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作 者:段静瑶 肖俊峰[1] 于飞龙[1] 高松[1] 李园园[1] 刘战胜 张蒙[1] 闫安[1] DUAN Jing-yao;XIAO Jun-feng;YU Fei-long;GAO Song;LI Yuan-yuan;LIU Zhan-sheng;ZHANG Meng;YAN An(Xi'an Thermal Power Research Institute Co.,Ltd.,Xi'an 710032,China)
出 处:《汽轮机技术》2022年第4期267-270,317,共5页Turbine Technology
基 金:华能集团科技项目(HNKJ20-H42)。
摘 要:为研究叶顶冷却孔尺寸对透平叶片冷却特性的影响,以某重型燃气轮机透平第一级动叶为研究对象,在叶顶冷却孔直径为0.8mm、0.9mm、1.0mm和1.1mm的条件下进行定常三维数值模拟。计算结果表明,当叶顶冷却孔直径从0.8mm增大至1.1mm,其相对流量由2.23%增大至3.87%,叶顶平均温度降低了8℃,叶顶冷却效率增高了3.29%。叶顶冷却孔直径变化对叶身温度分布影响较小,对叶顶温度分布影响较大;大叶顶冷却孔直径情况下,冷却流量增大导致冷却流体射出后未贴附凹槽内壁面,部分高温燃气在凹槽前部流入叶顶形成高温区,但阻止了部分燃气冲击凹槽中部;小叶顶冷却孔直径情况下,从叶顶冷却孔流出的冷却气流分为两部分,其中一部分流向凹槽压力面侧,对压力面侧高温燃气进入凹槽起到一定阻碍作用。Three-dimensional steady RANS simulations were conducted on the heavy-duty gas turbine first stage bucketwith tip cooling hole diameter of 0.8mm,0.9mm,1.0mm and 1.1mm,to study the influence of cooling hole size on film cooling effect of gas turbine bucket.The results show that when the diameter of the tip cooling hole increases from 0.8mm to 1.1mm,the relative cooling mass flow increases from 2.23%to 3.87%,the average temperature of blade tip decreases by 8℃,and the cooling efficiency of blade tipincreases by 3.29%.The tip cooling hole diameter change has little effect on the temperature distribution of the blade body,but has a significant influence on the blade tip.In the case of largetip hole diameter,the increase in cooling flow causes the cooling fluid to escape from the bottom of the squealer tip,which prevents part of the gas from impacting the middle of the squealer tip,whereas some gas flow entersthe squealer tip at the front and forms a high-temperature zone.In the case of small tip holediameter,the tipcooling flow is divided into two parts,one of which flows to the pressure surface side of squealer tip,which prevents the gas on the pressure surface side from entering the squealer tip.
分 类 号:TK474.7[动力工程及工程热物理—动力机械及工程]
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