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Jet Noise Prediction with Eddy Relaxation Source Model

机译:涡流松弛源模型的射流噪声预测

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Previously, a hybrid CFD/CAA approach has been applied for jet noise prediction utilizing a stochastic realization of the Tarn &c Auriault (T&A) and the Tarn, Pastouchenko and Viswanathan (TPV) source models. These models describe two-point cross-correlation functions of a mixing noise source in the jet shear-layer. All input data needed for the modeling can be derived from RANS. The fluctuating acoustic sources are generated stochastically by the Fast Random Particle-Mesh (FRPM) method. For sound propagation a CAA code PIANO is applied with linearized or non-linearized Euler equations in perturbed form. In comparison to measurements, CAA results with the T&A and TPV source models have proven a relatively high accuracy for jet mixing noise prediction of different isolated nozzle configurations (single/dual stream jets, static and forward-flight configuration, hot/cold). On the other hand, recent studies of the authors reveal that alternative source models based on vorticity modeling deliver better noise predictions for the noise generation mechanisms underlying airframe noise problems, i.e. trailing or leading edge noise. Both modeling approaches are well applicable if mixing and airframe noise are regarded separately. However, for instance the study of jet installation effects, where the jet interacts with the trailing edge of an airfoil, require a combination of jet mixing and airframe noise prediction. A common base for both source mechanisms of installed configurations could be provided by the recently proposed Eddy Relaxation source model, which is used to force stochastically the vortical structures in the source region. Based on the relaxation source parameter the coupling can be achieved with variable strength, ranging from entirely prescribed sources to unforced simulation. Two different configurations (single stream jet and jet-flap interaction) in 2-D and 3-D space are currently studied with the eddy relaxation source model. First test computations of these configurations have been performed, which delivered encouraging results.
机译:以前,已使用Tarn&c Auriault(T&A)和Tarn,Pasteouchenko和Viswanathan(TPV)源模型的随机实现,将混合CFD / CAA方法应用于喷气噪声预测。这些模型描述了射流剪切层中混合噪声源的两点互相关函数。建模所需的所有输入数据都可以从RANS派生。波动的声源是通过快速随机粒子网格(FRPM)方法随机生成的。对于声音传播,将CAA代码PIANO与摄动形式的线性化或非线性欧拉方程一起应用。与测量相比,通过T&A和TPV源模型得出的CAA结果已证明在不同隔离喷嘴配置(单/双流喷嘴,静态和正向飞行配置,热/冷)的射流混合噪声预测中具有相对较高的精度。另一方面,作者的最新研究表明,基于涡度建模的替代源模型可为机身噪声问题(即后缘或前缘噪声)背后的噪声生成机制提供更好的噪声预测。如果分别考虑混合和机身噪声,则两种建模方法都适用。但是,例如,对射流与机翼后缘相互作用的射流安装效果的研究,需要将射流混合与机体噪声预测结合起来。最近提出的涡流松弛源模型可以为已安装配置的两种源机制提供一个共同的基础,该模型用于随机地强迫源区域中的涡旋结构。基于松弛源参数,可以以可变强度实现耦合,范围从完全指定的源到非强制模拟。目前,利用涡流松弛源模型研究了二维和三维空间中的两种不同配置(单流射流和射流-襟翼相互作用)。已经对这些配置进行了首次测试计算,得出了令人鼓舞的结果。

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