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asadolahi ghahie, A., aghai togh, R., yousefi, M. (2019). Numerical Investigation of the Effect of Rotor Sweep on the Performance of One- Stage Transonic Compressor of an Industrial Gas Turbine. Electronic and Cyber Defense, 8(1), 143-160.
abdollah asadolahi ghahie; reza aghai togh; meysam yousefi. "Numerical Investigation of the Effect of Rotor Sweep on the Performance of One- Stage Transonic Compressor of an Industrial Gas Turbine". Electronic and Cyber Defense, 8, 1, 2019, 143-160.
asadolahi ghahie, A., aghai togh, R., yousefi, M. (2019). 'Numerical Investigation of the Effect of Rotor Sweep on the Performance of One- Stage Transonic Compressor of an Industrial Gas Turbine', Electronic and Cyber Defense, 8(1), pp. 143-160.
asadolahi ghahie, A., aghai togh, R., yousefi, M. Numerical Investigation of the Effect of Rotor Sweep on the Performance of One- Stage Transonic Compressor of an Industrial Gas Turbine. Electronic and Cyber Defense, 2019; 8(1): 143-160.

Numerical Investigation of the Effect of Rotor Sweep on the Performance of One- Stage Transonic Compressor of an Industrial Gas Turbine

مکانیک سیالات و آیرودینامیک
Article 11, Volume 8, Issue 1 - Serial Number 23, July 2019, Pages 143-160    PDF (1.58 M)
Document Type: Original Article
Authors
abdollah asadolahi ghahie* 1; reza aghai togh2; meysam yousefi2
1sanAt havapeimai
2azad olom tahghighat
Receive Date: 22 February 2019,  Revise Date: 19 April 2019,  Accept Date: 25 July 2019 
Abstract
Compressor is one of the most parts of gas turbines that increase the pressure in the cycle of gas turbine. In regard to the fact that flow in compressor is influenced by positive pressure gradient and  the nature of the flow at compressor is very complicated, exact aerodynamic design of compressor blades (whose task is transmission work to the flow) is vital. In this project, effects of maximum changes of backward and forward sweeps of a rotor blade of special transonic compressor over the performance curves, including the efficiency and pressure ratio, has surveyed.  For 3d simulation of complex flow field of axial compressor the CFX software was utiliged. The results were compared with prior activities and soundness of that was certified then changes that above mentioned was exerted over the first stage rotor and change effects on performance parameters has surveyed. Results show us exert of changes that above mentioned causes to reduction of efficiency but if just the increase of pressure ratio intended the efficiency rises obviously.
Keywords
Axial Compressor; Backward Sweep; Forward Sweep; CFD; Numerical Solution
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