TY  - JOUR
AB  - Purpose This paper aims to present the designing and investigating various types of impulse blade profiles to find the optimal profile that has better performance than the first or original blade. The studied model is a turbine with an output power below 1 MW and a large pressure ratio up to 20, which is used to gain relatively high specific work output. As a result of its low mass flow rate, the turbine is used under partial-admission conditions. The turbine’s stator is a group of convergence–divergence nozzles that provide supersonic flow.Design/methodology/approach More than 10 types of two-dimensional blade profiles were designed using the developed preliminary design calculations and numerical analysis. The numerical results are validated using the existing experimental results. Finally, the case with improved performance is introduced as the final optimum case.Findings It was found that the performance parameters such as efficiency, power and torque are increased by more than 8% in the selected best model, in comparison with the original model. Moreover, the total pressure loss is 12% decreased for the selected model. Finally, the selected profile with superior performance is proposed.Originality/value Simultaneous numerical tests are conducted to examine the interaction of different supersonic blade profiles with the partially injected flow to the rotor.
VL  - 92
IS  - 6
SN  - 1748-8842
DO  - 10.1108/AEAT-06-2019-0132
UR  - https://doi.org/10.1108/AEAT-06-2019-0132
AU  - Togh Reza Aghaei
AU  - Karimi Mohammad Mahdi
PY  - 2020
Y1  - 2020/01/01
TI  - Finding an optimal blade-profile to improving the performance of partially admitted turbines
T2  - Aircraft Engineering and Aerospace Technology
PB  - Emerald Publishing Limited
SP  - 863
EP  - 877
Y2  - 2024/04/26
ER  -