MATEC Web Conf.
Volume 108, 20172017 International Conference on Mechanical, Aeronautical and Automotive Engineering (ICMAA 2017)
|Number of page(s)||5|
|Section||Power System and Mechatronics|
|Published online||31 May 2017|
Study on the Influence of Blade Roughnesson Axial Flow Compressor Stage Performance
1 Electronic Information and Automation College, Civil Aviation University of China, China
2 Sino-European Institute of Aviation Engineering, Civil Aviation University of China, China
3 Mechanical Engineering Department, Civil Aviation University of China, China
4 Aviation Ground Special Equipments Research Base, Civil Aviation University of China, China
A typically actual inlet stage NASA Stage 36 is chosen to study the influence of surface roughness on axial compressor performance. Firstly, a geometry model is created by blade design software BladeGen using transferred coordinates data of blade profile and flow path. Secondly, validation of simulation model is conducted by comparing computational data and field experiment data. Lastly, SST k-ω turbulence model is chosen to study the influence of blade surface roughness on performance parameters under different work points. It shows that adding roughness will significantly reduce axial compressor stage’s adiabatic efficiency and total pressure ratio and cause stage characteristic map shift toward left. It should not neglect the influence of surface roughness of stator near stall region under 100% design speed; Mach number shows a big difference after adding surface roughness, and it can be considered as a sensibility parameter of roughness.
© The Authors, published by EDP Sciences, 2017
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