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Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades
Alternative TitleBlade bowing effects on radial equilibrium of inlet flow in axial compressor cascades
Xu Han1; Chang Hao2; Jin Donghai1; Gui Xingmin1
2017
Source PublicationChinese Journal of Aeronautics
ISSN1000-9361
Volume30Issue:5Pages:1651-1659
AbstractThe 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.
Other AbstractThe 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.
KeywordAxial compressor Bowing Cascade Circumferential fluctuation Inlet flow Radial equilibrium Motor vehicles. Aeronautics. Astronautics TL1-4050
Indexed ByCSCD
Language英语
Funding Project[National Natural Science Foundation of China] ; [National Basic Research Program of China] ; [Beijing Natural Science Foundation]
CSCD IDCSCD:6089584
Citation statistics
Cited Times:1[CSCD]   [CSCD Record]
Document Type期刊论文
Identifierhttp://ir.imr.ac.cn/handle/321006/154041
Collection中国科学院金属研究所
Affiliation1.北京航空航天大学
2.中国科学院金属研究所
Recommended Citation
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.
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