摘要
针对某中档功率燃气轮机压气机部件气动性能需求，开展了五级轴流低压压气机气动设计技术数值研究。围绕提高效率和扩大喘振裕度两个根本问题，在气动设计的一维设计、S2通流设计、叶片造型等各个环节进行了参数筛选与性能优化，并通过Numeca软件和Denton程序全三维数值模拟性能确认，设计点气动性能满足并超过了指标要求。为了满足低速运行压气机喘振裕度要求，一维经验统计数值预测前面级导叶调节所能带来的喘振裕度拓展区间，并研究了几级联调的调节规律，以指导五级轴流压气机气动性能试验。本文研究提供了满足性能指标要求的全新五级轴流压气机气动设计，获得的扩喘导叶调节规律可供相似多级轴流压气机导叶联调参考。
The aerodynamic design of five-stage low-pressure axial compressor（LPC） was conducted aimed at the aerodynamic performance need of the components of a mid-power gas turbine. Two main problem, efficiency and stall margin, were considered and the design parameters of 1D, $2 throughflow, blade shape were filtered and optimized. Full 3D numerical simulations were conducted using Numeca software and Denton code and the results show that the aerodynamic performance at design point exceed the design requirements. To satisfy with the requirements of stall margin of low speed operation, 1D experienced statistical numerical method was used to predict the stall margin resulted from adjusting front stage guide blade and research the rule of adjusting to multi-stage simultaneously, these rule can be used to guide aerodynamic experiments of five-stage LPC. A newly designed fivestage LPC that satisfy with indices of aerodynamic performance is presented in this paper and rule of adjusting guide blade for enhancing stall margin can be used to similar multi-stage axial compressors.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2010年第6期943-946,共4页
Journal of Engineering Thermophysics
基金
国家科技部863计划项目(No.50376062)
关键词
燃气轮机
轴流压气机
气动设计
数值模拟
gas turbine
axial compressor
aerodynamic design
numerical simulation
