自适应循环发动机快速推力变化过渡过程性能初步研究

As an advanced power device designed for the future flight platforms, the adaptive cycle engine is based on the concept of a variable cycle engine and takes into account various factors such as aircraft-engine integrated design and thermal management to ensure comprehensive performance. This engine drives more variable components to adjust bypass ratio, pressure ratio, gas flow rate and working mode, which can adapt to the complex requirements of different flight missions and obtain performance optimization in a larger flight envelope. Based on the adaptive cycle engine performance model and previous performance researches, this paper puts forward a new transient process to realize rapid thrust change via combined the acceleration/deceleration with operating mode switch transient process and carries out the contrast verification via the performance model. According to acceleration/deceleration and mode switch control schedule design, the rapid thrust change transient process performance analysis on typical working condition is carried out and the related control schedule design method feasibility is verified. Under the subsonic cruise condition, the relative physical speed of low pressure rotor of engine rises up from 0.6 to 1.0 at the minimum angle of the fan on blade of mode M3, leading to the maximum termination thrust growth of 32.4%. Compared with the single mode acceleration and deceleration transient process, the thrust variation range is wider, the acceleration time is shorter, and the rotate speed variation range is smaller.