Consideration of Internal Flow Network for Small Supersonic Aerospace Engine

Abstract

Internal flow of an engine for a supersonic aircraft is complicated path with merge and branch. In the previous research, we have tried to build 1-D internal flow network to grasp and evaluate internal flow conditions. We also conducted cold run tests to investigate pressure, temperature and rotor vibration of the engine. Improvement of prediction accuracy of internal flow rate of each paths and making appropriate flow direction are required for the engine test driven by hot gas in the future. In this study, the design concepts for improvement of the internal flow network built in the previous report and the investigation progress of the internal flow is reported.