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A quasi-one-dimensional CFD model for multistage turbomachines

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Abstract

The objective of this paper is to present a fast and reliable CFD model that is able to simulate stationary and transient operations of multistage compressors and turbines. This analysis tool is based on an adapted version of the Euler equations solved by a time-marching, finite-volume method. The Euler equations have been extended by including source terms expressing the blade-flow interactions. These source terms are determined using the velocity triangles and a row-by-row representation of the blading at mid-span. The losses and deviations undergone by the fluid across each blade row are supplied by correlations. The resulting flow solver is a performance prediction tool based only on the machine geometry, offering the possibility of exploring the entire characteristic map of a multistage compressor or turbine. Its efficiency in terms of CPU time makes it possible to couple it to an optimization algorithm or to a gas turbine performance tool. Different test-cases are presented for which the calculated characteristic maps are compared to experimental ones.

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References

  1. Sellers J.F., Daniele C.J., 1975: DYNGEN-A Program for Calculating Steady-State and Transient Performance of Turbojet and Turbofan Engines, NASA Technical Note TN-D-7901.

  2. Reddy K.C., Nayani S.N., 1985: Compressor and Turbine Models-Numerical Stability and Other Aspects, AEDC Report TR-85-5.

  3. Garrard G.D., 1995: ATEC: The Aerodynamic Turbine Engine Code for the Analysis of Transient and Dynamic Gas Turbine Engine System Operations, Ph.D. Thesis, University of Tennessee, USA.

    Google Scholar 

  4. O’Brien W.F., 1992: Dynamic Simulation of Compressor and Gas Turbine Performance, AGARD LS-183, pp. 5.1–5.28.

  5. Davis M.W.Jr, 1987: A Post-Stall Compression System Modeling Technique, NASA Technical Report AD-A177610.

  6. Bloch G.S., O’Brien W.F., 1992: A Wide-Range Axial-Flow Compressor Stage Compressor Model, ASME Paper 92-GT-58.

  7. Schobeiri M.T., Attia M., Lippke C., 1994: GETRAN: A Generic, Modularly Structured Computer Code for Simulation of Dynamic Behaviour of Aero-and Power Generation Gas Turbine Engines, ASME Journal of Engineering for Power, Vol 116, pp. 483–494.

    Google Scholar 

  8. Day I.J., Freeman C., 1993: The Unstable Behaviour of Low and High Speed Compressors, ASME Paper 93-GT-26

  9. Vavra M.H., 1960: Aero-Thermodynamics and Flow in Turbomachines, John Wiley and Sons, New-York.

    Google Scholar 

  10. Lieblein S., 1965: Experimental Flow in Two-Dimensional Cascades, NASA SP-36, pp. 183–226.

  11. Creveling H.F., Carmody R.H., 1968: Axial Flow Compressor Computer Program for Calculating Off-Design Performance (Program IV), NASA Contract Report CR-72427.

  12. Çetin M., Üçer A.Ş., Hirsch Ch., Serovy G.K., 1987: Application of Modified Loss Correlations to Transonic Axial Compressors, AGARD Report 745.

  13. Cahill J.E., 1997: Identification and Evaluation of Loss and Deviation Models for Use in Transonic Compressor Stage Performance Prediction, M.Sc. Thesis, Virginia Polytechnic Institute and State University, USA.

    Google Scholar 

  14. Koch C.C., Smith L.H.Jr, 1976: Loss Sources and Magnitudes in Axial-Flow Compressors, ASME Journal of Engineering for Power, july 1976, pp. 411–424.

  15. Horlock J.H., 1958: Axial Flow Compressors, Butterworths Scientific Publications, London, UK.

    Google Scholar 

  16. Cumpsty N.A., 1989: Compressor Aerodynamics, Longman Scientific & Technical, Harlow, UK.

    Google Scholar 

  17. Aungier R.H., 2003: Axial-Flow Compressors-A Strategy for Aerodynamic Design and Analysis, ASME Press, New York, USA.

    Google Scholar 

  18. Roberts W.B., Serovy G.K., Sandercock D.M., 1986: Modeling the 3D Flow Effects on Deviation Angle for Axial Compressor Middle Stages, ASME Journal of Engineering for Gas Turbines and Power, vol. 108, pp. 131–137.

    Google Scholar 

  19. Ainley D.G., Mathieson G.C.R., 1951: A Method for Performance Estimation of Axial-Flow Turbines, ARC R&M 2974.

  20. Ainley D.G., Mathieson G.C.R., 1951: An Examination of the Flow and Pressure Losses in Blade Rows of Axial-Flow Turbines, ARC R&M 2891.

  21. Dunham J., Came P.M., 1970: Improvements to the Ainley-Mathieson Method of Turbine Performance Prediction, ASME Journal of Engineering for Power, July 1970.

  22. Kacker S.C., Okapuu U., 1982: Mean line Prediction Method for Axial Flow Turbine Efficiency, ASME Journal of Engineering for Power vol. 104/1, pp 111–119.

    Google Scholar 

  23. Zhu J., Sjolander S.A., 2005: Improved Profile Loss and Deviation Correlations for Axial-Turbine Blade Rows, Proceedings of ASME Turbo Expo 2005, paper GT2005-69077.

  24. Benner M.W., Sjolander S.A., Moustapha S.H., 1997: Influence of Leading-Edge Geometry on Profile Losses in Turbines at Off-Design Incidence: Experimental Results and an Improved Correlation, ASME Journal of Turbomachinery, vol. 119, pp 193–200.

    Article  Google Scholar 

  25. Benner M.W., Sjolander S.A., Moustapha S.H., 2005: An Empirical Prediction Method for Secondary Losses in Turbines: Part I — A New Loss Breakdown Scheme and Penetration Depth Correlation, Proceedings of ASME Turbo Expo 2005, paper GT2005-68637.

  26. Benner M.W., Sjolander S.A., Moustapha S.H., 2005: An Empirical Prediction Method for Secondary Losses in Turbines: Part II — A New Secondary Loss Correlation, Proceedings of ASME Turbo Expo 2005, paper GT2005-68639.

  27. Dunham J., 1970: A Review of Cascade Data on Secondary Losses in Turbines, Journal of Mechanical Engineering Science, vol. 12/1, pp 48–59.

    Article  MathSciNet  Google Scholar 

  28. Stratford, B.S., 1967: The Use of Boundary Layer Techniques to Calculate the Blockage from the Annulus Boundary Layers in a Compressor, ASME Paper 67-WA/GT-7.

  29. Craig H.R.M., Cox H.J.A, 1970: Performance Estimation of Axial Flow Turbines, Proceedings of the Institution of Mechanical Engineers 1970–71, vol. 185 32/71, pp 407–424.

    Article  Google Scholar 

  30. Wei N., 2000: Significance of Loss Models in Aerother-modynamic Simulation for Axial Turbines, PhD Thesis, Royal Institute of Technology (KTH), Sweden.

    Google Scholar 

  31. Hirsch Ch., 1988: Numerical Computation of Internal and External Flows — Volume 1: Fundamentals of Numerical Discretization, John Wiley & Sons, Chichester, UK.

    MATH  Google Scholar 

  32. Jennions I.K., Stow P., 1985: A Quasi Three Dimensional Turbomachinery Blade Design System: Part 1-Throughflow Analysis, ASME Journal of Engineering for Gas Turbines and Power, vol. 107, pp. 301–307.

    Article  Google Scholar 

  33. Barth T.J., 1993: Recent Developments in High Order K-Exact Reconstruction on Unstructured Meshes, AIAA Paper 93-0668.

  34. Horlock J.H., Perkins H.J., 1974: Annulus Wall Boundary Layers in Turbomachines, AGARD Lecture Series AG-185.

  35. Burdsall E.A., Canal E.Jr, Lyons K.A., 1979: Core Compressor Exit Stage Study-I. Aerodynamic and Mechanical Design, NASA Contract Report CR-159714.

  36. Behlke R.F., Burdsall E.A., Canal E.Jr, Korn N.D., 1980: Core Compressor Exit Stage Study — II. Final Report, NASA Contract Report CR-159812.

  37. Timko L.P., 1984: Energy Efficient Engine High Pressure Turbine Component Test Performance Report, NASA Contract Report 168289.

  38. Rodriguez C.G., 1997: One-Dimensional, Finite-Rate Model for Gas-Turbine Combustors, Ph.D. Thesis, Virginia Polytechnic Institute and State University, USA.

    Google Scholar 

  39. Hartsel J.E., 1972: Prediction of Effects of Mass-Transfer Cooling on the Blade Row Efficiency of Turbine Airfoils, AIAA Paper 72-11.

  40. Ito S., Eckert E.R.G., Goldstein R.J., 1980: Aerodynamic Loss in a Gas Turbine Stage with Film Cooling, ASME Journal of Engineering for Power, vol. 102, pp 964–970.

    Article  Google Scholar 

  41. Aungier R.H., 2000: Centrifugal Compressors: a Strategy for Aerodynamic Design and Analysis, ASME Press, New York.

    Google Scholar 

  42. von Backström T.W., 2006: A Unified Correlation for Slip Factors in Centrifugal Impellers, ASME Journal of Turbomachinery, vol. 128, pp 1–10.

    Article  Google Scholar 

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Authors and Affiliations

  1. University of Liège — Turbomachinery Group, Liege, Belgium

    Olivier Léonard & Olivier Adam

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  1. Olivier Léonard
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  2. Olivier Adam
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Correspondence to Olivier Léonard.

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Léonard, O., Adam, O. A quasi-one-dimensional CFD model for multistage turbomachines. J. Therm. Sci. 17, 7–20 (2008). https://doi.org/10.1007/s11630-008-0007-z

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  • DOI: https://doi.org/10.1007/s11630-008-0007-z

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