CAJ | 학술논문

为探讨非轴对称端壁造型降低涡轮叶栅二次流损失的有效性，构建基于高压涡轮直列叶栅的非轴对称端壁气动优化设计方法，并用NUMECA／FineTurbo模块对优化后的结果和原涡轮叶栅分别进行流场计算。结果表明：非轴对称端壁造型使叶栅通道的总压损失系数面降低了2．84％；改变了通道内的叶片载荷分布，形成了叶型的载荷后置；改善了流场内的流动结构，使气流的流动变得更加通畅；延迟了通道涡的过早形成，减小了通道涡的强度和尺度。因此，非轴对称端壁造型可以有效地降低涡轮叶栅通道内的二次流损失。
위탐토비축대칭단벽조형강저와륜협책이차류손실적유효성，구건기우고압와륜직렬협책적비축대칭단벽기동우화설계방법，병용NUMECA／FineTurbo모괴대우화후적결과화원와륜협책분별진행류장계산。결과표명：비축대칭단벽조형사협책통도적총압손실계수면강저료2．84％；개변료통도내적협편재하분포，형성료협형적재하후치；개선료류장내적류동결구，사기류적류동변득경가통창；연지료통도와적과조형성，감소료통도와적강도화척도。인차，비축대칭단벽조형가이유효지강저와륜협책통도내적이차류손실。
Aiming for investigating the effectiveness of using non-axisymmetric end wall contouring to reduce secondary flow losses in turbine cascade. Hence, concerning a high pressure linear turbine cascade, a system is established to search for the optimum profiled non-axisymmetric end wall. Hereafter, with respect to the con toured end-wall and baseline cascade, detailed numerical simulations are conducted on the turbine cascade flow field. Numerical results show that comparing the contoured end wall to the baseline cascade, the mass averaged total pressure loss is decreased by 2.84%, and the blade loadings in the blade channel are modified, further more, the modification of flow structures enhances flow performance, and thus the formation of the passage vortex is delayed to a large degree and the scale and intensity of the passage vortex is enormously decreased. Hence non-axisymmetric end-wall contouring is proved to be effective in reducing secondary flow losses in tur- bine cascade.