航空工程进展2012，Vol.3Issue(4)：486-491,6.
一种新型涡轮叶栅非轴对称端壁造型的数值研究
Numerical Investigation of a Novel Non-axisymmetric End-wall Contouring for Turbine Cascade
摘要
Abstract
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.关键词
涡轮叶栅/非轴对称端壁造型/二次流损失/通道涡Key words
turbine cascade~ non-axisymmetric end-wall contouring l secondary tlow loss~ passage vortex分类
航空航天引用本文复制引用
刘波,陈得胜,那振喆,曹志远,黄建..一种新型涡轮叶栅非轴对称端壁造型的数值研究[J].航空工程进展,2012,3(4):486-491,6.基金项目
国家自然科学基金 （）
