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针对水冷包层子模块并行通道的流量分配对热量导出的影响,以水冷包层子模块第一壁为研究对象,对其并行通道试验段的模化设计与流量分配特性展开了研究。采用模化方法对第一壁的结构进行设计,得出试验段相关参数。采用计算流体力学(CFD)的方法对模化设计的试验段进行数值模拟,并分析其流动状态。将结果与原型结构下的流动特性参数进行比较,验证了采用模化方法得到的试验段参数可以有效反映水冷包层子模块第一壁的流动特点,为试验装置的搭建提供参考。     

水冷包层模块局部模型流量分配数值模拟

用JAEA 水冷包层(WCSB)模块侧壁的流量分配实验验证了SST 湍流模型,建立了水冷包层模块第一壁的数值分析模型,研究了第一壁各冷却管中的流量分配情况。分析结果发现,第一壁模型入口集管中存在复杂的流动行为,冷却剂可以明显的区分为主流和逆流两大部分,其中主流进入冷却管的位置是影响流量分配的主要因素,逆流区形成了一系列次级涡流和沿管壁的环向流动。分析结果表明,在第一壁模型中,在所以条件下,各冷却剂通道中存在流量分配不均匀现象,流速最大值与最小值偏差均小于2%。     

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用JAEA水冷包层(WCSB)模块侧壁的流量分配实验验证了SST湍流模型,建立了水冷包层模块第一壁的数值分析模型,研究了第一壁各冷却管中的流量分配情况。分析结果发现,第一壁模型入口集管中存在复杂的流动行为,冷却剂可以明显的区分为主流和逆流两大部分,其中主流进入冷却管的位置是影响流量分配的主要因素,逆流区形成了一系列次级涡流和沿管壁的环向流动。分析结果表明,在第一壁模型中,在所以条件下,各冷却剂通道中存在流量分配不均匀现象,流速最大值与最小值偏差均小于2%。     

高增益包层冷却系统设计及初步热工水力分析北大核心CSCD

高增益包层氚增殖率能够达到1.5以上,能量放大倍数约为5,包层燃料区平均功率达50MW/m3,针对包层存在高功率密度区的这一特点,设计了采用迂回流动方案的水冷系统,主要由内嵌冷却管和汇总分流腔组成。建立了包括第一壁和燃料区的包层三维热工水力计算模型,利用CFD程序FLUENT对冷却系统进行模拟分析,研究了稳态工况条件下包层关键区域的整体热工水力特性。结果表明,该水冷系统流量分配合理,燃料区冷却剂压降为102kPa,出口温度为594K,符合设计预期。包层温度分布结果表明各区域最高温度均满足限值要求,冷却系统能够有效载出包层内裂变反应释放的热量。     

高增益包层冷却系统设计及初步热工水力分析

高增益包层氚增殖率能够达到1.5以上,能量放大倍数约为5,包层燃料区平均功率达50 MW/m3,针对包层存在高功率密度区的这一特点,设计了采用迂回流动方案的水冷系统,主要由内嵌冷却管和汇总分流腔组成。建立了包括第一壁和燃料区的包层三维热工水力计算模型,利用CFD程序FLUENT对冷却系统进行模拟分析,研究了稳态工况条件下包层关键区域的整体热工水力特性。结果表明,该水冷系统流量分配合理,燃料区冷却剂压降为102 kPa,出口温度为594 K,符合设计预期。包层温度分布结果表明各区域最高温度均满足限值要求,冷却系统能够有效载出包层内裂变反应释放的热量。     

TBM子模块冷却剂流量分析及结构改进设计

采用计算流体软件FLUENT对国际热核聚变实验堆(ITER)实验包层模块(TBM)的子模块冷却剂流量分配进行三维数值模拟。结果表明,原有子模块冷却管道内氦气流量分配具有严重的不均匀性,导致冷却剂传热效率降低。为此,在对冷却剂流量进行三维数值模拟的基础上对相应的结构做了合理的改进设计,保证了实验包层模块及ITER的安全运行。     

