Boundary layer tripping on a transonic compressor profile

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Authors

  • A. Joseph Institute of Fluid-Flow Machinery, Polish Academy of Science (IMP PAN), Poland
  • M. Piotrowicz Institute of Fluid-Flow Machinery, Polish Academy of Science (IMP PAN), Poland
  • P. Flaszynski Institute of Fluid-Flow Machinery, Polish Academy of Science (IMP PAN), Poland
  • P. Doerffer Institute of Fluid-Flow Machinery, Polish Academy of Science (IMP PAN), Poland
  • P. Kaczynski Institute of Fluid-Flow Machinery, Polish Academy of Science (IMP PAN), Poland

Abstract

The numerical and experimental investigation of boundary layer tripping using steps on the suction side of a transonic compressor rotor has been presented in this paper. The presented research corresponds to an EU project known as TFAST (Transition Location Effects on Shock Wave Boundary Layer Interaction). A representative single passage test section has been designed to investigate the SBLI (Shock wave Boundary Layer Interaction) effects on the rotor profile. The geometrical and inflow boundary conditions have been defined by the project partner RRD (Rolls- Royce Deutschland). Two locations of step (x/c = 0.16 and x/c = 0.02) were chosen upstream of the shock location to investigate the boundary layer tripping effects and are compared with configuration without tripping setup. The numerical simulations were carried out on the test section model using the steady-state Reynolds Averaged Navier–Stokes (RANS) model with Explicit Algebraic Reynolds Stress Model (EARSM) turbulence model with transition effects included. The chosen turbulence model could accurately predict the shock location on the suction side of the lower profile in the test section and had a good agreement with wall pressure measurements using pressure taps. A detailed shock structure was captured using the schlieren technique and compared for different tripping configurations. To estimate the effectiveness of the tripping setup losses have been estimated using LDA (Laser Doppler Anemometry) along the traverse downstream the blade passage. To understand the tripping effect on the boundary layer a detailed investigation has been carried out at ten selected traverse locations from leading edge to trailing edge of the rotor profile. Based on the experimental validation of the defined numerical model for tripping setup, a few more step heights were compared at selected tripping locations numerically. To analyse the effect of step heights, the isentropic Mach number and wall shear stress are compared with without tripping configuration. The wake and stagnation pressure losses downstream of the profile have been compared to investigate the sensitivity of location and geometrical definition of the boundary layer tripping setup on the aerodynamic losses.

Keywords:

transonic aerodynamics, turbomachinery, internal flows, axial compressors, SBLI, flow control

References


  1. H.A. Schreiber, W. Steinert, B. Kusters, Effects of Reynolds number and free-stream turbulence on boundary layer transition in a compressor cascade, Journal of Turbomachinery, 124, 1, 1–9, 2002.

  2. H. Alexander, J. Klinner, S. Grund, C. Willert, W. Steinert, M. Beversdorff, On the importance of transition control at transonic compressor blades, Journal of Turbomachinery, 143, 3, 031007, 2021.

  3. D. Arnal, J. Delery, Laminar-turbulent transition and shock wave/boundary layer interaction, Office National d’Etudes et de Recherches Aérospatiales Onera-publications-tp, 109, 69, 2004.

  4. D.S. Todd, H. Babinsky, Influence of Transition on the Flow Downstream of Normal Shock Wave-boundary Layer Interaction, 54th AIAA Aerospace Science Meeting, 2016.

  5. G. Patrick, P. Flaszynski, R. Szwaba, M. Piotrowicz, P. Kaczynski, B. Tartinville, C. Hirsch, A. Hergt, Transition Location Effect on Shock Wave Boundary Layer Interaction: Experimental and Numerical Findings from the TFAST Project, Notes on Numerical Fluid Mechanics and Multidisciplinary Design, Springer, 144, 2020.

  6. A. Hergt, J. Klinner, J. Wellner, C. Willert, S. Grund, W. Steinert, M. Beversdorff, The present challenge of transonic compressor blade design, Journal of Turbomachinery, 141, 9, 091004, 2019.

