某型燃气轮机燃烧室改进试验  

Experimental modification for combustor of a gas turbine

作　　者：刘凯 曾文 刘爱虢 LIU Kai;ZENG Wen;LIU Aiguo(Faculty of Aerospace Engineering,Shenyang Aorospace University,Shenyang 110136,China)

机构地区：[1]沈阳航空航天大学航空航天工程学部(院),辽宁沈阳110136

出　　处：《热力发电》2018年第8期120-124,共5页Thermal Power Generation

基　　金：国家自然科学基金(51376133);航空科学基金(2015ZB54003)~~

摘　　要：针对燃气轮机低污染排放要求,对某型常规航空发动机燃烧室进行了增大主燃孔直径及掺混孔提前的改进,试验以0号柴油为燃料,进行了点火、熄火特性、出口温度场、污染物排放、燃烧效率研究。结果表明:主燃孔孔径由Φ9 mm增大到Φ11 mm,进气量由26.2%增大到39.1%,主燃区余气系数由0.95增大到1.10,常温常压贫油点火油气比由0.025 50~0.032 44变为0.024 46~0.036 25,但优于0.05的低污染燃烧室设计标准;出口温度分布系数由0.226 4降为0.207 1,提高了温度场品质;CO及未燃烃UHC排放指数有所提高,但NO_x排放指数由2.26 g/kg减小到1.34 g/kg,降低了40.7%;燃烧效率由0.984 2略有降低为0.982 3;在此基础上将掺混孔提前,但各项指标未见改善。研究结论为低污染燃气轮机的设计及常规燃烧室改型提供了参考。Aimed at the low pollution emission requirements of gas turbines, the increase of the main combustion hole diameter and the improvement of the mixing hole advance are carried out for one type of conventional aero-engine combustion chamber. The test is conducted using 0# diesel fuel as the fuel, and the research on ignition, flameout characteristics and exit temperature fields is performed. The results show that the main combustion hole diameter increases from 9 mm to 11 mm, the intake air flow increases from 26.2% to 39.1% and the excess air coefficient of main combustion zone increases from 0.95 to 1.10. The oil-gas ratio of lean ignition at normal temperature and pressure changes from 0.025 50~0.032 44 to 0.024 46~0.036 25, but better than the low pollution combustion chamber design standards value of 0.05. The distribution coefficient of outlet temperature is reduced from 0.226 4 to 0.207 1, which improves the quality of the temperature field. The emission indexes of CO and UHC increase, but the emission index of NO_x decreases from 2.26 g/kg to 1.34 g/kg, by 40.7%. The combustion efficiency slightly decreases from 0.984 2 to 0.982 3. After advancing the mixing hole, all indexes are not improved. This results provide a reference for the design of low pollution gas turbines and the modification of conventional combustion chambers.

关 键 词：燃气轮机 燃烧室 火焰筒 主燃孔 掺混孔 油气比 排放指数 燃烧特性 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]