Analysis and Control of Unsteady Three-Dimensional Vortical Flow Structure in Complex Flow Fields
Analysis and Control of Unsteady Three-Dimensional Vortical Flow Structure in Complex Flow Fields
批准号:
13305014
负责人:
INOUE Masahiro
金额:
$34.53万
依托单位:
依托单位国家:
日本
项目类别:
Grant-in-Aid for Scientific Research (A)
财政年份:
2001
资助国家:
日本
项目状态:
已结题
起止时间:
2001 至 2003
中文摘要
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英文摘要
A transient flow phenomenon of rotating stall inception in axial flow compressor rotors has been investigated by experimental fluid dynamics(EFD) and computational fluid dynamics(CFD). Instantaneous distributions of the casing wall pressure were obtained experimentally by 'Synchronous Field Measurement' using time interpolation. Unsteady three-dimensional separated and vortical Flow structure was captured by unsteady Navier-Stokes flow simulation. To elucidate the unsteady flow phenomenon at the stall inception, vortex structures and separation topology were identified by the critical point theory.In the axial compressor rotor with small tip clearance, the tip leakage vortex is so weak as to have little influence on the flow field. The leading edge separation dominates the rotating stall inception, which results in the short length-scale rotating stall. A short length-scale stall is of the part-span type occupying only a part of the annulus. Its cell structure consists of the tornado-l … More ike separation vortex linking the blade suction surface and casing wall boundary layers. The tornado-like separation vortex dominating the short length-scale stall cells has a large blockage effect. As the separation vortex grows and moves toward the pressure surface of the neighboring blade, it increases the incidence of the neighboring blade, thus bringing about a new leading edge separation on the neighboring blade. In the case of small clearance, the stall evolution depends on the stator-rotor gap. However, in the case of large clearance, there is little difference of the stall evolution among three gaps. From the measurement of the pressure and velocity field near the stall point, it seems that breakdown of tip leakage vortex occurs in the case of large clearance for three different gaps. It is supported from the axial velocity distribution at the rotor exit. From the pressure field traces just before the stall, we can find the distinctive flow phenomenon like rotating instability. The tip vortex plays a very important role for stall inception. Less
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Sung-Hyup KIM: "Numerical Analysis of Three-dimensional Vortical Flow Structure in a Propeller Fan"Proc. of the 5th International Symposium between Kyushu Univ. and Chungnam National Univ.. 148-153 (2001)
Sung-Hyup KIM:“螺旋桨式风扇三维涡流结构的数值分析”Proc。
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M.INOUE, M.FURUKAWA: "Physics of Tip Clearance Flow in Turbomachinery"Proceedings of 2002 ASME Joint US-European Fluids Engineering Conference, FEDSM. 31184 (2002)
M.INOUE、M.FURUKAWA:“涡轮机械中叶尖间隙流动的物理学”2002 年 ASME 美国-欧洲联合流体工程会议 (FEDSM) 论文集。
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Kazutoyo YAMADA: "Numerical Analysis of Rotating Stall Inception in an Axial Compressor Rotor"Proc. of the 5th JSME-KSME Fluids Engineering Conference. 1597-1602 (2002)
Kazutoyo YAMADA:“轴流压缩机转子中旋转失速起始的数值分析”Proc。
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Masahiro INOUE: "High-Frequency Instabilities in Axial Flow Compressors"Proceedings of the XI International Symposium on Airbreathing Engine. (CD-ROM). (2001)
Masahiro INOUE:“轴流压缩机中的高频不稳定性”第十一届吸气式发动机国际研讨会论文集。
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M.INOUE: "Vortex Consideration in Turbomachinery"Proceedings of The 2003 ASME/JSME Joint Fluids Engineering Conference. (CD-ROM). (2003)
M.INOUE:“涡轮机械中的涡流考虑”2003 年 ASME/JSME 联合流体工程会议论文集。
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