Document Type : Research Note


1 Assistant Professor . Department of Aerospace Engineering, Engineering Faculty, Science and Resarch Branch, Islamic Azad University, Tehran,Iran.

2 M.Sc. Department of Aerospace Engineering, Engineering Faculty, Science and Resarch Branch, Islamic Azad University, Tehran, Iran.

3 Assistant Professor. Department Mechanics, Electrical and Computer, Engineering Faculty, Science and Resarch Branch, Islamic Azad University, Tehran, Iran.


This research aims to improve aerodynamic performance of a radial gas microturbine from input to output, so that the best case can be selected. In this work, ANSYS CFX software was used. First, using one-dimensional model, different states were investigated and the best mode was selected. Then, by solving the governing equations, the efficiency of the designed turbine was obtained. This work combines computational work and experimental design to find the best blade profile for optimal operation. The geometrical parameters of rotor blade were considered as variable factors. Four levels were selected for each factor according to Credential references. According to the number of parameters and the number of levels determined, the appropriate orthogonal table can be selected and again numerically simulated with CFX software. The optimally designed rotor offers the highest efficiency and power output compared to the original rotor, such that the output power of the designed rotor is increased by 7.3%. 


Main Subjects

[1] Pakle, S. and Jiang, K., “Design of Double Curvature Radial Turbine Blades for a Micro Gas Turbine”, Applied Mathematical Modelling, Vol. 67,  pp. 529-548, 2019.
[2] Capata, R. and Achille, M., “Design and Optimization of Fuel Injection of a 50 kW Micro Turbogas”, Designs, Vol. 2, No. 2, pp. 14-25, 2018.
[3] Zheng, Y., Hu, D., Cao, Y., and Dai, Y., “Preliminary Design and Off-Design Performance Analysis of an Organic Rankine Cycle Radial-Inflow Turbine Based on Mathematic Method and CFD Method”,. Applied Thermal Engineering, Vol. 112,  pp. 25-37, 2017.
[4] Taghavi-Zenouz, R. and Abbasi, S., “Alleviation of Spike Stall in Axial Compressors Utilizing Grooved Casing Treatment”, Chinese Journal of Aeronautics, Vol. 28, No. 3,  pp. 649-658, 2015.
[5] Neshat, M.A., Akhlaghi, M., Fathi, A., and Khaledi,H., “Investigating the Effect of Blade Sweep and Lean in One Stage of an Industrial Gas Turbineʾs Transonic Compressor”, Propulsion and Power Research, Vol. 4, No. 4, pp. 221-229, 2015
[6] Aghaei-Tog, R., Mesgharpoor-Tousi, A., and Soltani, M., “Design and CFD Analysis of Centrifugal Compressor for a Microgasturbine”, Aircraft Engineering and Aerospace Technology, Vol. 79, No. 2,  pp. 137-143, 2007.
[7] Aghaei-Tog, R., Ghaffari, J., Mesgharpoor-Tousi, A., and Boroumand, M., “Numerical Study of the Effects of Blade Angles on the Performance of Centrifugal Impellers”, Journal of Aerospace Mechanics, Vol. 8, No. 2,  pp. 93-100, 2012 (In Persian).
[8] Kazuo Matsuura, C.K., Yoshiki, H., Matsuo, E., Ikeda, H.K.N., and Sapkota1, R., “Prototyping of Small-sized Two-dimensional Radial Turbines”, The International Gas Turbine Conference, Tokyo, Japan, 2003.
[9] Afghari, S.M.R, Mostofizade, A., Rezvani, M., and Vaziri, M.A., “One-dimensional Aerodynamic Design of Radial Flow Turbine Impelle”, The First Conference of the Iranian Aerospace Propulsion Association, Isfahan University of Technology, Isfahan, Iran, 2013 (In Persian).
[10] Nikouei, S. and Hasani, B., “Optimization of the Shape of Bifurcated Shells, Using Fully Analyzed Sensitivity Analysis and Using Isogeometric Method”, The 4th National Conference on Mechanical and Aerospace Engineering, Tehran, Iran, 2019 (In Persian).
[11] Zahed, A.H. and Bayomi, N.N.,, “Radial Turbine Design Process", ISESCO JOURNAL of Science and Technology, Vol. 11, No. 19, pp. 9-22, 2015.