气膜冷却流场和温度场特性的高速纹影研究
发布时间：2019-02-24 08:47
【摘要】：气膜冷却作为一种重要的冷却手段,已广泛应用于现代燃气轮机燃烧室和涡轮叶片等高温部件中,气膜冷却效率的提高在维护高温部件性能和提升整机使用寿命方面有着至关重要的作用。研究气膜冷却流场内部结构和相互作用机理对于提高气膜冷却效率有很大帮助。本文依托浙江理工大学现有的风洞系统搭建了平板气膜冷却实验台,结合改进的纹影系统和图像采集系统,对平板气膜冷却流场进行了可视化研究,在吹风比分别为0.5、1.0、1.5、2.0,射流角度分别为30°、45°、60°的工况下,从射流对主流的穿透力,射流在扩展区域的覆盖面积,以及射流和主流相互作用形成的涡的结构方面进行了深入研究。结合数值模拟的方法,对流场内部涡量场、温度场、密度场的变化进行了分析,并与实验所得结果进行了对比,得出以下主要结论:1、不同工况下射流对主流的穿透力不同。射流角度相同时,随着吹风比的增大,射流对主流的穿透力增强。吹风比相同时,随着射流角度的增大,射流对主流的穿透力增强,两者都呈单调变化趋势。2、不同工况下射流在扩展区域的覆盖面积变化规律不同。在入射角为30°时,射流覆盖面积随着吹风比的增大而增大,在入射角为45°,吹风比为2.0与吹风比为1.5相比射流覆盖面积并无明显变化,在入射角为60°时,吹风比为2.0与吹风比为1.5相比,射流覆盖面积减小。3、相同吹风比下,随着入射角的增大,剪切涡和尾迹涡尺度越来越大,越来越明显。相同射流角度下,随着吹风比的增大,剪切涡和尾迹涡尺度越来越大,越来越明显。但是入射角度对剪切涡和尾迹涡的的影响更大。
[Abstract]:As an important cooling method, film cooling has been widely used in modern gas turbine combustor, turbine blade and other high temperature components. The improvement of film cooling efficiency plays an important role in maintaining the performance of high temperature components and improving the service life of the whole machine. The study of the internal structure and interaction mechanism of film cooling flow field is of great help to improve the film cooling efficiency. In this paper, based on the existing wind tunnel system of Zhejiang University of Technology, a flat film cooling experimental platform is built, combined with an improved schlieren system and an image acquisition system, a visualization study on the flat film cooling flow field is carried out. Under the condition that the air blowing ratio is 0.5 ~ (1. 0) / 1. 5 ~ 1. 5 / 2, and the jet angle is 30 掳, 45 / 60, respectively, the coverage area of the jet in the expanded area is obtained from the penetration of the jet to the main stream and the area covered by the jet in the expanded area. And the structure of vortex formed by the interaction of jet and mainstream is studied. Combined with numerical simulation, the variation of vortex field, temperature field and density field in the flow field are analyzed and compared with the experimental results. The main conclusions are as follows: 1. When the jet angle is the same, the penetration of the jet to the main stream increases with the increase of the blowing ratio. When the blowing ratio is the same, with the increase of the jet angle, the penetration of the jet to the mainstream increases, and both of them show a monotone changing trend. 2. The variation of the coverage area of the jet in the expanded area is different under different operating conditions. When the incidence angle is 30 掳, the jet coverage area increases with the increase of the blowing ratio. When the incident angle is 45 掳, the blowing ratio is 2.0 and the blowing ratio is 1.5, the coverage area of the jet does not change significantly, and when the incidence angle is 60 掳, the jet coverage area does not change obviously. When the blowing ratio is 2.0 and the blowing ratio is 1.5, the coverage area of the jet decreases. 3. At the same blowing ratio, the scale of shear vortex and wake vortex becomes larger and more obvious with the increase of the incident angle. At the same jet angle, the scale of shear vortex and wake vortex becomes larger and larger with the increase of blowing ratio. But the incident angle has more influence on the shear vortex and wake vortex.