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基于ITER装置窗口C,完成了中国氦冷固态增殖剂试验包层模块的设计改进,给出了模块主要性能参数和设计参数。改进后的TBM包层模块外围尺寸为环向484mm、纵向1660mm和极向675mm。根据该模块设计的结构特点,对研制用材料CLF-1钢真空扩散连接和真空电子束焊等关键工艺进行了研究,初步探索了第一壁等关键部件的研制工艺流程,并最终成功试制了第一壁和子模块冷却板模拟件。     

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通过对HCSB-DEMO示范堆包层子模块进行热工水力及中子学的迭代计算及优化,得到了第一壁、包层子模块在单独冷却下满足要求的结构布局。材料温度均已低于限值,冷却剂出口温度达到了500℃,冷却剂压降也符合工程上的要求,同时TBR在不考虑格架等复杂结构的情况下达到了1.30。结合得到的结构布局对第一壁、包层子模块共同冷却情况进行了讨论,鉴于第一壁是具有高热负载的特殊部件,建议工程上采用单独冷却方式进行冷却。     

U型并联多通道中流量分配特性

高增益包层并联多通道流量分配特性直接影响其传热效率,在初始设计中,缺少简洁有效的设计方法。采用Fluent程序对U型布置并联多通道的流量分配特性进行数值模拟,通过敏感性分析,确定了影响流量分配特性的支管长度、支管横截面积、支管个数以及总管横截面积等重要参数,提出了预估流量分配特性的方法。分析表明,无量纲参数Kfd越低,流量分配越均匀；当Kfd低于0.03时,流量丧失比低于5%。     

U型并联多通道中流量分配特性

高增益包层并联多通道流量分配特性直接影响其传热效率,在初始设计中,缺少简洁有效的设计方法。采用Fluent程序对U型布置并联多通道的流量分配特性进行数值模拟,通过敏感性分析,确定了影响流量分配特性的支管长度、支管横截面积、支管个数以及总管横截面积等重要参数,提出了预估流量分配特性的方法。分析表明,无量纲参数Kfd越低,流量分配越均匀;当Kfd低于0.03时,流量丧失比低于5%。     

Failure of the Ingard-Myers boundary condition for a lined duct: an experimental investigation

This paper deals with experimental investigation of the lined wall boundary condition in flow duct applications such as aircraft engine systems or automobile mufflers. A first experiment, based on a microphone array located in the liner test section, is carried out in order to extract the axial wavenumbers with the help of an "high-accurate" singular value decomposition Prony-like algorithm. The experimental axial wavenumbers are then used to provide the lined wall impedance for both downstream and upstream acoustic propagation by means of a straightforward impedance education method involving the classical Ingard-Myers boundary condition. The results show that the Ingard-Myers boundary condition fails to predict with accuracy the acoustic behavior in a lined duct with flow. An effective lined wall impedance, valid whatever the direction of acoustic propagation, can be suitably found from experimental axial wavenumbers and a modified version of the Ingard-Myers condition with the form inspired from a previous theoretical study [Aure?gan et al., J. Acoust. Soc. Am. 109, 59-64 (2001)]. In a second experiment, the scattering matrix of the liner test section is measured and is then compared to the predicted scattering matrix using the multimodal approach and the lined wall impedances previously deduced. A large discrepancy is observed between the measured and the predicted scattering coefficients that confirms the poor accuracy provided from the Ingard-Myers boundary condition widely used in lined duct applications.     

Turbulent boundary layer over a flat plate with uniform wall suction

A complete theory of turbulent boundary layer flow over a flat plate with uniform wall suction is proposed. The theory relies on an asymptotic analysis of the Reynolds equations and dimensional considerations and does not involve any special closure hypotheses. Characteristics of the turbulent boundary layer with suction are calculated for the entire range of flow parameters by using the known characteristics of a reference flow (turbulent boundary layer over an impermeable flat plate). The velocity and shear stress profiles, the distribution of skin friction along the plate, and integral flow characteristics are obtained by using only the known velocity profile in the reference flow. The normal Reynolds stresses are calculated by using analogous characteristics of the reference flow. Results are presented in terms of scaling variables.     

