压力面小翼对涡轮叶栅不同冲角下流场影响的实验研究
发布时间：2018-09-03 09:23
【摘要】：为了控制和降低涡轮动叶由叶顶间隙所引起的泄漏损失,对加装不同宽度压力面小翼的涡轮叶栅间隙流场进行了实验研究,详细测量了±10°,±5°,0°冲角时涡轮叶栅出口流场和叶片表面静压分布情况。结果表明:随来流冲角由负到正,泄漏涡强度减弱,泄漏损失降低;通道涡强度增强,其引起的损失增大。压力面小翼在不同冲角下均对叶顶泄漏流动具有一定的控制作用,在设计冲角和较小的正冲角工况下PW0.3方案压力面小翼作用效果较好,分别使叶栅总损失降低10.38%和8.11%。在冲角变化范围更大时,PW0.4方案压力面小翼效果更好。
[Abstract]:In order to control and reduce the leakage loss caused by the tip clearance of turbine blades, an experimental study was carried out on the gap flow field of turbine cascades with small wings with different widths of pressure surfaces. The flow field at the outlet of turbine cascade and the distribution of static pressure on the blade surface at 卤10 掳and 卤5 掳angle of attack are measured in detail. The results show that the leakage vortex intensity decreases and the leakage loss decreases with the angle of incidence from negative to positive, and the channel vortex strength increases with the increase of the channel vortex intensity. The pressure plane wing has certain control effect on the leakage flow at the blade top under different angles of incidence. Under the condition of design angle of incidence and small positive angle of incidence, the pressure plane wing of the PW0.3 scheme has a better effect, which reduces the total cascade losses by 10.38% and 8.11%, respectively. When the angle of incidence is larger, the effect of PW0.4 pressure surface wing is better.
【作者单位】： 大连海事大学轮机工程学院;
【基金】：国际自然科学基金重点项目(51436002) 中央高校基本科研业务费专项资助(3132014319) 辽宁省高等学校创新团队支持计划资助(LT2015004)
【分类号】：V231
[Abstract]:In order to control and reduce the leakage loss caused by the tip clearance of turbine blades, an experimental study was carried out on the gap flow field of turbine cascades with small wings with different widths of pressure surfaces. The flow field at the outlet of turbine cascade and the distribution of static pressure on the blade surface at 卤10 掳and 卤5 掳angle of attack are measured in detail. The results show that the leakage vortex intensity decreases and the leakage loss decreases with the angle of incidence from negative to positive, and the channel vortex strength increases with the increase of the channel vortex intensity. The pressure plane wing has certain control effect on the leakage flow at the blade top under different angles of incidence. Under the condition of design angle of incidence and small positive angle of incidence, the pressure plane wing of the PW0.3 scheme has a better effect, which reduces the total cascade losses by 10.38% and 8.11%, respectively. When the angle of incidence is larger, the effect of PW0.4 pressure surface wing is better.
【作者单位】： 大连海事大学轮机工程学院;
【基金】：国际自然科学基金重点项目(51436002) 中央高校基本科研业务费专项资助(3132014319) 辽宁省高等学校创新团队支持计划资助(LT2015004)
【分类号】：V231
【相似文献】
相关期刊论文 前10条
1 王国权,杜辉强,李福民,王安民,葛洪生;用激光技术测定轮轨冲角的研究[J];中国铁道科学;1991年02期
2 牛茂升;臧述升;;叶栅进口冲角对叶顶喷气效果影响的试验研究[J];燃气轮机技术;2011年02期
3 胡自荣;冲角和横向力对机车轮缘磨损的影响[J];润滑与密封;1993年05期
4 冯子明;李青燕;邢宗涛;魏玉阳;;冲角对导向涡轮叶栅气动性能影响研究[J];节能技术;2011年06期
5 周逊;王振峰;王祥锋;韩万金;;冲角变化对涡轮静叶栅流场的影响[J];实验流体力学;2009年04期
6 顾中华,韩万今,周逊,芦文才,王仲奇;冲角对涡轮低压导向器气动特性影响的实验研究[J];航空动力学报;2000年02期
7 陈绍文;卞兆喜;刘顺隆;;冲角对高负荷正弯叶栅壁面静压影响的实验研究[J];热能动力工程;2008年05期
8 王祥锋;颜培刚;黄洪雁;韩万金;;汽轮机静叶栅变冲角性能的实验研究[J];实验流体力学;2011年06期
9 曹起鹏,杨\炆，
本文编号：2219560
本文链接：https://www.wllwen.com/kejilunwen/hangkongsky/2219560.html
