|
|
|
题名
|
作者
|
年代
|
出处
|
被引量
|
| 1 | Optimization Study of a Coanda Ejector显示文摘Coanda 效果长在太空应用程序被采用了改进各种各样的设备的表演。这效果是流动的能力没有分离,跟随一个弄弯的轮廓并且很好在液体的一口高速度喷气在驱逐者身体从一张嘴出现,跟随弄弯的表面并且拖进驱逐者的第二等的流动的驱逐者被利用了。在 Coanda 驱逐者,第二等的流动由于主要流动动量在驱逐者被拖。到第二等的流动的从主要流动的动量的转移通过狂暴的混合发生并且粘滞效果。第二等的流动然后被拖由狂暴砍当被大狂暴的紧张的坚持在整个驱逐者与主要流动混合时,驱逐者强迫。一个 Coanda 驱逐者的表演主要基于它多好拖第二等的流动和在驱逐者出口在二流动之间混合的数量被学习。现在的学习的目的是在 Coanda 驱逐者表演上调查各种各样的几何参数和压力比率的影响。各种各样的因素的效果,例如,系统性能上的压力比率,主要的嘴和驱逐者配置基于在其它地方定义的一个性能参数被评估了。Coanda 驱逐者的表演强烈取决于主要的嘴配置和压力比率。当它决定第二等的集体流动率的比率到主要集体流动率和混合长度,混合的层生长在优化 Coanda 驱逐者的表演起一个主要作用。关键词 Coanda 驱逐者 - 可压缩的混合层 - 拖的流动 - 混合长度 - 导致的流动 CLC 数字 | H.D.Kim G.Rajesh T.Setoguchi S.Matsuo | 2006 | Journal of Thermal Science2006，15，4： | 6 |
| 2 | Characteristics of the Mach Disk in the Underexpanded Jet in which the Back Pressure Continuously Changes with Time显示文摘When the high-pressure gas is exhausted to the vacuum chamber from the nozzle,the underexpanded supersonic jet contained with the Mach disk is generally formed.The eventual purpose of this study is to clarify the unsteady phenomenon of the underexpanded free jet when the back pressure continuously changes with time.The characteristic of the Mach disk has been clarified in consideration of the diameter and position of it by the numerical analysis in this paper.The sonic jet of the exit Mach number Me=1 is assumed and the axisymmetric conservational equation is solved by the TVD method in the numerical calculation.The diameter and position of the Mach disk differs with the results of a steady jet and the influence on the continuously changing of the back pressure is evidenced from the comparison with the case of steady supersonic jet. | T.Irie T.Yasunobu H.Kashimura T.Setoguchi | 2003 | Journal of Thermal Science2003，12，2： | 3 |
| 3 | Natures of Rotating Stall Cell in a Diagonal Flow Fan显示文摘In order to clarify the natures of a rotating stall cell, the experimental investigation was carried out in a high specific-speed diagonal flow fan. The pressure field on the casing wall and the velocity fields at the rotor inlet and outlet were measured under rotating stall condition with a fast response pressure transducer and a single slant hot-wire probe, respectively. The data were processed using the “Double Phase-Locked Averaging (DPLA)”technique, which enabled to obtain the unsteady flow field with a rotating stall cell in the relative co-ordinate system fixed to the rotor. As a result, the structure and behavior of the rotating stall cell in a high specific-speed diagonal flow fan were shown. | N.SHIOMI K.KANEKO T.SETOGUCHI | 2005 | Journal of Thermal Science2005，14，1： | 2 |
| 4 | Compressible flow characteristics around a biconvex arc airfoil in a channel显示文摘Shock wave-boundary layer interactions(SWBLI)are observed in several practical high-speed internal flows,such as compressor blades,turbine cascades,nozzles and so on.Shock induced oscillations(SIO),aerodynamic instabilities so-called buffet flows,flutter,aeroacoustic noise and vibration are the detrimental consequences of this unsteady shockboundary layer interactions.In the present study,a numerical computation has been performed to investigate the compressible flow characteristics around a 12%thick biconvex