摘要
为了研究复燃对火箭发动机射流声场的影响,建立了一个可以计算火箭发动机射流复燃流场和声学特性的模型:采用DES湍流模型模拟湍流流动;有限速率化学反应模型模拟固体火箭冲压发动机射流的复燃;以基于FW-H方程的声类比方法分析了分析射流噪声。以2个典型算例进行了验证性模拟计算,并与文献中计算结果进行了对比,表明本文所采用的算法在计算射流流场二次燃烧和噪声预测的可靠性。分析了冻结流和化学非平衡流两种工况下的流场特性和声学特性。计算结果表明:当考虑燃烧时,在整体上总声压级有所增大,特别是在角度为0~30°方向上有所增加,相差最大可达6dB。
In order to study the influence of after-burning on the rocket engine jet acoustic field,a model which can be calculated the combustion flow-field and the acoustic properties is established.DES turbulence model are adopted to simulate the turbulent flow;Finite rate chemical reaction model simulation of the solid rocket engine jet;acoustic analogy method based on FW-H equation is used to analyze the jet noise.Two typical examples are calculated to verify simulation calculation.The results are compared with the literature,and show that the algorithm used in this paper is reliable in the calculation of jet flow field structure,combustion and noise prediction.The flow field characteristics and acoustic characteristics of frozen flow and chemical non-quilibrium flow are analyzed.Calculation results show that:when combustion is considered,the total sound pressure level increases,especially in the angle of 30°to 60°,and the maximum difference is 6dB.
作者
马丽璇
李恩义
MA Li-xuan;LI En-yi(Anyang Institute of Technology,Flight Collogy,Anyang 455000,China)
出处
《内燃机与配件》
2020年第24期27-30,共4页
Internal Combustion Engine & Parts
