中文摘要：

为了阐明进气预冷膨胀式空气涡轮火箭发动机在最大状态下的部件匹配规律和性能特点,基于ε—NTU法建立了换热有效度随工况改变的预冷器模型,完成了氢燃料发动机的性能仿真与分析。增大涡轮前压力、燃料流量,同时减小尾喷管喉道和出口面积,可实现压气机工作点沿等物理转速线由堵塞区向喘振边界移动,压气机压比及燃空比均增大。在此过程中,发动机若在低马赫数工作,尾喷管内燃气总压、总温升高使推力增大;在近堵塞区域,压比迅速增大导致比冲上升;在近喘振区域,压比增大减缓,燃空比的上升导致比冲下降。若在高马赫数工作,高温米流使压气机工作于低折合转速区域,工作点在等物理转速线上由堵塞区向喘振边界移动时,燃空比增加补偿了空气流量下降导致的推力衰减,总推力基本保持不变;由于低折合转速下压比增大减缓,增大的燃空比使比冲下降。

英文摘要：

In order to present the component matching and the performance features for air turbo ramjets expander（ATREX） at maximum rotation speed within the compressor blade material limit,a hydrogen fuel ATREX engine is simulated and analyzed using a precooler model based on ε-NTU method that considers the variation of effectiveness at off-design conditions.The operation for the compressor from choking toward surge at a constant rotation speed can be achieved by increasing the turbine inlet pressure and fuel mass flow rate but however reducing the nozzle throat and exit area,the compressor pressure ratio and fuel-air ratio increase.During this operation process,at low flight Mach numbers,the engine thrust increases with the increase of the nozzle inlet total pressure and temperature;as compressor operation point moves upward from the choking,the engine specific impulse increases because the compressor pressure ratio increases rapidly in this area;as compressor operation point moves to the surge line,the engine specific impulse decreases with the increase of fuel-air ratio because the increase of compressor pressure ratio slows down in this area.At high flight Mach numbers,the compressor operates in low corrected speed area because of the high temperature free stream,as the operation point moves from the choking to surge line,although the air mass flow rate decreases,the engine thrust is almost unchanged because of the increase of fuel-air ratio;since the compressor pressure ratio increases slowly in low corrected speed area,the engine specific impulse decreases with the increase of fuel-air ratio.