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高频不稳定燃烧一直是液体火箭发动机研制过程中所要面临的重大难题之一.采用具有低色散低耗散特点的计算气动声学方法,对自燃推进剂变轨发动机(OME)的高频不稳定燃烧进行时域下的数值仿真.由Crocco的压力时滞模型对燃烧热释放和声波之间的耦合进行模拟,并对不同的时滞模型参数对稳定性结果的影响进行了分析,给出发动机的稳定性极限图,确定一阶切向及一阶径向振型为主的不稳定振型,与地面试车实验捕捉到的不稳定振型相一致.结果表明:采用计算气动声学方法对带有Crocco压力时滞模型的声波扰动方程进行时域下的数值求解,可以对发动机的高频不稳定燃烧进行成功地预测.
High-frequency unstable combustion has always been one of the major challenges in the development of liquid propellant rocket engines.Using a computational aeroacoustics method with low dispersion and low dissipation, the high frequency instability of OME Combustion is carried out in the time domain numerical simulation.The Crocco pressure delay model is used to simulate the coupling between combustion heat release and acoustic wave and the influence of different time delay model parameters on the stability results is analyzed. , The first-order tangential and first-order radial modes are determined, which is consistent with the unsteady modes captured by the ground test. The results show that the aerodynamic acoustics The acoustic perturbation equation with Crocco pressure delay model is numerically solved in the time domain, which can successfully predict the high-frequency unstable combustion of the engine.