Slat noise modeling and prediction

This paper presents a model for aircraft slat noise prediction, based on the theory of aerodynamic sound generation and the first principles of source flow physics. Starting from the theory of acoustic analogy, the noise from the high Reynolds number and low Mach number flows in the slat cove region is formulated as a general solution by the method of dimensional analysis, far-field asymptotic expansion and statistical modeling. The solution relates the far-field noise spectrum to the surface pressure statistics, the characteristic length and time scales in the surface pressure statistics and Green's function that accounts for the sound-flow coupling and propagation effects. The general solution is then used to extract scaling laws and correlation models for the individual functional dependences between the far-field noise and various parameters, including the slat noise spectral shape, its Mach number dependence and its far-field directivity. The simple scaling laws and correlation models are validated by test data and serve as building blocks to construct a slat noise prediction model.     

Investigation of airframe noise for a large-scale wing model with high-lift devices

The acoustic characteristics of a large-scale model of a wing with high-lift devices in the landing configuration have been studied in the DNW-NWB wind tunnel with an anechoic test section. For the first time in domestic practice, data on airframe noise at high Reynolds numbers (1.1–1.8 × 10⁶) have been obtained, which can be used for assessment of wing noise levels in aircraft certification tests. The scaling factor for recalculating the measurement results to natural conditions has been determined from the condition of collapsing the dimensionless noise spectra obtained at various flow velocities. The beamforming technique has been used to obtain localization of noise sources and provide their ranking with respect to intensity. For flap side-edge noise, which is an important noise component, a noise reduction method has been proposed. The efficiency of this method has been confirmed in DNW-NWB experiments.     

Detonation in a Three-Dimensional Elbowed Channel

The results of simulation of detonation in a curved three-dimensional channel with a circular cross section of constant width blown through by a supersonic flow of a stoichiometric propane?air mixture are presented. In the bending zone, the channel wall was toroidal. The study was carried out within the framework of the one-stage combustion kinetics by the numerical method based on Godunov’s scheme in the original software package developed for multiparameter calculations and visualization of flows. The initiation of detonation occurs as a result of the formation of the shockwave configurations associated with the flow turn in the channel. Unsteady flow patterns are obtained, and their dependence on the parameters of the problem is investigated. The flow regime without detonation, the mode with the detonation wave emerging from the channel through the input cross section, and the mode with steady detonation are obtained.     

基于涡流发生器的风洞试验段附面层控制数值模拟

沿试验段侧壁发展的附面层是影响飞行器半模型实验数据精准度的主要因素之一.利用数值模拟方法验证了涡流发生器减小附面层影响的可行性,重点分析了安装角度、结构尺寸、安装位置及个数等设计参数对附面层内速度分布的影响规律,对涡流发生器尾涡强度以及沿流向的发展规律进行了初步探讨.结果表明,涡流发生器产生的尾涡能够有效改善附面层内的速度分布,进而减小附面层厚度,降低附面层影响;涡流发生器的后缘应略高于当地附面层厚度,安装角度、位置、个数等参数必须合理设计以减小涡流发生器对试验段主气流的影响.基于计算结果初步设计了可用于2.4 m跨声速风洞半模试验段的涡流发生器,在亚声速范围内能够减小模型区侧壁附面层厚度66%左右,对核心流Mach数影响小于0.003,为涡流发生器的实际应用提供了依据.      

水陆两栖飞机静水面高速滑行性能数值计算与试验分析

针对水陆两栖飞机静水面高速滑行过程的运动响应大、流场强非线性等问题，提出了一种基于传统动网格技术的"状态预估——精确计算"的数值模拟方法:通过求解Reynolds平均N-S方程结合运动方程来模拟飞机静水面滑行时的流场特征和运动特性，数值模拟方法为隐式有限体积法，湍流模型采用k-ω（SST Menter）结合壁函数进行处理，自由液面捕捉采用VOF方法；数值计算时，首先采用粗网格对简化后的飞机在不同航速下的姿态和升沉进行快速预估，再将飞机置于预估状态下进行精确网格划分，最后进行精确数值计算分析.为了验证数值模拟结果的正确性，在物理水池中进行了静水拖曳试验，将数值计算结果与试验结果进行对比分析可得:数值计算与水池试验的流场特征吻合，且阻力、姿态和升沉的计算精度达到90%，验证了数值模拟方法的可行性.