摘要
利用数值模拟的方法,研究了静叶采用前缘增弯对某多级重型燃气轮机压气机中间两级气动性能的影响。计算结果表明,在近失速点处,原型静叶角区存在较大尺度的闭式分离泡。应用端弯叶片技术后,端壁回流区消除,角区分离尺寸减小,在保证设计点处气动性能不变的前提下,两级压气机的喘振裕度增加了12.85%,峰值效率提高了约0.67%。
By applying the numerical methods, the effects of application of leading edge recambering in the stators on the aerodynamic performance of a two stage axial compressor in a multi-stage heavy duty gas turbine were investigated. The numerical simulations show that, near the stall point, a large-scale closed separation bubble emerges within the datum case comer region. By using the end-bend blade, the recirculation region on the endwall is eliminated and the corner separation size is reduced. At the premise of design point performance assurance, the stall margin of the compressor is increased by 12.85%, and the peak efficiency is increased by 0.67%.
出处
《汽轮机技术》
北大核心
2017年第3期180-182,206,共4页
Turbine Technology
关键词
地面重型燃气轮机
压气机
端弯
数值模拟
heavy duty gas turbine
compressor
end-bend
numerical simulation
