三级高负荷压气机改型设计与流动分析  

Design and Flow Analysis of Three-Stage Highly Loaded Compressor

作　　者：邓航文 罗磊[1] 牟光远 李柏 秦润轩 周逊[1] DENG Hangwen;LUO Lei;MOU Guangyuan;LI Bai;QIN Runxuan;ZHOU Xun(School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《工程热物理学报》2025年第3期807-814,共8页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.P2022-Ⅲ-003-002);国家重大科技专项(No.2017-Ⅱ-0007-0021)。

摘　　要：本文基于某重型燃气轮机末三级压气机,以提高压比、效率、拓宽裕度为目的,重新设计一台突破常规负荷的三级高负荷压气机,设计过程引入了三维叶片技术对静叶进行端部处理。对比分析了改型前后各级的效率压比以及静叶的出口总压损失等关键参数的变化,结果表明,与原型相比,在进口气流角和出口马赫数保持一致的前提下,三维叶片技术通过对壁面附面层的迁移有效地控制了压气机静叶角区分离,三级高负荷改型压气机在设计点附近效率达到90.08%,压比1.393,失速裕度25.5%。This article is based on the 9FA heavy-duty gas turbine final stage compressor,aiming to improve the pressure ratio,efficiency,and expand the margin.It redesigns a three-stage high-load compressor that breaks through the conventional load.In the design process,three-dimensional blade technology is used in the end region of the stator blades.Comparative analysis was conducted on the changes in key parameters such as efficiency,pressure ratio,and total pressure loss at the outlet of each stage before and after the modification.The results show that,compared to the prototype,the three-dimensional blade technology effectively controls the separation of the stator blade corner by transferring the boundary layer on the wall while maintaining consistent inlet flow angle and outlet Mach number.The modified three-stage high-load compressor achieves an efficiency of 90.08%,a pressure ratio of 1.393,and a surge margin of 25.5%near the design point.

关 键 词：高负荷改型压气机 三维叶片技术 端部处理 流动分析 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]