سال انتشار: ۱۳۹۱

محل انتشار: بیستمین کنفرانس سالانه مهندسی مکانیک

تعداد صفحات: ۵

نویسنده(ها):

Ashkan Moshkelgosha – MSc. Student, Amirkabir University of Technology, Aerospace Department
Majid Asli – MSc. Student, Amirkabir University of Technology, Aerospace Department
Abolqasem M. Tousi – Associate Professor, Amirkabir University of Technology, Aerospace Department

چکیده:

A computer code is presented for off-design performance prediction of axial-flow compressors and fans. Stage and compressor performance is obtained by a stage-stacking method that uses representative velocity diagrams at rotor inlet and outlet mean line radius. The code has options for: (1) direct user input or calculation of non-dimensional stage characteristics; (2) adjustment of stage characteristics for off-design speed; (3) calculation of different source of loss in design and off-design condition. New blading concepts as used in modern transonic axial-flow compressors require improved loss and deviation angle correlations. The new model presented in this paper incorporates several elements and treats blade-row flows have both subsonic and transonic inlet conditions .Correlations from experimental data are used to model real flow conditions. Then Calculations are compared with experimental data. Although this type of flow analysis is a gross simplification of a complex three-dimensional system, which can now be modeled more accurately by many of today’s computational fluid dynamics (CFD) packages, it does offer the advantages of simple input requirements and fast convergence times.