Preliminary Design of a Transonic Fan for Low By-Pass Turbofan Engine

(*) Corresponding author

Authors' affiliations

DOI's assignment:
the author of the article can submit here a request for assignment of a DOI number to this resource!
Cost of the service: euros 10,00 (for a DOI)


Design optimization of axial compressors using numerical simulations requires huge computational efforts. Therefore, the design process needs to be started from a reasonable design point. In the current study, a design tool is developed for the preliminary design of transonic compressors using different correlations of cascade experimental data for the shock losses and the deviation angle. A parametric study is performed to select the design parameters for optimum fan performance in terms of efficiency and surge margin. The designed fan is tested during off design operation and simulated numerically using computational fluid dynamics to verify the developed design tool. The numerical simulations of designed fan show good agreement with the preliminary design results.
Copyright © 2013 Praise Worthy Prize - All rights reserved.


Fan Design; Loss Models; Numerical Simulation

Full Text:



Hah, C. & Reid, L. (1992). A Viscous Flow Study of Shock-Boundary Layer Interaction, Radial Transport, and Wake Development in a Transonic Compressor, ASME Journal of Turbomachinery, Vol. 114, No. 3, (July 1992), pp. 538-547, ISSN 0889-504X.

Ning, F. & Xu, L. (2001). Numerical Investigation of Transonic Compressor Rotor Flow Using an Implicit 3D Flow Solver With One-Equation Spalart-Allmaras Turbulence Model, Proceedings of ASME Turbo Expo 2001, 2001-GT-0359.

Puterbaugh, S. L.; Copenhaver, W. W.; Hah, C. & Wennerstrom, A. J. (1997). A Three- Dimensional Shock Loss Model Applied to an Aft-Swept, Transonic Compressor Rotor, ASME Journal of Turbomachinery, Vol. 119, No. 3, (July 1997), pp. 452-459, ISSN 0889-504X

Strazisar, A. J. (1985). Investigation of Flow Phenomena in a Transonic Fan Rotor Using Laser Anemometry, ASME Journal of Engineering for Gas Turbines and Power, Vol.107, No.2, (April 1985), pp. 427-435, ISSN 0742-4795

R. Mdouki, A. Gahmousse, " Numerical Exploration of Endwall Flow in a Slotted Compressor Cascade at Design Condition", International Review of Aerospace Engineering, March 2012 (Part A), Vol. 6 N. 3, pp. 520-527.

Miller, G. R.; Lewis, Jr., G. W. & Hartmann, M. J. , Shock Losses in Transonic Compressor Blade Rows, ASME Journal of Engineering for Power, Vol. 83, No. 3, July 1961, pp. 235-242.

Wennerstrom, Arthur. J., Design of Highly Loaded Axial-Flow Fans and Compressors, Concepts ETI, Inc, 2000.

Wu, C. H., A General Theory of Three-Dimensional Flow in Subsonic and Supersonic Turbomachines of Axial-, Radial-, and Mixed Flow Types, NACA TN 2604, 1952.

Wennerstrom, A. J. & Puterbaugh, S. L. (1984). A Three-Dimensional Model for the Prediction of Shock Losses in Compressor Blade Rows, ASME Journal of Engineering for Gas Turbines and Power, Vol. 106, No. 2, (April 1984), pp. 295-299, ISSN 0742-4795

Freeman, C. & Cumpsty, N. A. (1992). Method for the Prediction of Supersonic Compressor Blade Performance, Journal of Propulsion and Power, Vol. 8, No. 1, (Jan-Feb 1992), pp. 199-208, ISSN 0748-4658.

Schreiber, H.-A., and Tweedt, D. L., 1987, "Experimental Investigation and Analysis of the Supersonic Compressor Cascade ARL-2DPC," DFVLR IB-325-02-87.

König, W.M., C.K. Hennecke, and L. Fottner. “Improved Blade Profile Loss and Deviation Angle Models for Advanced Transonic Compressor Bladings: Part II – A Model for Supersonic Flow,” ASME Journal of Turbomachinery, 117 :81–87 (January 1996).

Lieblein, S., “Viscous Flow in Two-dimensional Cascades,” NASA SP-36, 1965.

