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着眼于建立一套性能分析工具,可用于高超声速飞行器串联式涡轮/冲压组合动力装置总体方案的性能评估及设计约束条件分析。为了满足飞行器从起飞到飞行马赫数5宽广飞行包线内对动力装置性能的苛刻要求,所研究的组合发动机通过调整五个可调机构再加涡扇冲压燃油调节来实现变循环概念。该工具采用一维气动热力分析技术,使用了经试验验证的各部件特性,同时考虑了气体的变比热性质。通过采用面向对象的程序设计方法,该工具提供了一个性能仿真平台,可供涡扇工作模式,冲压工作模式,涡扇/冲压模式转换过程的热力循环分析,非设计点性能分析,控制规律研究等。借助于该工具,涡扇模式及冲压模式的热力循环分析结果表明,回流裕度是涡扇模式循环参数选择中需要重点考虑的因素;高的冲压燃烧室出口温度有利于提高冲压发动机的循环性能。
Focusing on the establishment of a performance analysis tool, it can be used to evaluate the performance and design constraints of the overall scheme of the HPS tandem turbine / ram combination power plant. In order to meet the stringent requirements for power plant performance in a wide flight envelope from take-off to flight Mach 5, the combined engine studied was designed to achieve a variable cycle by adjusting five adjustable mechanisms plus turbo-charged fuel regulation. The tool uses one-dimensional aerodynamic thermodynamics, using the tried-and-tested features of each part, taking into account the variable specific heat properties of the gas. By using an object-oriented programming approach, the tool provides a performance simulation platform for the analysis of the thermal cycle of the turbofan operating mode, the ram working mode, the turbofan / ram mode conversion process, the non-design point performance analysis and the control law Wait. With the help of this tool, the results of thermodynamic cycle analysis of the turbofan mode and the stamping mode show that the backflow margin is the key factor to be considered in the selection of the circulation parameters of the turbofan mode. The high outlet temperature of the ramjet can improve the cycle performance of the ramjet .