重型燃气轮机燃烧室设计与试验研究  

Design and development test of a heavy-duty gas turbine combustor

作　　者：金戈[1] 齐兵[1] 王克新[1] 刘常青[1] 尹家录[1] 顾铭企[1] 

机构地区：[1]中国一航沈阳发动机设计研究所,沈阳110015

出　　处：《燃气轮机技术》2009年第4期44-48,共5页Gas Turbine Technology

摘　　要：完成了用于110MW级重型燃气轮机的干低排放燃烧室的设计和第一阶段试验验证。燃烧室采用轴向分级的贫油预混燃烧技术降低NOx排放,将火焰筒头部分为环形区、预混区和扩散区三个燃烧区。单管燃烧室全尺寸中压试验结果表明:在第一种工作模式下,燃烧室的总压损失、起动点火、燃烧效率、出口温度分布、压力脉动和火焰筒壁温均满足设计要求,但NOx排放超过设计要求。受周期和试验条件限制,第二种工作模式下的NOx排放试验尚未完成。The design and first stage development test of a dry low emission eombustor for a 110MW heavy- duty gas turbine has been finished. The combustor adopts a axial staged lean premixed combustion technique to reduce NO, emission, and the head of combustion liner is separated into annular combustion zone, premixed zone and diffusion zone. The full - scale, medium - pressure development test of single can has been conducted, test results show that in the first operating mode, combustor operating parameters including total pressure loss, starting ignition, combustion efficiency, exhaust temperature profile, dynamic pressure and metal temperature distribution are able to meet the design requirements except NO2 emission. Be restricted by schedule and test condition,the NO, emission test in the second operating mode doesn＇t complete yet.

关 键 词：燃烧室 设计 试验 NOX排放 

分 类 号：TK474.9[动力工程及工程热物理—动力机械及工程]