aerodynamic loading coefficient is increased by 8.7%.