Numerical prediction of cooling performance sensitivity of 1st stage nozzle guide vane under aerothermal conditions

CORC > 力学研究所 > 中国科学院力学研究所 > 流固耦合系统力学重点实验室(2012-)

	Numerical prediction of cooling performance sensitivity of 1st stage nozzle guide vane under aerothermal conditions
	Prapamonthon P ; Yin B(银波); Yang GW(杨国伟); Zhang MH(张莫晗)
	2019
会议日期	December 5, 2019 - December 6, 2019
会议地点	Chennai, Tamil Nadu, India
关键词	Aerothermal condition Cooling effectiveness Cooling performance Thermal sensitivity Turbine vane
英文摘要	To obtain high power and thermal efficiency, the 1st stage nozzle guide vanes of a high-pressure turbine need to operate under serious circumstances from burned gas coming out of combustors. This leads to vane suffering from effects of high thermal load, high pressure and turbulence, including flow-separated transition. Therefore, it is necessary to improve vane cooling performance under complex flow and heat transfer phenomena caused by the integration of these effects. In fact, these effects on a high-pressure turbine vane are controlled by several factors such as turbine inlet temperature, pressure ratio, turbulence intensity and length scale, vane curvature and surface roughness. Furthermore, if the vane is cooled by film cooling, hole configuration and blowing ratio are important factors too. These factors can change the aerothermal conditions of the vane operation. The present work aims to numerically predict sensitivity of cooling performances of the 1st stage nozzle guide vane under aerodynamic and thermal variations caused by three parameters i.e. pressure ratio, coolant inlet temperature and height of vane surface roughness using Computational Fluid Dynamics (CFD) with Conjugate Heat Transfer (CHT) approach. Numerical results show that the coolant inlet temperature and the vane surface roughness parameters have significant effects on the vane temperature, thereby affecting the vane cooling performances significantly and sensitively. Copyright © 2019 ASME.
会议录	ASME 2019 Gas Turbine India Conference, GTINDIA 2019
语种	英语
URL标识	查看原文
ISBN号	9780791883525
内容类型	会议论文
源URL	[http://dspace.imech.ac.cn/handle/311007/85114]
专题	力学研究所_流固耦合系统力学重点实验室(2012-)
作者单位	1.School of Engineering Science, University of Chinese Academy of Sciences, Beijing, 100049, China 2.Department of Aeronautical Engineering, International Academy of Aviation Industry, King Mongkut’s Institute of Technology, Ladkrabang, Bangkok, 10520, Thailand 3.Key Laboratory for Mechanics in Fluid Solid Coupling Systems, Institute of Mechanics, Chinese Academy of Sciences, Beijing, 100190, China
推荐引用方式 GB/T 7714	Prapamonthon P,Yin B,Yang GW,et al. Numerical prediction of cooling performance sensitivity of 1st stage nozzle guide vane under aerothermal conditions[C]. 见:. Chennai, Tamil Nadu, India. December 5, 2019 - December 6, 2019.