Author:
Abdelwahid Mohammed Balla,Musa Eimad Eldin Elhadi,Taha Hazim Mohammed,Hamed Sohaib Osman,Alhassan Esra Abdulrahman Mohamed
Abstract
Erosion of compressor blades due to operation in dusty environments is a serious problem for the manufacturers and users of gas turbine engines, because of significant degradations in performance. This study has been devoted to estimating the change of performance parameters of an axial compressor stage due to erosive deterioration. The influence of erosion considered as consequences of a reduction of rotor blade airfoils, and an increase of tip clearance. The results of this study obtained using the CFD code “NUMECA Fine/Turbo”. This CFD code is a steady, quasi-three-dimensional Reynolds Averaged Navier-Stokes (RANS) solver. A Spalart-Allmaras turbulence model is used. The compressor stage parameters presented for three rotational speeds. Proposed a new approach to consider the changes of geometric parameters of blades due to erosion. Presented an analysis of the effect of erosion and its individual consequences on the pressure ratio, isentropic efficiency and stability margin of the stage. The obtained results verified using an existing experimental data.
Reference7 articles.
1. Balan, C., Tabakoff W., Axial compressor performance deterioration. AIAA Paper. – 1984. No. 84-1208.
2. Singh D., Hamed A., Tabakoff W., Simulation of performance deterioration in eroded compressors. University of Cincinnati, Cincinnati, 45221, 1996.
3. Ghenaiet A.,. Tan C., Elder R., Prediction of an axial turbomachine performance degradation due to sand ingestion. Journal of power and energy, 2005, 219: 273.
4. Hamed A, Tabakoff W., Singh D., Modeling of compressor performance deterioration due to erosion. International Journal of Rotating Machinery. – 1998. – Vol. 4, No. 4. – pp. 243–248.
5. Schrade M., Staudacher S., High-speed test rig for the investigation of erosion Damage of axial compressor blades. University of Stuttgart, Germany, 2014.