  7. A. Joseph, P. Flaszynski, P. Doerffer, M. Piotrowicz, Low Reynolds Number Effect on Highly Loaded Compressor Stator Cascade, 15th European Conference on Turbomachinery Fluid Dynamics & Thermodynamics European Turbomachinery Society, 239, 2023.

  8. L. Wesley, D.M. Martin, G. Tillman, Flow control opportunities in gas turbine engines, Fluids 2000 Conference and Exhibit, 2000.

  9. M. Hecklau, C. Gmelin, W. Nitsche, F. Thiele, A.Huppertz, M. Swoboda, Experimental and numerical results of active flow control on a highly loaded stator cascade, Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 225, 7, 907–918, 2011.

  10. M. Bright, D. Culley, E. Braunscheidel, G. Welch, Closed Loop Active Flow Separation Detection and Control in a Multistage Compressor, [in:] 43rd AIAA Aerospace Science Meeting and Exhibit, 849, 2005.

  11. A. Hegt, R. Meyer, K. Engel. Experimental investigation of flow control in compressor cascades, Turbo Expo: Power for Land, Sea and Air, 4241, 2006.

  12. S. Kubacki, Z. Rarata, A. Drozdz, R. Gnatowska, V. Sokolenko, W. Elsner, Prediction of laminar-to-turbulent transition in a separated boundary layer subjected to an external acoustic forcing, Archives of Mechanics, 75, 5, 591–616, 2023.

  13. J. Tiainen, A. Gronman, A.J. Varri, J. Backman, Flow control methods and their applicability in low-Reynolds-number centrifugal compressors-a review, International Journal of Turbomachinery, Propulsion and Power, 3, 1, 2, 2018.

  14. V. Shinde, J. McNamara, D. Gaitonde, Control of transitional shock wave boundary layer interaction using structurally constrained surface morphing, Aerospace Science and Technology, 96, 105545, 2020.

  15. P. Doerffer, O. Szulc, Shock wave smearing by wall perforation, Archives of Mechanics, 58, 6, 543–573, 2006.

  16. C. Lietmeyer, B. Denkena, T. Krawczyk, R. Kling, L. Overmeyer, B. Wojakowski, E. Reithmeier, R. Scheuer, T. Vynnyk, J.R. Seume, Recent advances in manufacturing of riblets on compressor blades and their aerodynamic impact, Journal of Turbomachinery, 135, 4, 041008, 2013.

  17. N. Tabatabaei, R. Vinuesa, R. Örlü, P. Schlatter, Techniques for turbulence tripping of boundary layers in RANS simulations, Flow, Turbulence and Combustion, 108, 3, 661–682, 2022.

  18. P. Doerffer, P. Flaszynski, J.P. Dussauge, H. Babinsky, P. Grothe, A. Petersen, F. Billard [eds.], Transition Location Effect on Shock Wave Boundary Layer Interaction: Experimental and Numerical Findings from the TFAST Project, Springer Nature, 144, 2020.

  19. P. Flaszynski, P. Doerffer, R. Szwaba, M. Piotrowicz, P. Kaczynski, Laminar-turbulent transition tripped by step on transonic compressor profile, Journal of Thermal Science, 27, 1, 1–7, 2018.

  20. P. Flaszynski, P. Doerffer, R. Szwaba, P. Kaczynski, M. Piotrowicz, Shock wave boundary layer interaction on suction side of compressor profile in single passage test section, Journal of Thermal Science, 24, 510–515, 2015.

  21. J. Antony, W. Schmidt, E. Turkel, Numerical solution of the Euler equations by finite volume methods using Runge Kutta time stepping schemes, 14th Fluid and Plasma Dynamics Conference, 1981.

  22. Numeca FINETM/Turbo Theoretical Manual Documentation, 17, 1a, 2022.

  23. F.R. Menter, A.V. Garbaruk, Y. Egorov, Explicit algebraic Reynolds stress models for anisotropic wall-bounded flows, Progress in Flight Physics, 3, 89–104, 2012.

  24. H. Blasius, The boundary layers in fluids with little friction, National Advisory Committee for Aeronautics, 1256, 1950.