Study on the Influence of Blade Roughnesson Axial Flow Compressor Stage Performance

Abstract

Abstract.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.

Performance Evaluation of Transonic Axial Flow Compressor under Distorted Conditions by Groove Casing Technique with Tip Injection and Surface Roughness Effects

“…Blades of rotors and stators were set to possess surface roughness of 40 µm. The remaining parameters used were same as that used in baseline analysis and tip injection combined with groove casing analysis, respectively [32,33]. Simulation results are validated with the experimental data [35].…”

“…Table 5 represents the surface roughness flow simulation on the compressor stage both rotor and stator blades with a smooth surface and rough surface 40 µm. The baseline model was subjected to 40 µm roughness as given by Xudong Shi et al [32]. Simulations are performed for 30, 40, 50 and 60 µm different rough surface values.…”

“…Therefore, it is clear that at higher erosion angle, maximum erosion is possible on the leading edge of the blades. Xudong Shi et al [32] and Nicola Aldi et al [33] conducted an investigation on the axial flow compressor to study the effect of surface roughness on its aerodynamic performance. The results show a significant decrement in the performance of the compressor's efficiency and pressure ratio.…”

Numerical simulation of low reynolds number 2-d rough blade compressor cascade

“…In past research, researchers often used two methods to study the effect of roughness on the compressor cascade. Mirko Morini et al (Morini et al, 2011;Nicola et al, 2014;Shi et al, 2017) used the wall equation to simulate the roughness on the compressor blade, while Sun Hai-Ou et al (Sun et al, 2021) changed the profile of the blade.…”