A Review of Some Early Design Practice Using Computational Fluid Dynamics and a Current Perspective

[+] Author and Article Information
J. H. Horlock, J. D. Denton

Cambridge University Engineering Department, Whittle Laboratory, Madingley Road, Cambridge CB3 0DY, UK

J. Turbomach 127(1), 5-13 (Feb 09, 2005) (9 pages) doi:10.1115/1.1650379 History: Received December 01, 2002; Revised March 01, 2003; Online February 09, 2005
Copyright © 2004 by ASME
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Lakshminarayana, B., 1996, Fluid Dynamics and Heat Transfer in Turbomachinery, John Wiley and Sons, New York.
Cumpsty, N. A., 1989, Compressor Aerodynamics, Longman, London.
Howell, A. R., 1942, “The Present Basis of Axial Flow Compressor Design: Part I—Cascade Theory and Performance,” Aeronautical Research Council R. and M. No. 2095.
Carter, A. D. S., and Hughes, H. P., 1950, “A Theoretical Investigation of the Effect of Profile Shape on the Performance of Aerofoils in Cascade,” Aeronautical Research Council R. and M. No. 2384.
Lieblein,  S., 1959, “Loss and Stall Analysis of Compressor Cascades,” ASME J. Basic Eng., 81, p. 3.
Whittle,  Frank, 1945, “The Early History of the Whittle Jet Propulsion Gas Turbine,” Proc. Inst. Mech. Eng., 152, pp. 419–535.
Ainley, D. G., and Mathieson, G. C. R., 1955, “An Examination of the Flow and Pressure Losses in Blade Rows of Axial Flow Turbines,” Aeronautical Research Council R. and M. 2891.
Shapiro, A. H., 1953, The Dynamics and Thermodynamics of Compressible Fluid Flow, Ronald Press, New York.
Wu,  Chung-hua, and Brown,  C. A., 1952, “A Theory of the Direct and Inverse Problems of Compressible Flow Past Cascade of Arbitrary Aerofoils,” J. Aeronaut. Sci., pp. 183–196.
Stanitz, J. D., 1952, “Design of Two-dimensional Channels With Prescribed Velocity Distributions Along the Channel Walls,” NACA Tech. Notes 2593, 2595.
Stanitz, J. D., 1951, “Approximate Design Method for High-Solidity Blade Elements in Compressors and Turbines,” NACA Tech. Note 2408.
Weinig, F., 1935, Die Stromung um die Schaufeln von Turbomaschinen, Joh. Ambr. Barth, Leipzig.
Kraft,  H., 1958, “Development of a Laminar Wing Type Turbine Bucket,” ZAMP, 404.
Garrick, J. E., 1944, “On the Plane Potential Flow Past a Lattice of Arbitrary Aerofoils,” NACA Report 778.
Schlicting, H., and Scholz, N., 1951, Uber die Theoretische Berechung der Stromungsverluste eines ebenen Schaufelgitters, Ingen.-Arch. Bd. XIX Heft. 1.
Martensen,  E., 1959, “The Calculation of the Pressure Distribution on a Cascade of Thick Aerofoils by Means of Fredholm Integral Equations of the Second Kind,” Arch. Ration. Mech. Anal., 3, pp. 251–270.
Gostelow, J. P., 1962, “Potential Flow Through Cascades-Extension to an Exact Theory,” Aeronautical Research Council, CP 808.
Hobson, D. E., 1979, “Shock Free Transonic Flow in Turbomachinery Cascade,” Cambridge University Report CUED/A Turbo 65 (also Ph.D. thesis Cambridge University).
Stratford,  B. S., 1959, “The Prediction of Separation of the Turbulent Boundary Layer. An Experimental Flow With Zero Skin Friction Throughout Its Region of Pressure Rise,” J. Fluid Mech., pp. 1–16, 17–35.
Le Foll, J., 1976, Inverse Method for Optimised Blading Calculations, VKI Lecture Series 84.
Hawthorne,  W. R., 1951, “Secondary Circulation in Fluid Flow,” Proc. R. Soc. London, Ser. A, 206, p. 374.
Hawthorne,  W. R., 1955, “Rotational Flow Through Cascades, Part I—The Components of Vorticity,” Q. J. Mech. Appl. Math., 8, p. 266.
Smith,  L. H., 1953, “Secondary Flow in Axial Flow Turbomachinery,” Trans. ASME, 77, p. 1065.
Langston,  L. S., Nice,  M. L., and Hooper,  R. M., 1977, “Three-Dimensional Flow Within a Turbine Passage,” ASME J. Eng. Gas Turbines Power, 99, pp. 21–28.
Dunham,  J., and Came,  P. M., 1970, “Improvements to the Ainley-Mathieson Method of Turbine Performance Prediction,” ASME J. Eng. Gas Turbines Power, A92, p. 252.
Hah,  C. A., 1984, “Navier-Stokes Analysis of Three-Dimensional Turbulent Flows Inside Turbine Blade Rows at Design and Off-Design Conditions,” ASME J. Eng. Gas Turbines Power, 106, pp. 421–429.
Smith,  L. H., 1962, discussion of Proc. Inst. Mech. Eng., 176(30), p. 789.
Stubner,  A. W., 1962, discussion of Proc. Inst. Mech. Eng., 176(30), p. 789.
Marsh, H., 1968, “A Computer Program for the Through Flow Fluid Mechanics in an Arbitrary Turbomachine Using a Matrix Method,” Aeronautical Research Council R. and M. No. 3509.
