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Numerical Analysis of Flow in Ultra Micro Centrifugal Compressor -Influence of Meridional Configuration

Numerical Analysis of Flow in Ultra Micro Centrifugal Compressor -Influence of Meridional Configuration

作     者:Masanao Kaneko Hoshio Tsujita Toshiyuki Hirano 

作者机构:Graduate School of EngineeringHosei University Department of Mechanical EngineeringFaculty of Science and EngineeringHosei University Production Systems Engineering CourseTokyo Metropolitan College of Industrial Technology 

出 版 物:《Journal of Thermal Science》 (热科学学报(英文版))

年 卷 期:2013年第22卷第2期

页      面:111-116页

核心收录:

学科分类:080704[工学-流体机械及工程] 08[工学] 0807[工学-动力工程及工程热物理] 

主  题:Ultra Micro Centrifugal Compressor Two-dimensional Blade Gas Turbine Numerical Analysis 

摘      要:A single stage ultra micro centrifugal compressor constituting ultra micro gas turbine is required to operate at high rotational speed in order to achieve the pressure ratio which establishes the gas turbine cycle. As a conse- quence, the aerodynamic losses can be increased by the interaction of a shock wave with the boundary layer on the blade surface. Moreover, the centrifugal force which exceeds the allowable s^ress of the impeller material can act on the root of blades. On the other hand, the restrictions of processing technology for the downsizing of im- peller not only relatively enlarge the size of tip clearance but also make it difficult to shape the impeller with the i three-dimensional blade. Therefore, it is important to establish the design technology for the impeller with the two-dimensional blade which possesses the sufficient aerodynamic performance and enough strength to bear the centrifugal force caused by the high rotational speed. In this study, the flow in two types of impeller with the two-dimensional blade which have different meridional configuration was analyzed numerically, The computed results clarified the influence of the meridional configuration on the loss generations in the impeller passage.

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