以柴油为燃料的旋流杯燃烧室燃烧性能研究  

Combustion Performance Study of Swirl Cup Combustor Using Diesel as Fuel

作　　者：刘爱虢[1] 朱悦[1] 陈保东[1] 朱涛 刘凯[1] 曾文[1] 

机构地区：[1]沈阳航空航天大学航空航天工程学院,辽宁沈阳110136 [2]中国航发沈阳发动机研究所,辽宁沈阳110015

出　　处：《推进技术》2017年第8期1804-1811,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金(51476106);航空科学基金(2015ZB54003)

摘　　要：为分析燃料和燃烧室结构对燃烧性能的影响,对地面用燃气轮机采用旋流杯燃烧室以0号柴油为燃料时的燃烧性能进行了试验研究,同时研究了主燃孔尺寸和掺混孔轴向位置对燃烧性能的影响。试验结果表明:使用柴油为燃料后,由于粘度增加燃烧室的点火和熄火特性变差,常温点火油气比高于0.034,慢车贫油熄火油气比高于0.005,提高燃烧室入口气流温度至240℃可使最低点火油气比降至0.023;在相同油气比和入口条件下燃烧室温升超过900℃,高于相同入口条件下航空煤油温升,燃烧效率达到了98%以上,出口温度分布系数最高为0.2324满足出口温度分布均匀性要求,CO,NO_x和UHC排放最高值分别为76.57,56.73和626m L/m3,都满足污染物排放要求,SN4为11.9,达到了无烟燃烧室标准。主燃孔直径增大至11mm,使主燃区空气流量增加2%会导致燃烧室的点火油气比升高约5%,熄火油气比升高约3%;掺混孔前移导致贫油熄火油气比升高10%、燃烧效率下降1.3%,出口温度分布系数升高至0.2324,但会使NO_x和CO的排放分别降低49%和18%;掺混孔后移,会使出口温度分布系数降至0.197,NO_x排放降低26%。In order to analyze the effects of fuel and combustor structure on combustion performance, the combustion performance experiments of ground gas turbine with swirl cup combustor were studied using No.0 die- sel oil as fuel. The effects of the primary hole size and mixing hole axial position on combustion performance were studied using the experiment test. The experimental results show that the ignition and lean blowout performance were getting worse due to the increased viscosity of diesel, the ignition fuel-air ratio was higher than 0.034 at room temperature, and idle lean blowout fuel-air ratio was higher than 0.005. The lowest ignition fuel-air ratio can be decreased to 0.023 by increasing the inlet airflow temperature to 240℃. The temperature rise is 900℃ which is higher than aviation kerosene under the same inlet conditions. The combustion efficiency reaches more than 98%, the highest outlet temperature distribution factor （OTDF） of 0.2324 can meet the requirments of temperature distribution uniformity. The highest values of CO, NOx and UHC are 76.57, 56.73 and 626mL/m^3, respectively, so the pollutant emission all meets the requirements. The combustor is smokeless with the SN4=11.9. The fuel-air ration will increase 5% and 3% for ignition and lean blowout when the primary hole diameter increased to 1 lmm causing the air flow in the main combustion zone increased 2%. The lean blowout fuel-air ra- tio can increase 10%, the combustion efficiency decreased 1.3% and the OTDF reaches to 0.2324 when the mix- ing holes were forward, while the emission of NO. and CO will decrease 49% and 18% at this condition. The OTDF can increase to 0.197 and the NOx emission decreases 26% for the backward of mixing holes.

关 键 词：燃气轮机 燃烧室 柴油 燃烧性能 

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]