Design of Multi-Stage Axial Flow Compressor and Validation using Numerical Simulations
Cheke K. D.1, Kamble A.G2
1Cheke K. D.*, Student, Heat Power, School of Mechanical and Civil Engineering, MIT Academy of Engineering, Alandi, Pune. Dist. Pune, Maharashtra, India.
2Kamble A.G., Associate Professor, School of Mechanical and Civil Engineering, MIT Academy of Engineering, Alandi, Pune. Dist. Pune, Maharashtra, India
Manuscript received on November 15, 2019. | Revised Manuscript received on 23 November, 2019. | Manuscript published on December 10, 2019. | PP: 2320-2325 | Volume-9 Issue-2, December 2019. | Retrieval Number: B7455129219©BEIESP | DOI: 10.35940/ijitee.B7455.129219
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: The optimum yield of gas turbine engines has so far been driven on and around the operational efficiency of the compressor and in essence around the efficiency of the compressor blade. The efficacy of a compressor is ascertained substantially by the smoothness of the air flowing through it. In this present work, a multi-stage axial compressor in the Turbojet engine with an application for propulsion is designed based on thermodynamic calculations. The calculations were carried out employing the principles of thermodynamics, and aerodynamics along the mean streamline based on the technique of a velocity triangle in the lack of inlet guide vanes. The coordinates for the blade profile has been calculated on and around the premise of the calibrated blade base profile. The model for the seven-stage axial flow compressors based on thermodynamic calculations was devised and analyzed utilizing computational fluid dynamics methodology. The multiple reference frame approach was used to represent the impact of both rotating and stationary components and the simulation for the first stage was conducted using a periodic approach. For the intent of the verification, a comparison was made between the analytical values and the simulated values and the variation between these values was found to be 16.7%. Validation results demonstrate that the proposed method is valid and can be used for multi-stage axial compressor design and performance evaluation.
Keywords: Aerodynamics, Axial Flow, Compressor, Computational Fluid Dynamics, etc.
Scope of the Article: Computational Biology