跨音速流动中涡轮动叶叶顶的气膜冷却特性分析
2024,46(2):153-161
张博伦
国防科技大学 空天科学学院, 湖南 长沙 410073，zhangbl_nudt@qq.com
夏军
国防科技大学 空天科学学院, 湖南 长沙 410073，putian9988@163.com
胡其高
国防科技大学 军政基础教育学院, 湖南 长沙 410073
朱惠人
西北工业大学 动力与能源学院, 陕西 西安 710129
国防科技大学 空天科学学院, 湖南 长沙 410073，zhangbl_nudt@qq.com
夏军
国防科技大学 空天科学学院, 湖南 长沙 410073，putian9988@163.com
胡其高
国防科技大学 军政基础教育学院, 湖南 长沙 410073
朱惠人
西北工业大学 动力与能源学院, 陕西 西安 710129
摘要：
为了掌握跨音速流动中涡轮动叶叶顶气膜冷却特性,采用压敏漆测试技术来研究叶顶间隙高度和质量流量比对叶顶气膜冷却特性的影响规律。研究结果表明:在小质量流量比条件下,增加叶顶间隙高度能够有效改善叶顶中弦区域的气膜覆盖,然而当质量流量较大时,叶顶间隙高度变化对叶顶中弦区域的气膜冷却效率分布影响并不明显；在小叶顶间隙高度条件下,随着质量流量比增加,叶顶中弦区域冷气覆盖效果逐渐变差,在大叶顶间隙高度条件下,仅当质量流量比从0.1%+0.05%增加到0.14%+0.07%时,叶顶中弦区域的冷气覆盖效果才有所改善。
为了掌握跨音速流动中涡轮动叶叶顶气膜冷却特性,采用压敏漆测试技术来研究叶顶间隙高度和质量流量比对叶顶气膜冷却特性的影响规律。研究结果表明:在小质量流量比条件下,增加叶顶间隙高度能够有效改善叶顶中弦区域的气膜覆盖,然而当质量流量较大时,叶顶间隙高度变化对叶顶中弦区域的气膜冷却效率分布影响并不明显；在小叶顶间隙高度条件下,随着质量流量比增加,叶顶中弦区域冷气覆盖效果逐渐变差,在大叶顶间隙高度条件下,仅当质量流量比从0.1%+0.05%增加到0.14%+0.07%时,叶顶中弦区域的冷气覆盖效果才有所改善。
基金项目：
国家部委基金资助项目(ZZKY-JJ-21-01)；青年自主创新科学基金资助项目(ZK2023-039)
国家部委基金资助项目(ZZKY-JJ-21-01)；青年自主创新科学基金资助项目(ZK2023-039)
Film cooling characteristics analysis of turbine blade tip in transonic flow
ZHANG Bolun
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,zhangbl_nudt@qq.com
XIA Jun
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,putian9988@163.com
HU Qigao
College of Basic Education, National University of Defense Technology, Changsha 410073, China
ZHU Huiren
School of Power and Energy, Northwestern Polytechnical University, Xi′an 710129, China
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,zhangbl_nudt@qq.com
XIA Jun
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,putian9988@163.com
HU Qigao
College of Basic Education, National University of Defense Technology, Changsha 410073, China
ZHU Huiren
School of Power and Energy, Northwestern Polytechnical University, Xi′an 710129, China
Abstract：
To grasp the film cooling characteristics of the turbine blade tip in transonic flow, the pressure sensitive paint technique was used to experimentally obtain the effects of the tip clearance gap and mass flow ratio on the film cooling performance of the blade tip. The results indicate that, under conditions of low mass flow ratio, increasing the tip clearance height effectively enhances the film coverage in the mid-chord region of the blade tip. However, when the mass flow ratio is high, changes in the tip clearance height have an insignificant effect on the distribution of film cooling efficiency in this region. Under conditions of small tip clearance heights, the cooling coverage in the mid-chord region deteriorates gradually as the mass flow ratio increases. In contrast, with larger tip clearance heights, an improvement in cooling coverage is only observed when the mass flow ratio increases from 0.1%+0.05% to 0.14%+0.07%.
To grasp the film cooling characteristics of the turbine blade tip in transonic flow, the pressure sensitive paint technique was used to experimentally obtain the effects of the tip clearance gap and mass flow ratio on the film cooling performance of the blade tip. The results indicate that, under conditions of low mass flow ratio, increasing the tip clearance height effectively enhances the film coverage in the mid-chord region of the blade tip. However, when the mass flow ratio is high, changes in the tip clearance height have an insignificant effect on the distribution of film cooling efficiency in this region. Under conditions of small tip clearance heights, the cooling coverage in the mid-chord region deteriorates gradually as the mass flow ratio increases. In contrast, with larger tip clearance heights, an improvement in cooling coverage is only observed when the mass flow ratio increases from 0.1%+0.05% to 0.14%+0.07%.
收稿日期：
2022-01-12
2022-01-12
