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旋转气冷涡轮三维流场的实验与数值研究 被引量:4
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作者 袁锋 竺晓程 杜朝辉 《中国电机工程学报》 EI CSCD 北大核心 2008年第2期82-87,共6页
采用k-ε湍流模型对气冷涡轮在静止和旋转2种工况下三维流场进行数值计算,并与PIV测量结果进行对比。计算得到射流和主流的掺混区域三维速度以及射流尾迹区二次流动,k-ε湍流模型的计算结果与实验基本吻合。与静止涡轮流场相比,旋转状... 采用k-ε湍流模型对气冷涡轮在静止和旋转2种工况下三维流场进行数值计算,并与PIV测量结果进行对比。计算得到射流和主流的掺混区域三维速度以及射流尾迹区二次流动,k-ε湍流模型的计算结果与实验基本吻合。与静止涡轮流场相比,旋转状态下涡轮内部流场中存在的离心力、哥氏力的作用使射流与主流掺混流场三维速度发生改变,其中径向速度的改变明显。计算和实验结果表明,旋转对气冷涡轮叶片压力面侧流场的影响大于吸力面。同时,吹风比增大使射流与主流掺混流场区域以及射流尾迹区的范围扩大。 展开更多
关键词 气膜冷却涡轮 旋转状态 静止状态 三维流场 激光粒子测速仪测量 数值计算
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Numerical simulation of 3D viscous flow field of air cooled turbine blades with coolant mixing
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作者 姜澎 王强 +1 位作者 黄洪雁 冯国泰 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2008年第6期781-785,共5页
To improve thrust and reduce oil consumption of aero-engines, the temperature at turbine inlet is becoming higher and higher, which leads to heavy thermal load of vanes. To efficiently cool the vanes, the mass of cool... To improve thrust and reduce oil consumption of aero-engines, the temperature at turbine inlet is becoming higher and higher, which leads to heavy thermal load of vanes. To efficiently cool the vanes, the mass of coolant with its maximum gas mass flow exceeding to 20% of main stream, has to be increased. In the pres- ent paper, a two-stage turbine with and without coolant mixing was simulated by CFX-TASCflow. Simulation resuits indicate that the flow field structure with coolant is obviously different from that without coolant, and the former has characteristics of lower-speed main flow, reduced mach number, weaker shock intensity and decreased stage efficiency. 展开更多
关键词 gas turbine film cooling MIXING MULTI-STAGE
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Investigation of film cooling on the leading edge of turbine blade based on detached eddy simulation 被引量:1
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作者 LIANG JunYu KANG Shun 《Science China(Technological Sciences)》 SCIE EI CAS 2012年第8期2191-2198,共8页
In order to assess the influences of curved hole passage on cooling effectiveness and flow structure of turbine blade leading edge,the detached eddy simulation is applied to numerically investigate the AGTB turbine ca... In order to assess the influences of curved hole passage on cooling effectiveness and flow structure of turbine blade leading edge,the detached eddy simulation is applied to numerically investigate the AGTB turbine cascade under the condition of global blowing ratio M=0.7.The straight or curved cooling holes are located at either the pressure or suction side near the leading edge.The analysis and discussion focus on the local turbulence structure;influence of pressure gradient on the structure,and distribution of cooling effectiveness on the blade surface.The numerical results show that cooling hole with curved passage could bring positive impact on the increase of the local cooling effectiveness.On the suction side,the increased cooling effectiveness could be about 82% and about 77% on the pressure side,compared to the conventional straight hole. 展开更多
关键词 film cooling blade leading edge detached eddy simulation cooling effectiveness coherent structure
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