Ma4内并联TBCC发动机匹配设计与模态转换性能分析

由于发动机自身工作能力的限制,要想获得最大的发动机性能,在不同的飞行马赫数下,对应不同的发动机形式,因此为了达到宽马赫数飞行的目的,在不同工作区间采用不同发动机进行工作的组合循环发动机应运而生。涡轮基组合循环发动机(TBCC)作为组合动力的一种,采用涡轮发动机与冲压发动机组合的形式,可以在未来作为远程高速飞行器和可重复使用2级入轨(TSTO)飞行器的第1级动力,有广阔的使用前景。作为宽速域内工作的 TBCC,模态转换是实现 TBCC 发动机宽马赫数工作必须解决的关键技术问题之一。针对Ma4 速域 TBCC 发动机,建立了相应的涡轮发动机与亚燃冲压发动机并联模型,通过考虑2种发动机的设计点与非设计点工作条件,对模态转换马赫数进行了选择,并基于保持固定流量这个前体条件,给出了相应的并联TBCC 模态转换控制过程。基于建模并联模型,初步确定了采用涡轮与亚燃冲压动力的 TBCC 发动机的可行性,在合适的匹配条件下,TBCC 组合动力可以满足飞行器的推力需求。

Processing Analysis of Matching Design and Mode TransitionPerformance for a Ma4 Over-under TBCC Engine

Because of constraint of the power device,the best engine performance for the supersonicaircraft can be obtained by employing different engine during the different flight operation domains.The Combined-Cycle Engine is emerged for the aircraft operating in the widely flight Mach number.The ''Turbine-Based Combined-Cycle Engine is one of the Combined-Cycle Engine ,it could use to thefutuure long-range high-speed vehicle and the first stage of Two-Stage-To-0rbit reusable launch vehicle which has broad application prospects, Mode transition from the low-speed propulsion system to thehigh-speed propulsion systme is one of the most critical ''TBCC enabling technologies. In this paper ,themodelingof a ''Turbine-Based Combined-Cycle Engine which is formed by a turbine engine and a ramjet engine is built to use for Ma4 supersonic aircraft. By considering and calculating the design point andnon design point of the two engines , the mode transition is designed under the constant flow rate of in-coming flow and its control law is obtained. Based on the the TBCC model,it is sure that the TBCCcomposed of turbine and ramjet is workable and it could meet the thrust demands of the aircraft.