Open Access Open Access  Restricted Access Subscription or Fee Access

Optimization of Aerodynamic Characteristic of Compressor Cascade by Genetic Algorithm Assisted by Modified Vortex Panel Method

G. Manikandan, M. Ananda Rao

Abstract


Axial compressor cascade blade shape optimization has been carried outto obtain improved aerodynamic performance using genetic algorithm optimization technique assisted by modified vortex panel flow solver. Three set of compressor cascades with aspect ratio 4.16, 3.246 and 2.0 have been designed and fabricated with solid side walls for experimental investigations. Compressor cascade mounting system has been designed and fabricated for mounting the cascade on the wind tunnel. To ensure resonance free testing in the wind tunnel and avoid flutter problems, Finite element model of compressor cascade mounting system has been developed and modal analysis have been carried out to glean the natural frequencies of vibration. NACA 9410-83 aerofoil has been chosenas a baseline aerofoil for blade section profile with 45, 55 and 65 degrees stagger angles respectively for high, medium and low aspect ratio compressor cascades. The compressor cascades have been tested at 0.06, 0.07 and 0.08 low subsonic Mach number and 0 to 5 degrees angle of attack. Modified vortex panel method has been formulated and validated by experimental investigations. Substantial differences in aerodynamic performance have been investigated between the baseline aerofoil profiled compressor cascade and genetic algorithm optimized aerofoil profiled compressor cascade.

Keywords


Aspect Ratio, Compressor Cascade, Modified Vortex Panel, Stagger Angle

Full Text:

PDF

References


Johnsen I and Bullock R, „„Aero dynamical Design of Axial-Flow Compressors,‟‟ NASA SP-36, 1965.

Hobbs D and Weingold H, „„Development of Controlled Diffusion Airfoils for Multistage Compressor Application,‟‟ ASME J. Eng. Gas Turbines Power, 106, pp. 271–278, 1984

Korn D, „„Numerical Design of Transonic Cascades,‟‟ ERDA Research and Development Report C00-3077-72, 1975.

Schmidt E, „„Computation of Supercritical Compressor and Turbine Cascades With a Design Method for Transonic Flows,‟‟ ASME Paper No.79-GT-30, 1979.

Stephens H, „„Application of Supercritical Airfoil Technology to Two-Dimensional Compressor Cascades: Comparison of Theoretical and Experimental Results,‟‟ AIAA J., 17, No. 6, pp. 594–600, 1979.

Rechter H Steinert W and Lehmann K., „„Comparison of Controlled Diffusion Airfoils With Conventional NACA 65 Airfoils Developed for Stator Blade Application in a Multistage Axial Compressor,‟‟ ASME J. Eng. Gas Turbines Power, 107, pp. 494–498, 1985.

Dunker R, Rechter H, Starken H, and Weyer H. B., „„Redesign and Performance Analysis of a Transonic Axial Compressor Stator and Equivalent Plane Cascades With Subsonic Controlled Diffusion Blades,‟‟ ASME J. Eng. Gas Turbines Power, 106, pp. 279–287, 1984.

Denton J.D, “Loss Mechanism in Turbo machines,” Journal of Turbomachinery, Vol.115, pp. 621-656, 1993.

Dunham J., “Aerodynamic Losses in Turbo machines,” AGARD-CP-571, Loss Mechanism and Unsteady Flows in Turbo machines, K1-K13, 1996.

Wennerstrom A. J., “Highly Loaded Axial Flow Compressors: History and Current Developments,” Journal of Turbomachinery, Vol. 112, pp. 567-578, 1990.

Erwin J.R and J.C Emery, “The effect of tunnel configuration and testing technique on cascade performance. NACA T.N. No.2028, 1950.

Sanger, N. L., „„The Use of Optimization Techniques to Design Controlled Diffusion Compressor Blading,‟‟ ASME J. Eng. Power, 105, pp. 256–265, 1983

Sanz J., „„Automated Design of Controlled Diffusion Blades,‟‟ ASME, Journal of Turbomachinery, 110, pp. 540–544, 1988.

Goel S., Cofer J. and Hardev S., „„Turbine Airfoil Design Optimization,‟‟ASME Paper No. 96-GT-158, 1996.

Pierret S., Van den Braembussche, R., „„Turbomachinery Blade Design Using a Navier–Stokes Solver and Artifical Neural Network,‟‟ Reprint from 4th National Congress of Theoretical and Applied Mechanics, May 22–23,Leuven, Belgium, 1997.

Carter A.D.S, “The low speed performance of related aerofoils in cascade”,ARC, C.P No 29, 1949.

Horlock J.H, R.Shaw, D.Pollard and A.K.Lewkowicz, “Reynolds number effects in cascades and axial flow compressors”, Journal of Engineering for power Trans. ASME, Vol.86, Series A, pp.236-242, 1964.

Schreiber H. A. and Starken H., “Experimental Cascade Analysis of a Transonic Compressor Rotor Blade Section,” Journal of Engineering for Gas Turbine and Power, Vol. 106, pp. 288-294, 1984.

Manna M. and Tuccillo R., “The Combined Use of Navier-Stokes Solvers and Optimization Methods for Decelerating Cascade Design,” ASME TURBO EXPO 2000, Munich, Germany, 2000-GT-523, 2000.

Rai M and Madavan N., “Application of Artificial Neural Networks to Design of Turbo machinery Airfoils,” Journal of Propulsion and Power, Vol. 17, No. 1, pp.176-183, 2001.

Terry L. Holst and Thomas H. Pulliam, “Evaluation of Genetic Algorithm Concepts Using Model Problems Part II: Multi-Objective Optimization”, NASA/TM–2003-212813, December 2003.

Manikandan G, Ananda Rao M, “Aerofoil shape optimization by normal to reference line method”, AIAA Journal of Aircraft, January 2011, submitted for publication.

Quagliarella D and Della Cioppa A, “Genetic Algorithms Applied to the Aerodynamic Design of Transonic Airfoils”, Journal of aircraft, Volume 32, Pages 889-891, 1995.

Yamamoto K and Inoue O, “Applications of genetic algorithms to aerodynamic shape optimization”, AIAA-95- 1650- CP, 1995.

Doorly DJ, Peiro J, Kuan T and Oesterle JP, “Optimization of Airfoils Using Parallel Genetic Algorithms”, in Proceedings of 15th International Conference on Numerical Methods in Fluid Dynamics, Monterey, 1996.

Oyama A., “Wing Design Using Evolutionary Algorithms,” PhD Thesis, Dept. of Aeronautics and Space Engineering, Tohoku University, Senadi, Japan, March 2000.


Refbacks

  • There are currently no refbacks.