【学位授予单位】：浙江理工大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：TK471
[Abstract]:As an important cooling method, film cooling has been widely used in modern gas turbine combustor, turbine blade and other high temperature components. The improvement of film cooling efficiency plays an important role in maintaining the performance of high temperature components and improving the service life of the whole machine. The study of the internal structure and interaction mechanism of film cooling flow field is of great help to improve the film cooling efficiency. In this paper, based on the existing wind tunnel system of Zhejiang University of Technology, a flat film cooling experimental platform is built, combined with an improved schlieren system and an image acquisition system, a visualization study on the flat film cooling flow field is carried out. Under the condition that the air blowing ratio is 0.5 ~ (1. 0) / 1. 5 ~ 1. 5 / 2, and the jet angle is 30 掳, 45 / 60, respectively, the coverage area of the jet in the expanded area is obtained from the penetration of the jet to the main stream and the area covered by the jet in the expanded area. And the structure of vortex formed by the interaction of jet and mainstream is studied. Combined with numerical simulation, the variation of vortex field, temperature field and density field in the flow field are analyzed and compared with the experimental results. The main conclusions are as follows: 1. When the jet angle is the same, the penetration of the jet to the main stream increases with the increase of the blowing ratio. When the blowing ratio is the same, with the increase of the jet angle, the penetration of the jet to the mainstream increases, and both of them show a monotone changing trend. 2. The variation of the coverage area of the jet in the expanded area is different under different operating conditions. When the incidence angle is 30 掳, the jet coverage area increases with the increase of the blowing ratio. When the incident angle is 45 掳, the blowing ratio is 2.0 and the blowing ratio is 1.5, the coverage area of the jet does not change significantly, and when the incidence angle is 60 掳, the jet coverage area does not change obviously. When the blowing ratio is 2.0 and the blowing ratio is 1.5, the coverage area of the jet decreases. 3. At the same blowing ratio, the scale of shear vortex and wake vortex becomes larger and more obvious with the increase of the incident angle. At the same jet angle, the scale of shear vortex and wake vortex becomes larger and larger with the increase of blowing ratio. But the incident angle has more influence on the shear vortex and wake vortex.
【学位授予单位】：浙江理工大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：TK471
【相似文献】
相关期刊论文 前10条
1 徐靖中,葛绍岩;弯曲壁面离散孔气膜冷却数值计算[J];工程热物理学报;1983年01期
2 徐靖中,姚永庆,贾建国,葛绍岩,邹福康;凸表面单排孔30°喷射气膜冷却流场近场特性的实验研究[J];工程热物理学报;1984年02期
3 姚永庆,夏彬,葛绍岩,邹福康;双排离散孔在凸表面上气膜冷却有效温比的传质实验研究[J];航空动力学报;1986年01期
4 张鸣远 ,陈学俊 ,邹福康 ,葛绍岩 ,徐靖中 ,陈时钧;双排叉排孔气膜冷却特性研究 (二) 绝热有效温比[J];航空动力学报;1990年01期
5 江涛,刘松龄;曲壁气膜冷却数值计算的研究[J];航空学报;1991年05期
6 朱惠人,许都纯,刘松龄,王宝珑;簸箕形排孔气膜冷却实验研究[J];航空学报;1997年05期
7 蒋雪辉,赵晓路;非定常尾迹对叶片头部气膜冷却的影响[J];航空动力学报;2005年04期
8 张树林,王洪斌;多斜孔板气膜冷却性能试验研究[J];航空发动机;2005年03期
9 姚玉;张靖周;李永康;;带三角形突片气膜冷却结构换热特性的数值研究[J];航空动力学报;2006年04期
10 曾军;王彬;康勇;;气膜冷却涡轮导向叶片流场数值模拟[J];燃气涡轮试验与研究;2006年04期
相关会议论文 前10条
1 贺安江;;新型气膜冷却孔的数值研究[A];北京力学会第17届学术年会论文集[C];2011年
2 秦晏e，
本文编号：2429370
本文链接：https://www.wllwen.com/kejilunwen/dongligc/2429370.html
