The goal of this paper is to calculate the blade design of axial flow compressor. Main objective of the compressor usage is to compress the fluid and to deliver higher pressure than its original pressure. So, the stagnation pressure ratio and overall pressure ratio are calculated in this paper. Blade mean diameter is 0.295 m for all five stages.
Khema Theint (2018); Five-Stage Axial Flow Compressor for Gas Turbine; International Journal of Scientific and Research Publications (IJSRP)
8(9) (ISSN: 2250-3153), DOI: http://dx.doi.org/10.29322/IJSRP.8.9.2018.p8129