Journal of Dalian Maritime University >
2017 , Vol. 43 >Issue 3: 71 - 77
DOI: https://doi.org/10.16411/j.cnki.issn1006-7736.2017.03.012
Numerical study on aerodynamic characteristics of axial compressor cascade
Received date: 2017-03-27
Revised date: 2017-04-19
Online published: 2017-04-19
The axial compressor DMU37 rotor blade 5% typical section blade was taken as the study object, the outlet flow field loss and aerodynamic characteristics of the cascade under different incidence angle and inlet isentropic Mach numbers were calculated and analyzed by using Fluent software. Results show that under the same impact angle, the increase of the inlet isentropic Mach number increases the blade load and the capacity of expanding pressure, but also increase the outlet total pressure loss, and the stall angle becomes smaller. For the same inlet Mach number, the total pressure loss at the outlet decreases first and then increases with the increase of the incidence angle, and the total pressure loss at the angle of -4° is the smallest. At the same time, it is verified that the loss characteristics of inlet isentropic Mach number and incidence angle of the axial compressor cascade are similar. Besides, the influence of change of the inlet Mach number and the angle of incidence on the wall area is lager.
Key words： axial compressor; plane cascade; grid distribution; numerical simulation
LI Da-chun , YANG Ling , GAO Yu , ZHONG Jing-jun . Numerical study on aerodynamic characteristics of axial compressor cascade[J]. Journal of Dalian Maritime University, 2017 , 43(3) : 71 -77 . DOI: 10.16411/j.cnki.issn1006-7736.2017.03.012
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