Optimal Design of Hypersonic Turbojet Engines for Two-Stage-to-Orbit Spaceplane

摘要

The Japan Aerospace Exploration Agency has been developing hypersonic (Mach 5+) turbojet engine technologies that are applicable to future two-stage-to-orbit spaceplanes and hypersonic transports. Experimental studies using a 1:10 scale model engine were conducted to acquire data for designing a full-scale practical engine in the next development phase. These experimental data improve the accuracy of an engine performance-prediction tool used at the Japan Aerospace Exploration Agency. This paper presents the most promising engine configuration derived using a multidisciplinary -design-optimization system that includes the newest performance-prediction tool for hypersonic turbojet engines. Quantitative comparison of turbine configurations, thermal protection methods, and fuel types showed that the engine most promising for minimizing the gross takeoff weight of a two-stage-to-orbit spaceplane is a hydrogen-fueled single-spool augmented turbojet with an airflow bypass.