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建立了一种基于爆震波ZND理论和循环分析的PDTE性能计算模型-ZND循环分析模型(模型-1)。将该模型及目前已有的推力壁模型(模型-2)分别与基于实验的PDC特性图模型(模型-3)进行对比,计算了模型PDTE的设计点性能,结果表明:模型-1计算得到的PDTE单位推力(FS)及单位燃油消耗率(sfc)的计算误差较模型-2分别减小了1.75%和4.04%,准确性有所提高。与需要大量实验数据的模型-3相比较,模型-1更简便,可用于PDTE性能的快速评估。应用模型-1计算了飞行状态改变时PDTE性能增益的变化趋势。
A PDTE performance calculation model-ZND cycle analysis model (Model-1) based on the detonation wave ZND theory and cycle analysis was established. Comparing this model with the existing thrust wall model (Model-2) with the experimental PDC-based model (Model-3) respectively, the design point performance of the model PDTE is calculated. The results show that the calculated model-1 The PDTE unit thrust (FS) and the unit fuel consumption (sfc) error of calculation were reduced by 1.75% and 4.04% respectively compared with Model-2, the accuracy was improved. Compared to Model-3, which requires a large amount of experimental data, Model-1 is simpler and can be used for rapid evaluation of PDTE performance. The model-1 is used to calculate the trend of the PDTE performance gain when the flight status changes.