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涡轮基组合循环(TBCC)发动机是未来远程高速飞行器和可重复使用双级入轨(TSTO)飞行器第一级运载器的理想动力,而模态转换是实现TBCC发动机工程实用所必须解决的关键技术之一。针对Ma4一级内并联式TBCC发动机,分析了其工作原理,发展了相应的总体性能计算模型,该模型考虑了进气道与发动机的流量匹配关系,改进了发动机模型的迭代求解方法。通过对比涡轮模态与冲压模态的净推力、单位燃油消耗率沿飞行轨迹的变化规律,确定模态转换马赫数为3.0。根据模态转换期间发动机推力、空气流量连续变化的基本要求,提出了一种根据涡轮发动机工作状态分三阶段进行的模态转换策略,确定了模态转换过程的参数调节规律。模态转换动态性能模拟结果表明,基本实现了涡轮模态至冲压模态的平稳转换,但在涡轮发动机加力关闭时,为保证发动机空气流量连续变化,发动机总推力将出现短暂的下降,降幅约为12.5%。
The TBCC engine is the ideal power for the future long-range high-speed aircraft and the first-stage reusable TSTO aircraft, and the modal transformation is the key technology that must be solved to realize the TBCC engine engineering one. In the light of the first-stage parallel TBCC engine in Ma4, its working principle is analyzed, and the corresponding overall performance calculation model is developed. The model takes into account the matching relationship between the inlet flow and the engine flow rate and improves the iterative solution method of the engine model. By comparing the net thrust of the turbine mode and the stamping mode, the variation of unit fuel consumption rate along the flight path, the modal transition Mach number was determined as 3.0. According to the basic requirements of continuous change of engine thrust and air flow during modal transition, a strategy of modal conversion based on three phases of turbine engine operation is proposed, and the law of parameter regulation during modal conversion is determined. The simulation results of the dynamic performance of modal conversion show that the steady conversion from turbine mode to stamping mode is basically achieved. However, when the turbine engine is powered on and off, the total thrust of the engine will decrease for a short time to ensure the continuous change of engine air flow. About 12.5%.