• Kudale Shubham Nandu
• Dr. M. K. Nalawade

Axial compressor is prime device in concern with gas turbine engines. This type of axial compressors used in aircraft, helicopters, hovercraft, ships, hydrofoils, cruise missiles, small gas turbine turbofan and turboprop engines. In this paper single stage compressor is designed at rotational speed of 36000 rpm, mass flow rate of 6.8 kg/s, inlet total pressure and total temperature of 1.01325 bar and 288.3K, pressure ratio and isentropic efficiency of 2.5 and 87% respectively as design specification. Design result and analysis result are compared. To verifying the preliminary design results analysis is done in AxSTREAM software.In this work, total pressure at rotor inlet and total pressure at outlet is used to carry out analysis. In the numerical simulation results the mass flow rate and total pressure ratio are found as 6.82 kg/s and 2.52 bar. The efficiency obtained from simulation is 90.145%.

Axial flow compressor, Meanline Design of compressor, AxMap, Numerical Analysis

"Numerical analysis of axial flow compressor", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.5, Issue 6, page no.541-547, June-2018, Available :http://www.jetir.org/papers/JETIR1806469.pdf

"Numerical analysis of axial flow compressor", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.5, Issue 6, page no. pp541-547, June-2018, Available at : http://www.jetir.org/papers/JETIR1806469.pdf