燃气轮机过渡段气动优化设计
Aerodynamic Optimization Design for Transition Section of Gas Turbine
李翔宇 1朱晓明 1郭刚 2任永磊2
作者信息
- 1. 中国船舶集团有限公司第七〇三研究所,黑龙江 哈尔滨 150078;船舶与海洋工程特种装备和动力系统国家工程研究中心-燃气轮机研发与检测试验室,黑龙江 哈尔滨 150078
- 2. 国家管网集团西气东输公司,上海 200122
- 折叠
摘要
为研究燃气轮机过渡段高效气动设计方法,以某型燃气轮机过渡段为研究对象,在给定的气动边界和几何限制条件下,按照过渡段坡角设计、上下端壁型线优化设计、支柱型式选取的思路,采用CFD数值仿真方法,对过渡段气动设计方法进行研究.首先,对比过渡段坡角为 14°,19°,24°条件下的过渡段性能及下游动力涡轮比功;然后,对过渡段上、下端壁型线进行优化;最后,对比支柱对过渡段气动性能的影响,采用截面面积由下至上减小和截面面积不变两种型式,根部截面面积保持一致,完成过渡段气动优化设计.结果表明:坡角为 19°条件下过渡段气动性能最优;在1.0 工况下,相比原型型线优化后的过渡段总压恢复系数由0.994 8 提高到0.995 1,静压升系数由2.450 4 提高到2.595 2,过渡段出口马赫数由0.217 6 降低到0.199 5,出口静压分布更为均匀;截面面积由下至上递减的支柱型式过渡段气动性能更优.
Abstract
In order to study the high-efficient aerodynamic design method of transition section of gas tur-bine,taking the transition section of a certain gas turbine as the research object,under the condition of given aerodynamic boundary and geometric constraints,CFD numerical simulation method was adopted to study the aerodynamic design for gas turbine transition section according to the ideas of slope angle de-sign,profile optimization design of upper and lower end walls and pillar type selection.Firstly,the per-formance of transition section and the specific power of downstream power turbine were compared under 14°,19°and 24°slope angles;then,the upper and lower wall profiles of the transition section were opti-mized;finally,the influence of two types of pillars on the aerodynamic performance of transition section was compared,adopting two kinds of states,such as decreasing from bottom to top and remaining un-changed for section area,the root section area remains unchanged,so as to complete the transition sec-tion aerodynamic optimization design.Results indicate that when the slope angle is 19°,the aerodynamic performance of transition section is best;the total pressure recovery coefficient of optimized transition sec-tion increases from 0.994 8 to 0.995 1,the static pressure rise coefficient increases from 2.450 4 to 2.595 2,and the outlet Mach number decreases from 0.217 6 to 0.199 5 compared with the prototype profile under the working condition of 1.0.The outlet static pressure distribution is more uniform;the aerodynamic performance of the transition section with the pillar type is better under the section area de-creasing from bottom to top.
关键词
燃气轮机/过渡段/坡角/型线/支柱/气动优化设计Key words
gas turbine/transition section/slope angle/profile/pillar/aerodynamic optimization design引用本文复制引用
基金项目
国家科技重大专项(J2019-Ⅱ-0009-0029)
国家科技重大专项(Y2019-Ⅷ-0013-0174)
中船集团自立科技项目(202109Z)
出版年
2024
NETL
NSTL
万方数据