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采用非周期 C 型网格模拟透平叶栅跨音流场 被引量:1
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作者 陈铁 刘仪 +2 位作者 刘斌 冯斌 吴其林 《汽轮机技术》 北大核心 1997年第5期278-281,305,共5页
通过求解椭圆方程技术来调整网格正交性和边界附近网格距离来生成非周期C型网格。周期边界采用物理参数双线性插值,结合矢通量分裂隐式差分格式对RD叶栅跨音流场进行了无粘数值模拟,结果表明非周期C型网格比周期H型网格可以更细... 通过求解椭圆方程技术来调整网格正交性和边界附近网格距离来生成非周期C型网格。周期边界采用物理参数双线性插值,结合矢通量分裂隐式差分格式对RD叶栅跨音流场进行了无粘数值模拟,结果表明非周期C型网格比周期H型网格可以更细致地模拟叶型头部区域流场,而且可以更准确地捕获激波。该网格系统有效地改善了网格正交性,加密比较自由,对透平叶栅数值模拟具有很好的发展前途。 展开更多
关键词 透平叶栅 跨音流场 非周期C型网格 汽轮机
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用四阶Runge-Kuta法和TVD格式求解两维跨超音流场
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作者 王尚锦 倪明玖 席光 《航空动力学报》 EI CAS CSCD 北大核心 1995年第3期221-224,共4页
利用坐标转换给出两维任意曲线坐标系下雅可比矩阵特征值、特征向量及Harten型TVD格式的详细表达式,并结合四阶Runge-Kuta法发展了一种新的、有效的求解超音、跨音流场的算法。数值计算表明,本文的方法可有效地求... 利用坐标转换给出两维任意曲线坐标系下雅可比矩阵特征值、特征向量及Harten型TVD格式的详细表达式,并结合四阶Runge-Kuta法发展了一种新的、有效的求解超音、跨音流场的算法。数值计算表明,本文的方法可有效地求解跨音流场。 展开更多
关键词 TVD格式 欧拉方程组 跨音流场 气体动力学
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一种新的隐格式构造及在跨音流动中的应用
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作者 刘仪 曹春丽 刘斌 《力学与实践》 CSCD 北大核心 1996年第2期51-53,共3页
本文提出了一种任意曲线坐标系下的Navier-Stokes方程组的隐式矢通量分裂格式的构造方法.该方法避开了近似因子分解、无矩阵运算,具有精度高、稳定性好、计算量少等优点.在扩压器进气道跨音流场的计算中,准确地捕获了... 本文提出了一种任意曲线坐标系下的Navier-Stokes方程组的隐式矢通量分裂格式的构造方法.该方法避开了近似因子分解、无矩阵运算,具有精度高、稳定性好、计算量少等优点.在扩压器进气道跨音流场的计算中,准确地捕获了激波,与实验比较,结果令人满意. 展开更多
关键词 隐格式 数值计算 跨音流场 激波
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Numerical Analysis of the Tip Leakage Flow Field in a Transonic Axial Compressor with Circumferential Casing Treatment 被引量:7
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作者 G.Legras N.Gourdain I.Trebinjac 《Journal of Thermal Science》 SCIE EI CAS CSCD 2010年第3期198-205,共8页
This paper reports on numerical investigations aimed at understanding the influence of circumferential casing grooves on the tip leakage flow and its resulting vortical structures.The results and conclusions are based... This paper reports on numerical investigations aimed at understanding the influence of circumferential casing grooves on the tip leakage flow and its resulting vortical structures.The results and conclusions are based on steady state 3D numerical simulations of the well-known transonic axial compressor NASA Rotor 37 near stall operating conditions.The calculations carried out on the casing treatment configuration reveal an important modification of the vortex topology at the rotor tip clearance.Circumferential grooves limit the expansion of the tip leakage vortex in the direction perpendicular to the blade chord,but generate a set of secondary tip leakage vortices due to the interaction with the leakage mass flow.Finally,a deeper investigation of the tip leakage flow is proposed. 展开更多
关键词 transonic axial compressor casing treatment circumferential groove tip leakage vortex
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A Study of the Unsteady Tip Flow Field of a Transonic Compressor 被引量:3
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作者 JingXuan Zhang Chengqin Li +1 位作者 Hongwu Zhang Weiguang Huang 《Journal of Thermal Science》 SCIE EI CAS CSCD 2011年第1期1-5,共5页
An experimental investigation on the unsteady tip flow field of a transonic compressor rotor has been performed.The casing-mounted high frequency response pressure transducers were arranged along both the blade chord ... An experimental investigation on the unsteady tip flow field of a transonic compressor rotor has been performed.The casing-mounted high frequency response pressure transducers were arranged along both the blade chord and the blade pitch.The chord-wise ones were used to indicate both the ensemble averaged and time varying flow structure of the tip region of the rotor at different operating points under 95% design speed and 60% design speed.The pitch-wise circumferential transducers were mainly used to analyze the unsteadiness frequency of the tip leakage flow in the rotor frame at the near stall condition.The contours of casing wall pressure show that there were two clear low pressure regions in blade passages,one along the chord direction,caused by the leakage flow and the other along the tangential direction,maybe caused by the forward swept leading edge.Both low pressure regions were originated from the leading edge and formed a scissor-like flow pattern.At 95% design speed condition,the shock wave interacted with the low pressure region and made the flow field unsteady.With the mass flow reduced,the two low pressure regions gradually contracted to the leading edge and then a spike disturbance emerged. 展开更多
