Improved streamline curvature throughflow method and its application in a bypass compression system design
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Improved streamline curvature throughflow method and its application in a bypass compression system design
Vol. 23, Issue 6, (2008)
作者机构:
1. 南京航空航天大学 能源与动力学院,南京,210016
2. 北京动力机械研究所,北京,100074
3. 哈尔滨工业大学 能源科学与工程学院,哈尔滨,150001
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Published:2008
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SHAO Fu-yong, YANG Jin-guang, LIU Zhen-de, et al. Improved streamline curvature throughflow method and its application in a bypass compression system design[J]. 2008, 23(6).
DOI:
SHAO Fu-yong, YANG Jin-guang, LIU Zhen-de, et al. Improved streamline curvature throughflow method and its application in a bypass compression system design[J]. 2008, 23(6).DOI:
Improved streamline curvature throughflow method and its application in a bypass compression system design
a streamline curvature throughflow method is presented in this paper.Improvements on streamline curvature calculation and relaxation factor determination were made
which enhanced the convergence
stability and precision of this method.Asimple blade force handling method was also proposed for computing flow field in the blade passage.At the same time
a bypass compression system computational method was integrated
which was stable and fast
and which enabled this method to solve arbitrary regions in bypass compression systems composed of fans and any type of high pressure compressors(axial-flow
centrifugal and combined type etc.).Finally this method was applied to an inverse design of a fan/high pressure compressor system
A Mass Addition Approach to the Bypass Turbomachine Through Flow Inverse Design Problem
Integrated throughflow design method of variable-cycle compression system
Prediction method on equivalent thermal conductivity coefficient of plain braided C/SiC composites material based on finite element method
Aerodynamic characteristics of design Mach number of 5 two-dimensional inlet with mixed-compression under typical condition
Computation of effect of different nozzle parameters on internal performance of convergent-divergent axisymmetric nozzle
Related Author
SHAN Peng
LIU Xi yang
LIU Bao-jie
JIA Shao-feng
YU Xian-jun
LU Si-da
GAO Xi-guang
SONG Ying-dong
Related Institution
Beijing University of Aeronautics and Astronautics
School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics
National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics
Collaborative Innovation Center for Advanced Aero-Engine
Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics