Journal of Computational & Applied Research in Mechanical Engineering (JCARME)
مقاله 10 ، دوره 8، شماره 1 - شماره پیاپی 15 ، مهر 2018، صفحه 107-120 1.79 M )
نوع مقاله: Research Paper
شناسه دیجیتال (DOI): 10.22061/jcarme.2018.1948.1164 نویسندگان
Omid Fathi 1 Hadi Kargarsharifabad* 2 1 Department of Mechanical Engineering, Najafabad Branch, Islamic Azad University, Najafabad, Iran.2 Energy and Sustainable Development Research Center, Semnan Branch, Islamic Azad University, Semnan, Iran
تاریخ دریافت : 09 مهر 1395 ،
تاریخ بازنگری : 19 آذر 1396 ،
تاریخ پذیرش : 20 دی 1396
چکیده Improving the efficiency of compressors has been one of the most important goals of researchers over the years. In this paper, three different methods are presented for parameterization and blade optimization of axial flow compressor. All methods consist of flow analysis tool, optimization algorithms, and parametric geometry generation tool, that are different in each approach. Objective function is defined based on the aerodynamic performance of blade in the acceptable incidence angles range. A DCA blade is used as the initial guess for all methods. The performance of optimized blades and the initial blade are compared for evaluating the capability of various methods that a good agreement has been achieved. The results show that the value of performance improvement in each method depends on the number and type of the chosen parameters. All three methods have improved blade performance at the design incidence angle. However, only the first method shows significant performance improvement in off-design conditions. کلیدواژهها
Parametric geometry ؛ Loss coefficient ؛ Optimization algorithm ؛ Multi-point objective function
مراجع
[1] K. Park, M. G. Turner, K. Siddappaji, S. Dey, and A. Merchant, “Optimization of a 3-stage booster: part 1-the axisymmetric multi-disciplinary optimization approach to compressor design”, in ASME 2011 Turbo Expo: “Turbine Technical Conference and Exposition” , pp. 1413-1422, (2011).
[2] D. Bonaiuti and M. Zangeneh, “On the coupling of inverse design and optimization techniques for the multiobjective, multipoint design of turbomachinery blades”, Journal of Turbomachinery, Vol. 131, No. 2, p. 021014, (2009).
[3] T. Korakianitis, “Hierarchical development of three direct-design methods for two-dimensional axial-turbomachinery cascades”, Journal of turbomachinery, Vol. 115, No. 2, pp. 314-324, (1993).
[4] T. Sonoda, Y. Yamaguchi, T. Arima, M. Olhofer, B. Sendhoff, and H.-A. Schreiber, “Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition: Part 1-Design and Optimization”, in ASME Turbo Expo 2003, “collocated with the 2003 International Joint Power Generation Conference” , pp. 437-450, (2003).
[5] S. Shahpar and D. Radford, “Application of the FAITH linear design system to a compressor blade”, International Society for Air Breathing Engines- ISOABE , “ISABE- International Symposium on Air Breathing Engines ” , 14 th, Florence, Italy, (1999).
[6] S. Kammerer, J. Mayer, M. Paffrath, U. Wever, and A. Jung, “Three-dimensional optimization of turbomachinery bladings using sensitivity analysis”, in ASME Turbo Expo 2003, “collocated with the 2003 International Joint Power Generation Conference” , pp. 1093-1101, (2003).
[7] D. Buche, G. Guidati, and P. Stoll, “Automated design optimization of compressor blades for stationary, large-scale turbomachinery”, in ASME Turbo Expo 2003, “collocated with the 2003 International Joint Power Generation Conference” , pp. 1249-1257, (2003)
[8] E. Benini and A. Tourlidakis, “Design optimization of vaned diffusers of centrifugal compressors using genetic algorithms”, 15th AIAA Computational Fluid Dynamics Conference, Vol. 2583, pp. 2001, (2001).
[9] D. Bonaiuti and V. Pediroda, “Aerodynamic optimization of an industrial centrifugal compressor impeller using genetic algorithms”, in Proceedings of Eurogen , pp. 467-472, (2001).
[10] K. Siddappaji, M. G. Turner, S. Dey, K. Park, and A. Merchant, “Optimization of a 3-Stage Booster: Part 2-The Parametric 3D Blade Geometry Modeling Tool”, in ASME 2011 Turbo Expo: “Turbine Technical Conference and Exposition” , pp. 1431-1443, (2011).
[11] R. Jaron, A. Moreau, S. Guérin, and R. Schnell, “Optimization of Trailing-Edge Serrations to Reduce Open-Rotor Tonal Interaction Noise”, Journal of Fluids Engineering, Vol. 140, No. 2, pp. 021201-021201-8, (2017).
[12] S. Vitale, T. A. Albring, M. Pini, N. R. Gauger, and P. Colonna, “Fully turbulent discrete adjoint solver for non-ideal compressible flow applications”, Journal of the Global Power and Propulsion Society, Vol. 1, pp. 252-270, (2017).
[13] H. Schreiber and H. Starken, “Experimental cascade analysis of atransonic compressor rotor blade section”, Journal of Engineering for Gas Turbines and Power, Vol. 106, No. 2, pp. 288-294, (1984).
[14] M. Kermani and E. Plett, “Modified entropy correction formula for the Roe scheme”, 39th Aerospace Sciences Meeting and Exhibit , (2001).
[15] B. Van Leer, “Towards the ultimate conservative difference scheme. V. A second-order sequel to Godunov's method”, Journal of computational Physics, Vol. 32, No. 1, pp. 101-136, (1979).
[16] W. Steinert, B. Eisenberg, and H. Starken, “Design and testing of a controlled diffusion airfoil cascade for industrial axial flow compressor application”, Journal of Turbomachinery, Vol. 113, No. 4, pp. 583-590, (1991).
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