关键词 TRANSONIC COMPRESSOR unsteady flow
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Control of Transonic Flow Fields Using Local Occurrence of Non-Equilibrium Condensation
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作者 Junji Nagao Shigeru Matsuo +2 位作者 Tokitada Hashimoto Toshiaki Setoguchi Heuy Dong Kim 《Journal of Thermal Science》 SCIE EI CAS CSCD 2013年第4期327-332,共6页
Control of supersonic flow fields with shock wave is important for some industrial fields. There are many studies for control of the supersonic flow fields using active or passive control. When non-equilibrium condens... Control of supersonic flow fields with shock wave is important for some industrial fields. There are many studies for control of the supersonic flow fields using active or passive control. When non-equilibrium condensation occurs in a supersonic flow field, the flow is affected by latent heat released. Many studies for the condensation have been conducted and the characteristics have been almost clarified. Further, it was found that non-equilibrium condensation can control the flow field. In these studies, the condensation occurs across the passage of the flow field and it causes the total pressure loss in the flow field. However, local occurrence of non-equilibrium condensation in the flow field may change the characteristics of total pressure loss compared with that by the condensation across the passage of the nozzle and there are few for researches of locally occurred non-equilibrium condensation in supersonic flow field. The purpose in the present study is to clarify the effect of local occurrence of non-equilibrium condensation on the transonic flow field in a nozzle with a circular bump. As a result, local occurrence of non-equilibrium condensation reduced the shock strength and total pressure loss in the transonic flow field by flowing the moist air from trailing edge of the circular bump to the mainstream. 展开更多
关键词 Compressible flow Transonic flow Shock wave Non-equilibrium condensation Circular bump
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Transonic Moist Air Flow around a Circular Arc Blade with Bump 被引量:2
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作者 A.B.M.Toufique HASAN Shigeru MATSUO +1 位作者 Toshiaki SETOGUCHI Heuy Dong KIM 《Journal of Thermal Science》 SCIE EI CAS CSCD 2009年第4期325-331,共7页
The unsteady phenomena in the transonic flow around airfoils are observed in the flow field of fan, compressor blades and butterfly valves, and this causes often serious problems such as aeroacoustic noise and the vib... The unsteady phenomena in the transonic flow around airfoils are observed in the flow field of fan, compressor blades and butterfly valves, and this causes often serious problems such as aeroacoustic noise and the vibration. In recent years, the effect of bump wall on the flow field around an airfoil has been investigated experimentally and as a result, it was observed that the bump wall is effective for the control of shock wave on the airfoil. In the transonic or supersonic flow field, a rapid expansion of moist air or steam gives rise to non-equilibrium condensation. In the present study, the effect of non-equilibrium condensation of moist air on the self-excited shock wave oscillation around a circular arc blade with or without a bump on the blade was investigated numerically. The results showed that the non-equilibrium condensation significantly reduced the flow field unsteadiness such as root mean of pressure oscillation and frequency compared to the case without the non-equilibrium condensation. 展开更多
关键词 transonic flow moist air shock wave oscillation non-equilibrium condensation
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