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One-Dimensional Performance Improvement of a Single-Stage Transonic Compressor

Authors: A. Shahsavari, M. Nili-Ahmadabadi


This paper presents an innovative one-dimensional optimization of a transonic compressor based on the radial equilibrium theory by means of increasing blade loading. Firstly, the rotor blade of the transonic compressor is redesigned based on the constant span-wise deHaller number and diffusion. The code is applied to extract compressor meridional plane and blade to blade geometry containing rotor and stator in order to design blade three-dimensional view. A structured grid is generated for the numerical domain of fluid. Finer grids are used for regions near walls to capture boundary layer effects and behavior. RANS equations are solved by finite volume method for rotating zones (rotor) and stationary zones (stator). The experimental data, available for the performance map of NASA Rotor67, is used to validate the results of simulations. Then, the capability of the design method is validated by CFD that is capable of predicting the performance map. The numerical results of new geometry show about 19% increase in pressure ratio and 11% improvement in overall efficiency of the transonic stage; however, the design point mass flow rate of the new compressor is 5.7% less than that of the original compressor.

Keywords: One dimensional design, deHaller number, radial equilibrium, transonic compressor.

Digital Object Identifier (DOI):

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[1] Chen, L., Luo, Jun., Sun, Fengrui., Wu, Chih., Optimized efficiency axial-flow compressor. Applied energy, 2005. 81(4): p. 409-419.
[2] Chen, L., F. Sun, and C. Wu, Optimum design of a subsonic axial-flow compressor stage. Applied energy, 2005. 80(2): p. 187-195.
[3] Chen, L., Luo, Jun., Sun, Fengrui., Wu, Chih., Design efficiency optimization of the one-dimensional multi-stage axial flow compressor. Applied Energy, 2008. 85(7): p. 625-633.
[4] Boiko, A., Optimal Design for Flow-Path of Axial Turbines. 1982, Harkov: Higher Education Press.
[5] Lim, J.S. and M.K. Chjng, Design point optimization of an axial-flow compressor stage. International journal of heat and fluid flow, 1989. 10(1): p. 48-58.
[6] Jones, J.A., A multidisciplinary algorithm for the 3-D design optimization of transonic axial compressor blades. 2002.
[7] Benini, E., Three-dimensional multi-objective design optimization of a transonic compressor rotor. Journal of propulsion and power, 2004. 20(3): p. 559-565.
[8] Keskin, A. and D. Bestle, Application of multi-objective optimization to axial compressor preliminary design. Aerospace science and technology, 2006. 10(7): p. 581-589.
[9] Samad, A., and K.-Y. Kim, Multi-objective optimization of an axial compressor blade. Journal of Mechanical Science and Technology, 2008. 22(5): p. 999-1007.
[10] Aziz, M., F.M. Owis, and M. Abdelrahman, Preliminary design of a transonic fan for a low by-pass turbofan engine. International Review of Aerospace Engineering (IREASE), 2013. 6(2): p. 114-127.
[11] Okui, H., Verstraete, Tom., Van Den Braembussche, RA., Alsalihi, Zuheyr., Three-dimensional design and optimization of a transonic rotor in axial flow compressors. Journal of Turbomachinery, 2013. 135(3): p. 031009.
[12] Luo, J., C. Zhou, and F. Liu, Multipoint design optimization of a transonic compressor blade by using an adjoint method. Journal of Turbomachinery, 2014. 136(5): p. 051005.
[13] Song, P., J. Sun, and K. Wang. Blade Shape Optimization of Transonic Axial Flow Fan in Terms of Sectional Profiles and Stacking ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. 2014. American Society of Mechanical Engineers.
[14] Hatch, J.E., C.C. Giamatti, and R.J. Jackson, Application of radial-equilibrium condition to axial flow turbomachine design including consideration of a change of entropy with radius downstream of blade row. 1954, DTIC Document.
[15] Klapproth, J.F., A review of supersonic compressor development. Journal of Engineering for Gas Turbines and Power, 1961. 83(3): p. 258-268.
[16] Wennerstrom, A.J., Design of highly loaded axial-flow fans and compressors. 2000.
[17] Johnsen, I.A., and R.O. Bullock, Aerodynamic Design of Axial-Flow Compressors. NASA SP-36. NASA Special Publication, 1965. 36.
[18] Kerrebrock, J.L., Flow in transonic compressors. AIAA Journal, 1981. 19(1): p. 4-19.
[19] Falck, N., Axial Flow Compressor Mean Line Design. Master's thesis, Lund University, Lund, Sweden, 2008.
[20] Dixon, S.L. and C. Hall, Fluid mechanics and thermodynamics of turbomachinery. 2013: Butterworth-Heinemann, pp. 95–132.
[21] Aungier, R. H. (2003). Axial-Flow Compressors. American Society of Mechanical Engineers, New York.
[22] Dickens, T. and I. Day, The design of highly loaded axial compressors. Journal of Turbomachinery, 2011. 133(3): p. 031007.
[23] Seyler, D. and L. Smith Jr, Single stage experimental evaluation of high Mach number compressor rotor blading, Part I, Design of rotor blading. NASA CR-54581, 1967: p. 26-28.