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基于部件匹配技术的大涵道比涡扇发动机性能仿真模型和平行压气机模型耦合,实现了可以定量分析压力畸变影响的性能仿真程序。以某大涵道比涡扇发动机为例,开展了压力畸变对其压缩部件(风扇、增压级、高压压气机)的喘振边界、共同工作线、喘振裕度以及发动机推力、耗油率的影响仿真。计算结果表明,压力畸变对喘振裕度的影响主要是使压缩部件喘振边界下移,其共同工作线由于存在压力畸变会产生偏移,但其量级较小。对于大涵道比涡扇发动机,压力畸变对风扇外涵喘振裕度影响最大,对风扇内涵/增压级影响次之,对高压压气机影响最小;压力畸变同时会造成发动机推力下降、耗油率上升。
Based on the component matching technology, a large-bypass ratio turbofan engine performance simulation model and a parallel compressor model are coupled to realize a performance simulation program that can quantitatively analyze the influence of pressure distortion. Taking a large bypass turbofan engine as an example, the surge boundary, common working line, surge margin, engine thrust and fuel consumption of the compression components (fan, supercharger, high pressure compressor) Rate of impact simulation. The calculation results show that the effect of pressure distortion on the surge margin is mainly that the compressive part surges downwards and that the common working line will be offset due to the pressure distortion, but its magnitude is small. For large bypass ratio turbofan engines, the pressure distortion has the greatest effect on the fan outer margin surge margin, which has the lowest impact on the fan connotation / supercharging stage and the least impact on the high-pressure compressor. The pressure distortion will also cause the engine thrust to decrease and the consumption The oil rate goes up.