Wu, Chung-Hua, 1952, “A General Theory of Three-Dimensional Flow in Subsonic and Supersonic Turbomachine in Radial, Axial and Mixed Flow Types,” NACA Tech. Note 2604.
Rains, D. A., 1954, “Tip Clearance Flows in Axial Compressors and Pumps,” California Institute of Technology, Hydrodynamics and Mechanical Engineering Laboratories, Report No. 5.
Dean, R. C., 1954, “Secondary Flow in Axial Compressors,” Sc.D thesis, Gas Turbine Laboratory, M.I.T., Cambridge, MA.
Lakshminarayana, B., and Horlock, J. H., 1967, “Leakage and Secondary Flow in Compressor Cascades,” Aeronautical Research Council, R. and M. 3483.
Lakshminarayana,  B., 1970, “Predicting the Tip Clearance Flow in Axial Flow Turbomachines,” ASME J. Basic Eng., 92, pp. 467–482.
Constant, H., 1939, “Performance of Cascades of Aerofoils, Royal Aircraft Establishment,” Note No. E3696, Aeronautical Research Council, Report No. 4155.
Taylor, E. S., 1957, “Problem of the Convergent Nozzle,” Technical Note (unpublished) Gas Turbine Laboratory, M.I.T., Cambridge, MA.
Horlock, J. H., 1973, Axial Flow Turbines, Krieger Publishing Company, Melbourne, FL.
Horlock,  J. H., and Marsh,  H., 1971, “Flow Models for Turbomachinery,” J. Mech. Eng. Sci., 13, pp. 358–368.
Katsanis T., 1968, “Computer Program for Calculating Velocities and Streamlines on a Blade-to-Blade Stream Surface of a Turbomachine,” NASA TND 4525.
Wilkinson, D. H., 1972, “Calculation of Blade-to-Blade Flow in a Turbomachine by Streamline Curvature,” Aeronautical Research Council, R. and M. 3704.
Novak, R. A., and Haymann-Haber, G., 1982, “A Mixed-Flow Cascade Passage Design Procedure Based on a Power Series Expansion,” ASME Paper 82-GT-121.
Smith,  L. H., 2002, “Axial Compressor Aerodesign Evolution at General Electric,” ASME J. Turbomach., 124, pp. 321–330.
Miller, M. J., and Serovy, G. K., 1974, “Deviation Estimation for Axial-Flow Compressors Using Inviscid Flow Solutions,” ASME Paper 74-GT-74.
Wang,  L. C., Hetherington,  R., and Goulas,  A., 1983, “The Calculation of Deviation Angle in Axial Flow Compressor Cascades,” ASME J. Eng. Gas Turbines Power, 105, pp. 474–479.
Denton,  J. D., 1991, “The Calculation of Threedimensional Viscous Flow Through Multistage Turbomachines,” ASME J. Turbomach., 114.
Howell,  A. R., 1947, “Fluid Dynamics of Axial Compressors,” Proc. Inst. Mech. Eng., War Emergency Issue, 12.
Smith, L. H., 1969, “Casing Boundary Layers in Multistage Compressors, Flow Research in Blading,” L. S. Dzung, ed., Elsevier, New York.
Bolger, J. J., and Horlock, J. H., 1995, “Predictions of the Flow in Repeating Stages of Axial Compressors Using Navier-Stokes Solvers,” ASME Paper 95-GT-199.
Howard,  M. A., Ivey,  P. C., Barton,  J. P., and Young,  K. F., 1994, “End Wall Effects at Two Tip Clearances in a Multi-Stage Axial Flow Compressor With Controlled Diffusion Blading,” ASME J. Turbomach., 106, pp. 635–647.
Horlock,  J. H., 2000, “The Determination of End-Wall Blockage in Axial Flow Compressors—A Comparison Between Various Approaches,” ASME J. Turbomach., 122, pp. 218–224.
Harrison, S., 1989, “Secondary Loss Generation in a Linear Cascade of High-Turning Turbine Blades,” ASME Paper 89-GT-47.
Denton, J. D., and Xu, L., 2002, “The Effects of Lean and Sweep on Transonic Fan Performance,” ASME Paper GT-2002-30327.


Grahic Jump Location
Axial and tangential lift coefficients of Lakshimarayana’s cascade
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Calculated stagnation pressure contours behind Lakshimarayana’s cascade
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The growth of tip leakage loss through Lakshimarayana’s cascade
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Static pressure contours near the tip of Lakshimarayana’s cascade
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Lift coefficients of the four stages
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Exit flow angles from stage 3, rotor and stator
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(a) Axial velocities at rotor 3 exit, (b) axial velocities at stator 3 exit
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Stagnation pressure contours behind Harrison’s cascade; (a) inviscid calculation with inlet boundary layer, (b) viscous calculation with no inlet boundary layer, (c) viscous calculation with inlet boundary layer, (d) experiment
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Shock pattern in a swept fan. Mach number contours at midpitch.




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