应用管网算法预测旋转对动叶冷却结构性能的影响

应用自行开发的管网算法,数值模拟了某型重燃第一级动叶内部冷却结构在静止和旋转状态下的流动和换热特性,结果表明:在相同的边界条件下,与静止状态比较,动叶旋转产生的离心力和科氏力改善了冷气在冷却流道内的流动,提高了冷气的流量以及被冷却壁面对冷气的扰动,增大了冷却流道內壁面的换热系数,从而提高了冷气的冷却效率。如果在静止状态动叶冷却结构满足设计要求,那么在旋转状态动叶的冷却结构也必定满足设计要求。     

重燃涡轮通流特性的准三维数值模拟

采用自主开发的经过多次燃气涡轮工程设计考核的准三元设计平台,以重型燃气轮机涡轮作为研究对象,数值模拟了涡轮通流部分特征部位的气动参数分布规律。数值结果给出了总体气动性能,冷气分布、子午流线和各级反力度以及气动参数节距平均值沿诸列叶栅叶高的分布。通过对计算结果的比较分析,总结出9FA和中低热值燃料重型燃气轮机涡轮通流部分的气动设计特点,为我国自行研制重型燃气轮机涡轮提供借鉴和参考。     

蒸汽轮机末级应用海豚型静叶的数值仿真

分别对海豚型叶型和常规设计的蒸汽轮机叶型进行了一级全三维气液两相数值计算,对比发现所设计的海豚型叶型在改善常规叶型流场的气动性能、提高汽轮机轮周效率的同时,可以提高流道内叶片段区域的湿蒸汽干度,改善流道内湿蒸汽的分布。海豚型叶型具有短的扩压段,使激波和附面层干扰区域具有更强的防汽流脱落能力,这样可减少此区域内水膜被高速汽流急剧撕裂成二次水滴的可能。海豚型叶型通道内湿蒸汽湿度沿叶高的分布特点有利于在叶片上表面开设除湿槽,进行高效除湿。     

Numerical simulation of HP rotor cooling configuration using parameterized method

This paper implemented cooling configuration design on certain gas turbine HP rotor using parameterized method.It is convenient for complicated gas turbine blade modeling using parameters and also benefit for the geometry modify in later period.Parameterized modeling is the foundation of air cooling turbine blade design method engineering application.Mesh quality can be awarded when generated complicated cooling configuration blade grids,and also the increase of calculation error can arise by many mesh blocks.Film cooling and serpentine passage can effectively enhance the cooling effectiveness and protect blade.     

Effects of circumferential configuration concerning splitter blade on the aerodynamic performance in a transonic axial fan

For a certain type of transonic axial fan, the flow field of a fan rotor with splitter blade was computed by numerical simulation, and the shape of the rotor was modified. The effects of different circumferential distributions concerning the splitter cascades upon the aerodynamic performance were investigated. The studies show that the optimum splitter cascade is not very close to the suction side of main blade. The load between the main blade and the splitter blade can be soundly distributed in terms of the adjustment of circumferential position of the splitter blade. The best aerodynamic performance can be successfully obtained according to the optimum shape of the expanding fluid channel reasonably formed by the splitter blade and the main blade.     

Tests and numerical simulation on curved blade of super-critical adjust stage

Tests and numerical simulations of super-critical adjust stage blade were carried out and the effect of bowed blade on flow characteristics and the secondary flow were analyzed. The simulation and test results show that the adjust stage blade with aft-loading and big front-edge radius has good flow characteristics by meridian shrink. The numerical studies were carried out with software of NUMECA in order to investigate the aerodynamic characteristics of adjust stage blades,which include prototype blade(tested blade) ,positive curved blade (15°) and negative curved blade(-15°) . The simulation results show that the positive curved blade forms a negative static pressure gradient in the lower region of the cascade along the blade height and a positive static pressure gradient in the upper region. This leads to the reduction of the streamwise vortices intensity and the aerodynamic load on both sides of the blade and the endwall. Therefore,the crosswise secondary flow losses of endwall can be decreased considerably.     

超空泡航行体典型弹道特性仿真研究

针对超空泡航行体的弹道及操纵特性进行研究,建立了超空泡航行体在纵平面内的简化运动方程,编制了相应的弹道仿真程序,并对其在90 m/s左右速度区段内的典型弹道特性进行了仿真分析.仿真结果表明,通过对雷顶舵进行典型操舵控制,超空泡航行体可以在无反馈控制的情况下,实现定深直航,以及变航向、变深度等典型弹道机动,可见超空泡航行体的操纵特性良好.     

应用γ-Reθ湍流模型模拟超声速进气道流动

为了准确预估转捩起始点位置,采用考虑转捩的γ-Reθ湍流模型,对锥体高超声速流场和平板激波/边界层干扰流场进行了验证,有效地预测了边界层转捩位置、激波/边界层干扰的复杂波系结构、分离流动以及气动加热现象,且比传统的湍流模型具有更高的可信度.设计了三压缩角和等熵压缩型面进气道流场,计算结果表明,等熵压缩型面设计具有较好的...     

跨音压气机转子多目标气动优化设计

采用基于雷诺平均N-S方程的全三维流场模拟程序和基于多目标遗传算法的数值优化程序,对跨音压气机转子NASA Rotor37进行了优化设计。对所开发的三维N-S方程求解程序进行了实验验证,完善了多目标遗传算法与响应面方法相结合的具有全局寻优能力的优化程序,以总压比和绝热效率最大为设计目标,应用该优化方法对NASA Rotor37进行考虑中弧线和厚度分布的多目标气动优化设计。结果表明:在满足流量约束的条件下,绝热效率提高了0.7%,总压比提高了0.66%,并且优化设计时间大幅减小。     

跨音风扇转子弯掠结合的数值优化设计

为了研究弯掠结合对风扇气动性能的影响,采用基于雷诺平均N-S方程的全三维流场模拟程序和基于遗传算法的数值优化程序,对跨音风扇转子NASA Rotor67进行了优化设计.首先对所开发的三维N-S方程求解程序进行了实验验证,完善了遗传算法和响应面方法相结合的具有全局寻优能力的优化程序,以总压比最大为设计目标,应用该优化方法对NASA Rotor67进行弯掠两个自由度的气动优化设计.结果表明,弯掠联合的采用可以有效地改善流场内的流动状况,在质量流量和绝热效率严格满足约束条件的情况下,总压比提高了1个百分点;该优化方法是可行的.