| Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades | |
| Alternative Title | Blade bowing effects on radial equilibrium of inlet flow in axial compressor cascades |
| Xu Han1; Chang Hao2; Jin Donghai1; Gui Xingmin1 | |
| 2017 | |
| Source Publication | Chinese Journal of Aeronautics
 |
| ISSN | 1000-9361 |
| Volume | 30Issue:5Pages:1651-1659 |
| Abstract | 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. |
| Other Abstract | 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. |
| Keyword | Axial compressor Bowing Cascade Circumferential fluctuation Inlet flow Radial equilibrium Motor vehicles. Aeronautics. Astronautics TL1-4050 |
| Indexed By | CSCD |
| Language | 英语 |
| Funding Project | [National Natural Science Foundation of China] ; [National Basic Research Program of China] ; [Beijing Natural Science Foundation] |
| CSCD ID | CSCD:6089584 |
| Citation statistics |
Cited Times:1[CSCD]
[CSCD Record]
|
| Document Type | 期刊论文 |
| Identifier | http://ir.imr.ac.cn/handle/321006/154041 |
| Collection | 中国科学院金属研究所 |
| Affiliation | 1.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. |
| Files in This Item: | There are no files associated with this item. | |||||
Items in the repository are protected by copyright, with all rights reserved, unless otherwise indicated.
Edit Comment