Hostname: page-component-78c5997874-dh8gc Total loading time: 0 Render date: 2024-11-15T02:25:11.987Z Has data issue: false hasContentIssue false
  • English
  • Français

Experimental audit of the mixing-plane approach to turbomachinery analysis and a review of alternative multi-row techniques

Published online by Cambridge University Press:  04 July 2016

C. Lockwood ,
P. C. Ivey  and
R. G. Wells
C. Lockwood
Affiliation:
School of Mechanical Engineering, Cranfield University, Cranfield, UK
P. C. Ivey
Affiliation:
School of Mechanical Engineering, Cranfield University, Cranfield, UK
R. G. Wells
Affiliation:
ALSTOM Gas Turbines Limited, Lincoln, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

Detailed numerical comparisons of pressure and flow angle measurements made in stage three of a four-stage, large scale, low speed, axial compressor are presented. The measurements are in both the rotating and stationary frame and were obtained as part of a BRITE/EURAM collaborative study of cantilevered and shrouded-stator compressor configurations. The numerical analysis is 3D, considers three blade rows simultaneously and incorporates multiple row effects by use of a conservative mixing-plane model allowing circumferential variation at the mixing plane.

The paper discusses the early results of a study sponsored by Alstom Gas Turbines to examine steady-state, multiple blade-row modelling techniques. Growth in the endwall flow region due to multi-row effects is revealed from both the numerical and experimental results. The numerical simulation is conducted without altering blade gap spacings to assist numerical stability; the axial gap is increasingly being seen as a critical performance parameter for multiple row analysis. The limitations inherent in an approach using mixing-planes are presented and a review of alternative, more rigourous, treatments of these effects is then discussed. These treatments attempt to retain the unsteady flow structure in a steady-state model by the derivation of so-called deterministic stresses.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1033 , March 2000 , pp. 117 - 124
Copyright
Copyright © Royal Aeronautical Society 2000 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. 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.Google Scholar
2. Erdos, J.I., Alzner, E. and McNally, W. Numerical solution of periodic transonic flow through a fan stage, AIAA 76-369, 1976.Google Scholar
3. Denton, J.D. and Singh, U.K. Timemarchingmethodsfor turbomachinery flow calculation, VKI lecture series 1979-7, 1979.Google Scholar
4. Denton, J.D. The calculation of fully three-dimensional flow through any type of turbomachine blade-row, AGARD LS-140 3-D computation techniques applied to internal flows in propulsion systems, paper 9, 1985.Google Scholar
5. Deregel, P. and Tan, C.S. Impact of rotor wakes on steady-state axial compressor performance, ASME 96-GT-253, 1996.Google Scholar
6. Adamczyk, J.J. Wake mixing in axial-flow compressors, ASME 96- GT-29, 1996.Google Scholar
7. Van Zante, D.E., Adamczyk, J.J., Strazisar, A.J. and Okiishi, T.H. Wake recovery performance benefit in a high-speed axial compressor, ASME 97-GT-535, 1997.Google Scholar
8. Politis, E.S., Giannakoglou, K.C. and Papailiou, K.D.Axial compressor stage analysis through a multi-block 3D Navier-Stokes solution method, ASME 97-GT-93, 1997.Google Scholar
9. Copenhaver, W.W., Hah, C. and Puterbaugh, S.L. Three-dimensional flow phenomena in a transonic, high-throughflow, axial-flow compressor stage, ASME 92-GT-169, 1992.Google Scholar
10. Ni, R.R. and Bogoian, J.C. Prediction of 3D multi-stage turbine flow field using a multiple-grid Euler solver, AIAA 89-0203, 1989.Google Scholar
11. Arnone, A. and Benvenuti, E. Three-dimensional Navier-Stokes analysis of a two-stage gas turbine, ASME 94-GT-88, 1994.Google Scholar
12. Kim, S.C. and Stubbs, R.M. Numerical study of a high work low-aspect ratio turbine stage, AIAA Paper 95-3043, 1995.Google Scholar
