Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades

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	Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades
其他题名	Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades
	Xu Han 1; Chang Hao 2; Jin Donghai 1; Gui Xingmin 1
	2017
发表期刊	Chinese Journal of Aeronautics
ISSN	1000-9361
卷号	30 期号:5 页码:1651-1659
摘要	The circumferentially averaged equation of the inlet flow radial equilibrium in axial compressor was deduced. It indicates that the blade inlet radial pressure gradient is closely related to the radial component of the circumferential fluctuation (CF) source item. Several simplified cascades with/without aerodynamic loading were numerically studied to investigate the effects of blade bowing on the inlet flow radial equilibrium. A data reduction program was conducted to obtain the CF source from three-dimensional (3D) simulation results. Flow parameters at the passage inlet were focused on and each term in the radial equilibrium equation was discussed quantitatively. Results indicate that the inviscid blade force is the inducement of the inlet CF due to geometrical asymmetry. Blade bowing induces variation of the inlet CF, thus changes the radial pressure gradient and leads to flow migration before leading edge (LE) in the cascades. Positive bowing drives the inlet flow to migrate from end walls to mid-span and negative bowing turns it to the reverse direction to build a new equilibrium. In addition, comparative studies indicate that the inlet Mach number and blade loading can efficiently impact the effectiveness of blade bowing on radial equilibrium in compressor design.
其他摘要	The circumferentially averaged equation of the inlet flow radial equilibrium in axial compressor was deduced. It indicates that the blade inlet radial pressure gradient is closely related to the radial component of the circumferential fluctuation (CF) source item. Several simplified cascades with/without aerodynamic loading were numerically studied to investigate the effects of blade bowing on the inlet flow radial equilibrium. A data reduction program was conducted to obtain the CF source from three-dimensional (3D) simulation results. Flow parameters at the passage inlet were focused on and each term in the radial equilibrium equation was discussed quantitatively. Results indicate that the inviscid blade force is the inducement of the inlet CF due to geometrical asymmetry. Blade bowing induces variation of the inlet CF, thus changes the radial pressure gradient and leads to flow migration before leading edge (LE) in the cascades. Positive bowing drives the inlet flow to migrate from end walls to mid-span and negative bowing turns it to the reverse direction to build a new equilibrium. In addition, comparative studies indicate that the inlet Mach number and blade loading can efficiently impact the effectiveness of blade bowing on radial equilibrium in compressor design.
关键词	Axial compressor Bowing Cascade Circumferential fluctuation Inlet flow Radial equilibrium Motor vehicles. Aeronautics. Astronautics TL1-4050
收录类别	CSCD
语种	英语
资助项目	[National Natural Science Foundation of China] ; [National Basic Research Program of China] ; [Beijing Natural Science Foundation]
CSCD记录号	CSCD:6089584
引用统计	被引频次：5[CSCD] [CSCD记录]
文献类型	期刊论文
条目标识符	http://ir.imr.ac.cn/handle/321006/154041
专题	中国科学院金属研究所
作者单位	1.北京航空航天大学 2.中国科学院金属研究所
推荐引用方式 GB/T 7714	Xu Han,Chang Hao,Jin Donghai,et al. Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades[J]. Chinese Journal of Aeronautics,2017,30(5):1651-1659.
APA	Xu Han,Chang Hao,Jin Donghai,&Gui Xingmin.(2017).Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades.Chinese Journal of Aeronautics,30(5),1651-1659.
MLA	Xu Han,et al."Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades".Chinese Journal of Aeronautics 30.5(2017):1651-1659.