Hearsey, R.M., “HT0300-A Computer Program for the Design and Analysis of Axial Turbomachinery,” Parts I-II, Cambridge, Massachusetts, March 1970.

Carter, A.D.S. Hughes,.H.P. "A Theoretical Investigation into the Effect of Profile Shape on the Performance of Aerofoils in Cascade, ARC Rep. and Memo. 2384, 1950.

Cetin, M., Ucer, A.S., Hirsch, Ch., and Serovy, G.K., “Application of Modified Loss and Deviation Correlations to Transonic Axial Compressors” AGARD Report No. 745 November 1987.

Law and Puterbaugh, (1988)" Parametric Blade Study Test Report Rotor Configuration. Number 1", Air force wright aeronautical labs Wright-Patterson AFB OH, Nov 1988.

Roberto Biollo and Ernesto Benini (2011). "State-of-Art of Transonic Axial Compressors, Advances in Gas Turbine Technology", Dr. Ernesto Benini (Ed.), ISBN: 978-953-307-611-9, InTech.

H.I.H. Saravanamuttoo, GFC Rogers and H Cohen, (2001),”Gas Turbine Theory”, Prentice Hall, 5th Edition.

Cumpsty, Nicholas A. Compressor Aerodynamics. New York: John Wiley & Sons, Inc., 1989.

Wadia, A. R. & Law, C. H. (1993). Low Aspect Ratio Transonic Rotors: Part 2-Influence of Location of Maximum Thickness on Transonic Compressor Performance, ASME Journal of Turbomachinery, Vol. 115, No. 2, (April 1993), pp. 226-239, ISSN 0889-504X.

Chen, N.; Zhang, H.; Xu, Y. & Huang, W. (2007). Blade Parameterization and Aerodynamic Design Optimization for a 3D Transonic Compressor Rotor, Journal of Thermal Science, Vol. 16, No. 2, (May 2007), pp. 105-114, ISSN 1003-2169.

Suder, K. L.; Chima, R. V.; Strazisar, A. J. & Roberts, W. B. (1995). The Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor, ASME Journal of Turbomachinery, Vol. 117, No. 4, (October 1995), pp. 491-505, ISSN 0889-504.

Keith M. Boyer, 2001" An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Compression Systems", Doctor of Philosophy, Virginia Polytechnic Institute and State University , Blacksburg, Virginia, April 2001.

Joseph E. Cahill 1997" Identification and Evaluation of Loss and Deviation Models for use in Transonic Compressor Stage Performance Prediction", Master of Science, Virginia Polytechnic Institute and State University , Blacksburg, Virginia, September 22, 1997.

Koch, C.C., Smith, L.H., “Loss Sources and Magnitudes in Axial-Flow Compressors,” ASME Journal of Engineering for Power, Vol. 98, 1976, pp. 411-424.

Creveling, H.F., “Axial-Flow Compressor Computer Program for Calculating Off-Design Performance,” NASA CR 72472, 1968.

Gregory S. Bloch, 1996," Flow Losses in Supersonic Compressor Cascades"", Doctor of Philosophy, Virginia Polytechnic Institute and State University , Blacksburg, Virginia, July 1996.

B. Lakshminarayana and J. H. Horlock, (1963). Tip Clearance Flow and Losses for an Isolated Compressor Blade. Aeronautical Research council reports and memoranda, London, 1963.

J. H. Horlock, (1973), "Axial flow compressors, fluid Mechanics and Thermodynamics", Ropert E. Krieger Publishing Company, 1973.

Moeckel, W.E., “Approximate Method for Predicting Form and Location of Detached Shock Waves Ahead of Plane or Axially Symmetric Bodies,” NACA TN 1921, 1949.

J.P. Gostelow, K.W. krabacber, L.H. Smith, Jr."Performance Comparisons of High Mach Number Compressor Rotor Blading", Nationnal Aerodynamics and Space Administration.Washington, D.C. December, 1968.

Boyce, M.P,, Gas Turbine Engineering Handbook, Second Edition, Butterworth-Hienemann 2003.


  • There are currently no refbacks.

Please send any question about this web site to
Copyright © 2005-2023 Praise Worthy Prize