13. Shikano, Y. Numerical analysis of the flow field through a turbine stage with bucket tip clearance, JSME, Series B, 1993, 38, (4), pp 593–599.Google Scholar
14. Foley, A.C. Tip Clearance Effects in Low Speed, Axial Flow Compressors, PhD Thesis, Cranfield University, 1995.Google Scholar
15. Swoboda, M., Ivey, P.C., Wenger, U. and Gummer, V. An experimental examination of cantilevered and shrouded stators in a multi-stage axial compressor, ASME 98-GT-282, 1998.Google Scholar
16. Ivey, P.C. and Swoboda, M. Leakage effects in the rotor tip-clearance region of a multi-stage axial compressor, part 1: innovative experiments, ASME 98-GT-591, 1998.Google Scholar
17. Howard, M.A., Ivey, P.C, Barton, J.P. and Young, K.F. Endwall effects at two tip clearances in a multi-stage axial flow compressor with controlled diffusion blading, ASME 93-GT-299, 1993.Google Scholar
18. Smout, P.D. The Measurement of Near Wall Flows Using Pneumatic Wedge Probes, PhD Thesis, Cranfield University, 1995.Google Scholar
19. Smout, P.D. and Ivey, P.C. The effect of pressure probe characteristics on the validation of modelled aero-engine compressor blades, Proc RAeS, Paper 8, London, 23-24 Nov 1998.Google Scholar
20. Elmendorf, W., Mildner, F., Roper, R., Kruger, U. and Kluck, M. Three-dimensional analysis of a multi-stage compressor flow field, ASME 98-GT-249, 1998.Google Scholar
21. Von Hoyningen-Huene, M. and Hermeler, J. Comparison of three approaches to model stator-rotor interaction in the turbine front stage of an industrial gas turbine, IMechE C557/018/99, 1999.Google Scholar
22. Politis, E.S., Giannakoglou, K.C. and Papailiou, K.D. Leakage effects in the rotor tip-clearance region of a multi-stage axial compressor, part 2: numerical modelling, ASME 98-GT-592, 1998.Google Scholar
23. Galpin, P.F., Broberg, R.B. and Hutchinson, B.R. Three-dimensional Navier-Stokes predictions of steady-state rotor/stator interaction with pitch change, 3rd Canadian CFD conf, 1995.Google Scholar
24.AEA CFX-TASCflow version 2.7.2 — User documentation; AEA Technology, 1997.Google Scholar
25. Gwilliam, N.J. and Kingston, T.R. Validation of advanced computational fluid dynamics in the design of military turbines, Proc RAeS, Paper 17, London, 23–24 Nov 1998.Google Scholar
26. Hall, E.J. Aerodynamic modelling of multistage compressor flowfields I— analysis of rotor/stator/rotor aerodynamic interaction, ASME 97- GT-344,1997.Google Scholar
27. Adamczyk, J.J. Model equation for simulating flows in multistage turbomachinery, ASME 85-GT-226, 1985.Google Scholar
28. Dawes, W.N. Current and future developments in turbomachinery CFD, 2nd European Turbomachinery, Fluid Dynamics and Thermodynamics conf, 1997.Google Scholar
29. Adamczyk, J.J., Mulac, R.A. and Celestina, M.L. A model for closing the inviscid form of the average-passage equation system, ASME 86- GT-227, 1986.Google Scholar
30. Rhie, CM., Gleixner, A.J., Spear, D.A., Fischberg, C.J. and Zacharias, R.M. Development and application of a multi-stage Navier- Stokes solver, part I: multi-stage modelling using bodyforces and deterministic stresses, ASME 95-GT-342, 1995.Google Scholar
31. LeJambre, C.R., Zacharias, R.M., Biederman, B.P., Gleixner, A.J. and Yetka, C.J. Development and application of a multi-stage Navier- Stokes solver, part II: application to a high pressure compressor design, ASME 95-GT-343, 1995.Google Scholar
33. Hall, E.J. Aerodynamic modelling of multistage compressor flowfields II— modelling deterministic stresses, ASME 97-GT-345, 1997.Google Scholar
34. Sondak, D.L., Dorney, D.J. and Davis, R.L. Modelling turbomachinery unsteadiness with lumped deterministic stresses, AIAA 96-2570, 1996.Google Scholar
35. Sharma, O.P., Stetson, G.M., Daniels, W.A., Greitzer, E.M., , Blair, M.F. and Dring, R.P. Impact of periodic unsteadiness on performance and heat load in axial flow turbomachines, NASA CR-202319, 1997.Google Scholar