circular arc airfoil in a two dimensional channel.Reynolds averaged Navier-Stokes equations with two equation k-ωshear stress transport(SST)turbulence model have been applied for the computational analysis.The flow field characteristics has been studied from pressure ratio(ratio of back pressure,pb to inlet total pressure,p01)of 0.75 to 0.65.The present computational results have been compared and validated with the available experimental data.The results showed that the internal flow field characteristics such as shock wave structure,its behavior(steady or unsteady)and the corresponding boundary layer interaction are varied with pressure ratio.Self-excited shock oscillation was observed at certain flow conditions.Moreover,the mode of unsteady shock oscillation and its frequency are varied significantly with change of pressure ratio. | Md.Abdul Hamid A.B.M.Toufique Hasan S.M.Alimuzzaman S.Matsuo T.Setoguchi | 2014 | Propulsion and Power Research2014，3，1： | 2 |
| 5 | Nozzle geometry variations on the discharge coefficient显示文摘Numerical works have been conducted to investigate the effect of nozzle geometries on the discharge coefficient.Several contoured converging nozzles with finite radius of curvatures,conically converging nozzles and conical divergent orifices have been employed in this investigation.Each nozzle and orifice has a nominal exit diameter of 12.7x10^(-3)m.A 3rd order MUSCL finite volume method of ANSYS Fluent 13.0 was used to solve the Reynolds-averaged Navier-Stokes equations in simulating turbulent flows through various nozzle inlet geometries.The numerical model was validated through comparison between the numerical results and experimental data.The results obtained show that the nozzle geometry has pronounced effect on the sonic lines and discharge coefficients.The coefficient of discharge was found differ from unity due to the non-uniformity of flow parameters at the nozzle exit and the presence of boundary layer as well. | M.M.A.Alam T.Setoguchi S.Matsuo H.D.Kim | 2016 | Propulsion and Power Research2016，5，1： | 1 |
| 6 | A Study of the Critical Nozzle for Flow Rate Measurement of High-Pressure Hydrogen Gas显示文摘用一张批评的嘴的集体流动率测量显示出 inviscid 理论的有效性,显示当雷纳兹数字在理想的煤气的法律下面增加,分泌物系数增加并且来临统一。然而,当批评的嘴测量集体流动时,在一个压力象氢那样的真实气体评价百锁,分泌物系数超过统一,和真实气体效果应该被考虑。现在的学习瞄准用 high-pressured 氢气体调查批评的嘴的流动特征。axisymmetric,可压缩的海军司烧计算被采用模仿批评的嘴流动,和一个充分含蓄的有限的卷方法习惯于 discretize 管理方程系统。真实煤气的效果被模仿考虑分子间的力量,它说明液化氢气体的可能性。计算结果与过去试验性的数据相比。为真实气体的分泌物的系数能在采用真实煤气的假设的统一下面适当地被改正,这被发现了。 | H.D.Kim J.H.Lee K.A.Park T.Setoguchi andong.ac.kr*****Department of Mechanical Engineering Saga University Honjo-machi Saga-shi Saga 840-8502 Japan S.Matsuo | 2007 | Journal of Thermal Science2007，16，1： | 0 |
| 7 | Effect of Duct Geometry on Shock Wave Discharge显示文摘这份报纸描述计算工作理解从管的一个出口排出并且在一个扁平的盘子之上侵犯的一个冲击波的不稳定的流动地。一个扁平的盘子被定位对管的轴下游、正常。在管和扁平的板的出口之间的距离被改变。在现在的学习,二不同的管几何学(即,方形、生气的节) 被模仿在一个冲击波的不稳定的流动上调查管几何学的效果。在计算,减少的全部的变化(TVD ) 计划被采用解决三维,不稳定,可压缩, Euler 方程。计算从 1.05 ~ 1.75 在吃惊马赫数字的范围上被执行。计算结果能预言在扁平的板之上侵犯的冲击波的三维的动态行为。结果获得了吃惊冲击在板上产生的压力增加取决于的表演在管出口和板之间的管几何学和距离,以及吃惊马赫数。为有剖面图的管,对扁平的板起作用的不稳定的负担是更少,这也被发现,与方形的管相比。关键词不稳定的流动 - 可压缩的流动 - 冲击波 - 吃惊冲击 - 管几何学 CLC 数字 O354. | Y.-H.Kweon Y.Miyazato T.Aoki H.-D.Kim T.Setoguchi | 2006 | Journal of Thermal Science2006，15，4： | 0 |
