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.
Highlights
The performance deterioration of compressor is directly connected to aircraft safety and efficiency, it has become more and more important to study the factors causing compressor performance deterioration and to explore the laws of performance deterioration
From the view of boundary layer development, he discovered that it can be divided into three regimes to study the influence of roughness on pipe flow according to Reynold number value, pipe pressure loss coefficient depends on Reynold number and roughness height under low Reynold number condition, whereas friction resistance of pipe wall depends only on sand-grain diameter under high Reynold number condition
A geometrical modelling of NASA Stage36 based on original blade profile and flow path data is realized and model validation is conducted
Summary
The performance deterioration of compressor is directly connected to aircraft safety and efficiency, it has become more and more important to study the factors causing compressor performance deterioration and to explore the laws of performance deterioration. Based on k- turbulence model, Mirko Morini et al [7] chose NASA Stage 37 to study fouling influence on performance deterioration and flow blockage, according to their research, reductions in the flow coefficient and in the pressure coefficient were found to be the same order of magnitude of experimental results. Based on kturbulence model, Shi Hui et al [8,9] chose NASA Stage 35 to study the influence of adding thickness and roughness caused by fouling on compressor stage performance, and it shows that the influence of roughness applied on rotor is nearly the same as that on whole stage. Different levels of surface roughness are considered to study fouling effects on compressor stage performance under different work points, and variations of input power and Mach number are discussed
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
