预冷条件下高速涡轮发动机气动热力研究  

Aerodynamic and Thermodynamic Study of High Speed Turbine Engine Under Precooled Condition

作　　者：谢培民 袁巍[1] 刘远华 Xie Peimin;Yuan Wei;Liu Yuanhua(School of Energy and Power Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《气动研究与试验》2025年第1期74-83,共10页Aerodynamic Research & Experiment

摘　　要：预冷型涡轮发动机具有用作高超声速飞行器动力装置的应用前景,但目前针对宽速域发动机部件间的匹配关系及气动性能的研究仍有不足。为了实现飞行器速度Ma 0~4、飞行高度0~30km水平起降的目标,以带预冷器的单轴涡喷发动机为研究对象,通过变比热容部件法建立整机稳态气动热力模型,考虑了来流高滞止总温对压气机部件的影响,分析了发动机沿特定爬升轨迹条件下的发动机性能变化规律和调节规律。结果表明,高速飞行时,过高的压气机入口温度易使压气机首级叶片负荷系数过高,后面级负荷系数快速降低,导致压气机增压比不足;采用进气道适度预冷的气动热力方案,可以使压气机维持在较大的折合转速及高效率区间,并降低叶片负荷系数;高空高速巡航状态下,冲压效应显著,加力模式可以改善发动机的热效率;为了使得预冷型发动机的飞行包线更加宽广,组合调节规律可采用压气机进口总温作为主要调节依据。为宽速域航空发动机气动热力方案设计和部件性能参数选择提供可行的参考依据。The pre-cooled engine is promisingly applicated as a dynamic device for hypersonic aircrafts.However,current research on the matching relationships and aerodynamic performance of engine components over a wide speed range is still insufficient.To achieve the goal of horizontal take-off and landing for aircraft with a speed range from O to 4 Mach and a flight height from to 30km,the steady-state aerothermodynamic model of the single-axis turbojet with a precooler is established by variable specific heat component method.The impact on the incoming flow with high stagnation temperature is considered,and the engine characteristics and performance changes along a specific climbing trajectory are analyzed.The results indicate that during high-speed flight,excessively high compressor inlet temperature can lead to excessive load factors on the first-stage blades of compressor,with rapid decreases in load factors for subsequent stages,resulting in insufficient compressor pressure ratio.An aerodynamic and thermodynamic scheme with moderately pre-cooled inlet can make the compressor maintain a high equivalent speed and efficiency range while reducing the blade load factors.In the high altitude and high speed cruising condition,the ram effect is obvious,and afterburner mode can improve the thermal efficiency of the engine.In order to broaden the flight envelope of a precooled engine,the compressor inlet total temperature can be used as the main adjustment parameter of the combination regulation law.This work provides a feasible reference for the aerothermodynamic scheme design and the component performance parameters selection of wide-speed-rangeaero engine.

关 键 词：预冷型涡轮发动机 宽速域 部件法建模 部件特性 性能分析 调节规律 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]