国产25 MW燃气轮机进气室改型设计  

Modification Design of Intake Chamber of Domestic 25 MW Gas Turbine

作　　者：杜玉锋 孔庆毅 白冰 任博铖 DU Yu-feng;KONG Qing-yi;BAI Bing;REN Bo-cheng(Harbin Guanghan Gas Turbine Co.,Ltd.,Harbin,China,Post Code:150078;No.703 Research Institute of CSSC,Harbin,China,Post Code:150078)

机构地区：[1]哈尔滨广瀚燃气轮机有限公司,黑龙江哈尔滨150078 [2]中国船舶集团公司第七〇三研究所,黑龙江哈尔滨150078

出　　处：《热能动力工程》2022年第12期132-139,共8页Journal of Engineering for Thermal Energy and Power

摘　　要：为进一步提高国产25 MW燃气轮机进气稳定性、降低总压损失,首先计算分析了原进气室长、宽、高变化对总压损失及速度不均匀度的影响,确定了改进的独立进气室的主要几何参数,而后采用帕斯卡涡线对改进的独立进气室底面进行型线优化,采用圆弧曲线及维氏曲线对背面和部分底面进行型线优化。计算分析基于理想气体进口总压100 838 Pa,进口总温298.15 K,出口静压94 900 Pa的边界条件下开展。研究结果表明:相对于改进的独立进气室,采用型线优化的结构削弱了喇叭口前方形箱体内的涡流,进气室出口位置的速度不均匀度及总压损失均减小;相对于改进的独立进气室,选用圆弧曲线或维氏曲线优化型线,判定截面的速度不均匀度分别增加了0.13%,0.14%,总压损失分别降低15.58%,21.43%,内整流罩出口位置速度不均匀度分别降低0.28%,0.19%,总压损失分别降低13.73%,20.6%。In order to further improve the intake stability of the domestic 25 MW gas turbine and reduce the total pressure loss,the influence of the changes in the length,width and height of the original intake chamber on the total pressure loss and the speed non-uniformity is first calculated and analyzed,and the main geometric parameters of the improved independent intake chamber are determined.Then,the Pascal vortex line is used to optimize the profile of the bottom surface of the improved independent intake chamber.The circular arc curve and Witozinsky curve are used to conduct the test on the back and part of the bottom under the boundary conditions of ideal gas inlet total pressure of 100 838 Pa,inlet total temperature of 298.15 K,and outlet static pressure of 94 900 Pa.The results show that compared with the improved independent intake chamber,the vortex in the square box in front of the bell mouth is weakened by adopting the structure of profile optimization,and the velocity non-uniformity and total pressure loss at the outlet of the intake chamber are reduced;compared with the improved independent intake chamber,the circular arc curve or Witozinsky curve is selected to optimize the profile,and the velocity non-uniformity of the judgment section is increased by 0.13% and 0.14%,the total pressure loss is reduced by 15.58% and 21.43%,the velocity non-uniformity at the outlet of the inner fairing is reduced by 0.28% and 0.19%,and the total pressure loss is reduced by 13.73% and 20.6% respectively.

关 键 词：进气室改型设计 速度不均匀度 总压损失 帕斯卡涡线及维氏曲线 型线优化 

分 类 号：TK221[动力工程及工程热物理—动力机械及工程]