航改燃机排气蜗壳分段式扩压器设计方法研究  

Research on Design Method of Exhaust Volute Segmented Diffuser for Aeroderivative Gas Turbine

作　　者：李想 齐凤升 刘中秋 李宝宽 吴桐 LI Xiang;QI Feng-sheng;LIU Zhong-qiu;LI Bao-kuan;WU Tong(School of Metallurgy,Northeastern University,Shenyang 110819,China;Shenyang Engine Design Institute,Shenyang 110015,China)

机构地区：[1]东北大学冶金学院,沈阳110819 [2]沈阳发动机研究所,沈阳110015

出　　处：《汽轮机技术》2023年第1期6-10,共5页Turbine Technology

基　　金：国家自然科学基金(52174305)。

摘　　要：利用数值计算方法(CFD)建立排气蜗壳内三维流动数学模型模拟分析总压损失来源,在不改变其几何尺寸的前提下,提出航改燃机排气蜗壳分段式扩压器设计方法,并将采用该方法设计的排气蜗壳的结果与原型进行比较,结果表明:在设计工况下,采用分段式扩压器设计方法设计的排气蜗壳使总压损失系数降低19.23%,并通过流场分析揭示了分段式扩压器改善其气动性能的原理。In this paper,the numerical calculation method(CFD)is used to establish a three-dimensional flow mathematical model in the exhaust volute to simulate and analyze the source of the total pressure loss.On the premise of not changing its geometric size,the design method of the segmented diffuser is proposed,and the exhaust gas designed by this method is proposed.The results of the gas volute are compared with the prototype.The results show that:under the design conditions,the exhaust volute designed with the segmented diffuser design method reduces the total pressure loss coefficient by 19.23%,and the flow field analysis reveals that he principle of a segmented diffuser to improve its aerodynamic performance.

关 键 词：航改燃气轮机 排气蜗壳 扩压器 分段设计 数值模拟 

分 类 号：U664.131[交通运输工程—船舶及航道工程]