Design of a Triple Combined Cycle Engine

摘要

Combined cycle engine is still the most attractive solution to achieve reusable hypersonic flight with the ability of horizontal takeoff and landing. Compared with the combined engine consists of two sub powers, triple combined cycle engine has wider speed range and is more suitable for hypersonic flight. The interrelationships among sub powers are more complicated, therefore the triple combined cycle engine design is more complex. In order to achieve quick design of triple combined cycle engine, this paper established a parametric method for air-breathing combined cycle engine with wide speed range. The mission requirements were taken as a target in the method. Then installation loss and mass flow matching between the inlet and the engine were considered. This design method is capable of modifying and iterating the design parameters with consideration of the nondeterminacy of the mission profile. In this paper, the design of the triple combined cycle engine was completed and the main design parameters of the engine and the inlet were determined. Analysis of design results showed that the preliminary design was reasonable and feasible. The triple combined cycle engine design method established in this paper is practical and can offer guidance for the design of other combined engines.