Modares Mechanical Engineering

Modares Mechanical Engineering

Optimization of CDA airfoil Geometry of a transonic Axial Compressor, using Genetic Algorithm And CFD

Document Type : Original Research

10.48311/mme.25.1.1
Abstract
In recent years, due to the optimal geometry and lower pressure drop, diffusion control vanes have significant applications, especially in the aviation industry and in subsonic and transsonic conditions. In the current research, the airfoil of the axial stator compressor section designed in the National Aerospace Laboratory of India has been selected as the basic geometry. The goal of optimization is to minimize the pressure drop of the entire fluid flow and consequently reduce the drop rate. The working method in this research is the change in the profile geometry of the blade by changing the parameters of the parsec method, which leads to the creation of new geometries at each stage of the code execution. The used optimization method is developed based on Genetic Algorithm. For the aerodynamic analysis of the generated geometry in each step and extracting the total pressure drop value, the MATLAB code is coupled with Ansys software and in each step, after numerical solution for each generated geometry, the total pressure drop value is extracted and returned to the code. Finally, the work output of the vane is more optimal and with a lower pressure drop, which is finally compared with the original vane and introduced as a suitable alternative. The total pressure drop between inlet and outlet in the optimized vane has decreased by 18% compared to the original vane, and the mass flow rate has also increased by 0.083 kg/s, which is a significant amount. The improvement of various aerodynamic characteristics such as Mach number distribution and pressure and drop coefficients can also be seen between the two basic and optimized blades, which is detailed at the end of the article
Keywords
Controlled Diffusion Airfoil
Geometry Optimization
Axial Compressor
Parsec method
genetic algorithm

Subjects

[1] R. Mukesh a,K. Lingadurai a, U. Selvakumar b, “Airfoil shape optimization using non-traditional optimization technique and its validation,” Journal of King Saud University – Engineering Sciences, pp. 191-197, 2013.
[2] Luesutthiviboon, Salil; Avallone, Francesco; Ragni, Daniele; Snellen, Mirjam, “Assessment of the Thin-airfoil Method for Predicting Steady Pressure Distribution on Partially-porous Airfoils,”th AIAA/CEAS Aeroacoustics Conference, Delft, The Netherlands, 2019.
[3] Nilesh P. Salunke, S. A. Channiwala, “Design and Analysis of a Controlled Diffusion Aerofoil Section for,” International Journal of Fluid Machinery and Systems, 2010, vol 3.
[4] Sang Huang, Cheng Wu yang,Xingen Lu, “Multipoint design optimization for a controlled diffusion airfoil compressor cascade”, The Journal of Mechanical Engineering Science, Volume234, issue11,2020.
[5] Lieblein, S., and Johnsen, I, “Resume of Transonic-Compressor Research at NACA Lewis Laboratory,” Journal of Engineering for Power, p. 219–234, 1961.
[6] Johnsen, I., and Bullock, R., “Aerodynamical Design of Axial-Flow Compressors,” NASA, 1965.
[7] Hobbs, D., andWeingold, H., “Development of Controlled Diffusion Airfoils for Multistage Compressor Application,” ASME 1983 International Gas Turbine Conference and Exhibit, American Society of Mechanical Engineers., 1983.
[8] K¨oller, U., M¨onig, R., K¨usters, B., and Schreiber, H.-A., “Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part I: Design and Optimization,” Journal of Turbomachinery, vol.122 (3), pp. 397-405, 2000.
[9] K¨usters B., Schreiber H.-A., K¨oller U., and M¨onig R., “Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part II: Experimental and TheoreticalAnalysis.,” Journal of Turbomachinery, vol.122 (3), p. 406–414, 2000.
[10] Aulich M., Voss C., and Raitor T.,., “Optimization Strategies demonstrated on a Transonic Centrifugal Compressor.,” ISROMAC 15, japan, 2014.
[11] Nilesh P. Salunke, S. A. Channiwala, “Design and Analysis of a Controlled Diffusion Aerofoil Section for an Axial Compressor Stator and Effect of Incidence Angle and Mach No. on Performance of CDA,” International Journal of Fluid Machinery and Systems, , No. 1, January-March 2010.
[12] Salunke, N. P., Juned Ahamad, R., and Channiwala, S., “Airfoil parameterization techniques: A review,” American Journal of Mechanical Engineering, Vol. 2, No. 4, pp. 99-102, 2014.
[13] Hajian, R., and Jaworski, J. W, “The steady aerodynamics of aerofoils with porosity gradients,” Proc. R. Soc. A, No.2205, p. 20170266, 2017.
[14] R. Mukesh a,*, K. Lingadurai a, U. Selvakumar b, “Airfoil shape optimization using non-traditional optimization technique and its validation,” Journal of King Saud University – Engineering Sciences 2013
[15] Tan Xin., Lian Bo,Yu Peixiang, Qiang Xiaoqing , and Ouyang Hua .,“The effect of leading-edge shape on separation-induced transition on the suction surface of a controlled-diffusion airfoil “,Physics of Fluids 35, 075117 ,2023.
Modares Mechanical Engineering
Volume 25, Issue 1
January 2024
Pages 1-9