Design of a Scramjet Engine Supply System Using Transient Analysis

抄録

A quasi-transient simulator called Hypersonic Engine Dynamic Simulator (HEDS) was developed for the purpose of analyzing the transient behavior of the scramjet engine system. However, the transient analysis along the flight profile could not be performed with HEDS. In this study, an inlet performance calculation model and a quasi-one-dimensional analytical model for hydrocarbon fueled combustor were introduced into HEDS. In order to confirm the response of the fuel supply system with the improved HEDS, the transient analysis along one flight profile was performed. The engine model used in the transient analysis was based on n-dodecane as fuel and electric pump cycle as engine cycle. In addition, the behavior of the engine system due to the control was also studied by comparing the uncontrolled and sequence-controlled cases. As a result, when hydrocarbon fuels were used, a sudden decrease in fuel flow rate was observed around the critical point. Therefore, it was necessary to control the fuel flow rate so that it does not fall into a state near the critical point. In addition, the fuel flow rate was controlled to increase by two methods: increasing the pump speed and dumping the fuel. These two methods showed different characteristics to the engine system. Using the dynamic simulator to analyze the behavior of the engine system during the flight profile was effective for considering the engine system and developing control methods.