In the early development of gas turbines, many empirical design rules were used; for example in obtaining fluid deflection using the deviation from blading angles, in the assumption of zero radial velocities (so-called radial equilibrium) and in expressions for clearance loss (the Lakshminarayana formulas). The validity of some of these rules, and the basic fluid mechanics behind them, is examined by use of modern ideas and computational fluid dynamics (CFD) codes. A current perspective of CFD in design is given, together with a view on future developments.
Issue Section:
Technical Papers
1.
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2.
Cumpsty, N. A., 1989, Compressor Aerodynamics, Longman, London.
3.
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.
4.
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.
5.
Lieblein
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, 1959
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,” ASME J. Basic Eng.
, 81
, p. 3
3
.6.
Whittle
, Sir, Frank
, 1945
, “The Early History of the Whittle Jet Propulsion Gas Turbine
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, 152
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.7.
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.
8.
Shapiro, A. H., 1953, The Dynamics and Thermodynamics of Compressible Fluid Flow, Ronald Press, New York.
9.
Wu
, Chung-hua
, and Brown
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, 1952
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Stanitz, J. D., 1952, “Design of Two-dimensional Channels With Prescribed Velocity Distributions Along the Channel Walls,” NACA Tech. Notes 2593, 2595.
11.
Stanitz, J. D., 1951, “Approximate Design Method for High-Solidity Blade Elements in Compressors and Turbines,” NACA Tech. Note 2408.
12.
Weinig, F., 1935, Die Stromung um die Schaufeln von Turbomaschinen, Joh. Ambr. Barth, Leipzig.
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Kraft
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Garrick, J. E., 1944, “On the Plane Potential Flow Past a Lattice of Arbitrary Aerofoils,” NACA Report 778.
15.
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16.
Martensen
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18.
Hobson, D. E., 1979, “Shock Free Transonic Flow in Turbomachinery Cascade,” Cambridge University Report CUED/A Turbo 65 (also Ph.D. thesis Cambridge University).
19.
Stratford
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Hawthorne
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.23.
Smith
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, 1953
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.24.
Langston
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.25.
Dunham
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, and Came
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Hah
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.27.
Smith
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, 1962
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Stubner
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.29.
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.
30.
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.
31.
Rains, D. A., 1954, “Tip Clearance Flows in Axial Compressors and Pumps,” California Institute of Technology, Hydrodynamics and Mechanical Engineering Laboratories, Report No. 5.
32.
Dean, R. C., 1954, “Secondary Flow in Axial Compressors,” Sc.D thesis, Gas Turbine Laboratory, M.I.T., Cambridge, MA.
33.
Lakshminarayana, B., and Horlock, J. H., 1967, “Leakage and Secondary Flow in Compressor Cascades,” Aeronautical Research Council, R. and M. 3483.
34.
Lakshminarayana
, B.
, 1970
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, 92
, pp. 467
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.35.
Constant, H., 1939, “Performance of Cascades of Aerofoils, Royal Aircraft Establishment,” Note No. E3696, Aeronautical Research Council, Report No. 4155.
36.
Taylor, E. S., 1957, “Problem of the Convergent Nozzle,” Technical Note (unpublished) Gas Turbine Laboratory, M.I.T., Cambridge, MA.
37.
Horlock, J. H., 1973, Axial Flow Turbines, Krieger Publishing Company, Melbourne, FL.
38.
Horlock
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.39.
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40.
Wilkinson, D. H., 1972, “Calculation of Blade-to-Blade Flow in a Turbomachine by Streamline Curvature,” Aeronautical Research Council, R. and M. 3704.
41.
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.
42.
Smith
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,” ASME J. Turbomach.
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, pp. 321
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.43.
Miller, M. J., and Serovy, G. K., 1974, “Deviation Estimation for Axial-Flow Compressors Using Inviscid Flow Solutions,” ASME Paper 74-GT-74.
44.
Wang
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.45.
Denton
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Howell
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, War Emergency Issue, 12
.47.
Smith, L. H., 1969, “Casing Boundary Layers in Multistage Compressors, Flow Research in Blading,” L. S. Dzung, ed., Elsevier, New York.
48.
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.
49.
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
.50.
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
.51.
Harrison, S., 1989, “Secondary Loss Generation in a Linear Cascade of High-Turning Turbine Blades,” ASME Paper 89-GT-47.
52.
Denton, J. D., and Xu, L., 2002, “The Effects of Lean and Sweep on Transonic Fan Performance,” ASME Paper GT-2002-30327.
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