| 8 | Internal Flow Simulation of High-Performance Solid Rockets using a k-ω Turbulence Model显示文摘For technological reasons many high-performance solid rocket motors are made from segmented propellant grains with non-uniform port geometry. In this paper parametric studies have been carried out to examine the geometric dependence of transient flow features in solid rockets with non-uniform ports. Numerical computations have been carried out in an inert simulator of solid propellant rocket motor with the aid of a standard k-ω turbulence model. It was seen that the damping of the temperature fluctuation is faster in solid rocket with convergent port than with divergent port geometry. We inferred that the damping of the flow fluctuations using the port geometry is a meaningful objective for the suppression and control of the instability and/or pressure/thrust oscillations during the starting transient of solid rockets. | V.R.SANAL KUMAR H.D.KIM B.N.RAGHUNANDAN T.SETOGUCHI S.RAGHUNATHAN | 2005 | Journal of Thermal Science2005，14，2： | 0 |
| 9 | Performance estimation of bi-directional turbines in wave energy plants显示文摘基于的波浪精力种的震荡的水列(OWC ) 为把灵魂力量变换成柄力量与双向汽轮机的几种类型被设计了。有连接指南翼和固定指南翼的推动汽轮机在印度波浪精力植物被测试了。这在有井鈥檚 汽轮机的起始的试验以后。与有一个线性抑制特征的井鈥檚 汽轮机相对照,推动汽轮机有非线性的抑制。这在全面精力变换有重要效果从向电线招手。优化波浪精力植物与在大量流动系数上的线性抑制和好效率要求一台汽轮机。这个工作描述如此的一个图案怎么能用固定指南翼推动汽轮机被做。印度波浪精力植物被用作案例研究。 | S.Anand V.Jayashankar S.Nagata K.Toyota M.Takao T.Setoguchi | 2007 | Journal of Thermal Science2007，16，4： | 0 |
| 10 | The Effect of Reflector with Sound-Absorbing Material on Supersonic Jet Noise显示文摘This paper describes an experimental work to investigate the effect of a reflector on supersonic jet noise radiated from a convergent-divergent nozzle with a design Mach number 2.0. In the present study, a metal reflector and reflectors made of three different sound-absorbing materials (grass wool and polyurethane foam) were employed,and the reflector size was varied. Acoustic measurement is carried out to obtain the acoustic characteristics such as frequency, amplitude of screech tone and overall sound pressure level (OASPL). A high-quality schlieren optical system is used to visualize the detailed structure of supersonic jet. The results obtained show that the acoustic characteristics of supersonic jet noise are strongly dependent upon the jet pressure ratio and the reflector size. It is also found that the reflector with sound-absorbing material reduces the screech tone amplitude by about 5-13dB and the overall sound pressure levels by about 2-5dB, compared with those of the metal reflector. | Y.-H.KWEON M.TSUCHIDA Y.MIYAZATO T.AOKI H.-D.KIM T.SETOGUCHI | 2005 | Journal of Thermal Science2005，14，1： | 0 |
| 11 | A Study of the Weak Shock Wave Propagating over a Porous Wall/Cavity System显示文摘现在的计算学习探讨在管宣传的冲击波的变细,用一个多孔的墙 / 洞系统。在现在的学习,在多孔的墙 / 洞系统上宣传的一个弱冲击波与计算液体动力学被调查。A 总数变化减少计划被采用解决不稳定,二维,可压缩,海军司烧方程。一个起始的冲击波的马赫数字从 1.02 ~ 1.12 在范围被改变。多孔的墙 / 洞系统的几种不同类型被测试调查被动控制效果。结果证明墙压力强烈在事件冲击波后面由于衍射和冲击波的思考过程波动。从结果,为隧道推动波浪的有效缓和,穿孔区域的长度应该足够地长,这被理解。关键词可压缩的流动 - 穿孔的墙 - 铁路隧道 - 冲击波 CLC 数字 O354. | H.D.KIM S.J.JUNG T.AOKI T.SETOGUCHI | 2005 | Journal of Thermal Science2005，14，4： | 0 |
您所在的机构暂未开通此部分的功能，请联系管理员