Skip to main content
SpringerLink
Log in

Unsteady CFD Simulation of Transonic Axial Compressor Stages with Distorted Inflow

  • Conference paper
  • First Online:
Advances in Simulation of Wing and Nacelle Stall (FOR 1066 2014)

Part of the book series: Notes on Numerical Fluid Mechanics and Multidisciplinary Design ((NNFM,volume 131))

Included in the following conference series:

Abstract

The research unit “Simulation of Wing and Nacelle Stall” (FOR1066) funded by the DFG, Airbus, and Rolls Royce Deutschland, investigates new numerical methods to simulate wings in high lift configurations, nacelles and highly loaded compressors coupled in one single simulation environment, and coupled meteorological simulation of wind gusts. Subgroup B of FOR1066 deals with aircraft nacelle stall and its interaction with the jet engine. In this paper latest results of project B2 are presented, putting the focus on numerical investigations and detailed analyses of interaction phenomena between distorted inflow and a transonic axial compressor stage.

The challenge in simulating such configurations was approached by coupling two specialized CFD codes: TAU for the external flow around the nacelle and TRACE for the internal flow through the compressor. A coupling library has been implemented and applied to several test and validation cases. Details of the numerical complexity of the setup and initialization of coupled simulations and the challenges to approach complex configurations are outlined in the paper.

The research unit uses two different test cases to study the impact of flow distortions on transonic compressors in detail, namely the DLR-R030 test case and the axial compressor rig of TU Darmstadt in its rotor1 configuration. The Darmstadt rig has been modified for the purposes of the research unit to investigate the influence of inflow distortions on compressor performance and provided highly detailed and well validated simulation results. Different flow distortion generating devices were designed and analyzed, which led to a deeper understanding of the unsteady behavior of the flow in axial compressors. One major result is the finding, that at the distortion boundaries static pressure and inflow velocity become decoupled during their propagation through the compressor stage. This provides an explanation for the unsteady flow features observed in both experiment and simulation.

This is a preview of subscription content, log in via an institution to check access.

Access this chapter

Log in via an institution
Chapter
USD 29.95
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
eBook
USD 169.00
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
Hardcover Book
USD 219.99
Price excludes VAT (USA)
  • Durable hardcover edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info

Tax calculation will be finalised at checkout

Purchases are for personal use only

Institutional subscriptions

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. Ciorciari, R., Lesser, A., Blaim, F., Niehuis, R.: Tip clearance investigation for an axial transonic compressor. In: Proc. of the 10th Int. Symp. on Experimental Computational Aerothermodynamics of Internal Flows, Brussels, Belgium (2011)

    Google Scholar 

  2. Dunker, R., Hungenberg, H.: Transonic axial compressure using laser anemomentry and unsteady measurements. AIAA Journal 18 (1980)

    Google Scholar 

  3. Jerez Fidalgo, V., Hall, C.A., Colin, Y.: A Study of Fan-Distortion Interaction within the NASA Rotor 67 Transonic Stage. ASME paper GT2010-22914 (2010)

    Google Scholar 

  4. Gunn, E., Tooze, S., Hall, C., Colin, Y.: An Experimental Study of the Onception of Rotation Stall in a Single-Stage Low-Speed Axial Compressor. ASME paper GT2012-68888 (2012)

    Google Scholar 

  5. Iseler, J., Niehuis, R.: Steady and Unsteady Flow-Simulation of an Axial Transonic Compressor Stage. AIAA (2008)

    Google Scholar 

  6. Iseler, J.: Numerische Untersuchung des instation Strmungs- und Leistungsverhaltensvon Verdichterbeschaufelungen bei homogener und gestrter Zustrmung. PhD thesis, Fakulttfr Luft- und Raumfahrttechnik, Universitt der Bundeswehr Mnchen (2011)

    Google Scholar 

  7. Kelleners, P., Heinrich, R.: Accurate simulation of atmosphere-aircraft interaction. In: 19. DGLR-Fach-Symposium der STAB, November 04-05, München, Deutschland (2014)

    Google Scholar 

  8. Kozulovic, D., Rber, T., Kgeler, E., Nrnberger, D.: Modifications of a two-equation turbulence model for turbomachinery fluid flows. Deutscher Luft- und Raumfahrtkongress, Dresden (2004)

    Google Scholar 

  9. Lecht, M.: Beitrag zum Verhalten von Axialverdichterstufen, Dissertation, RWTH Aachen (1983)

    Google Scholar 

  10. Lesser, A., Niehuis, R.: Detailed numerical investigation of a transonic axial compressor stage with inlet distortions. In: Proc. of the 10th Int. Symp. on Experimental Computational Aerothermodynamics of Internal Flows, Brussels, Belgium (2011)

    Google Scholar 

  11. Lesser, A., Niehuis, R.: Numerical Investigation of a Highly Loaded Axial Compressor Stage with Inlet Distortions. ASME paper GT2011-46457 (2011)

    Google Scholar 

  12. Lesser, A., Ciociari, R., Barthmes, S., Niehuis, R.: Numerical investigation of the effect of inflow distortions on transonic axial compressor stages. In: Int. Symp. “Simulation of Wing and Nacelle Stall”, Braunschweig, Germany (2012)

    Google Scholar 

  13. Lesser, A., Niehuis, R.: A Study about Transonic Axial Compressors with Total Pressure Inlet Flow Field Distortions. ASME paper GT2014-26627 (2014)

    Google Scholar 

  14. Lesser, A.: Numerische Untersuchung von Axialverdichtern mit gestrter Zustrmung. PhDthesis, Fakultt fr Luft- und Raumfahrttechnik, Universitt der Bundeswehr Mnchen (2014) (to be published)

    Google Scholar 

  15. Longley, J.P., Greitzer, E.M.: Inlet Distortion Effects in Aircraft Propulsion System Integration. AGARD-LS-183 (1992)

    Google Scholar 

  16. Mazzawy, R.: Multiple Segment Parallel Compressor Model for Circumferential Flow Distortion. J. of Eng. for Power 99(2), 288–297 (1977)

    Article  Google Scholar 

  17. Niehuis, R., Lesser, A., Probst, A., Radespiel, R., Schulze, S., Khler, C.J., Spiering, F., Kroll, N., Wartzek, F., Schiffer, H.-P.: Simulation of nacelle stall and engine response. In: Proc. of the XXI. Int. Symp. on Air Breathing Engines (ISABE), ISABE-2013-1402, Busan, Korea (2013)

    Google Scholar 

  18. Nrnberger, D.: Implizite Zeitintegration fr die Simulation von Turbomaschinenstrmungen. DLR Forschungsbericht 2004-27 (2004)

    Google Scholar 

  19. Reid, C.: The Response of Axial Flow Compressor to Intake Flow Distortion. ASME paper 69-GT-29 (1969)

    Google Scholar 

  20. SAE Aerospace Information Report: Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines. SAE AIR1419 Rev. A (1999)

    Google Scholar 

  21. Schulze, S., Khler, C.J., Radespiel, R.: On the comparison of stalling flow-through nacelles and powered inlets at take-off conditions. In: CEAS (2007)

    Google Scholar 

  22. Schulze, G.: Betriebsverhalten eines transsonischen Axialverdichters. Dissertation, TU Darmstadt (1996)

    Google Scholar 

  23. Schwamborn, D., Gerhold, T., Heinrich, R.: The DLR TAU-Code: Recent applications in research and industry. In: Proc. of the European Conference on Computational Fluid Dynamics (ECCOMAS CFD 2006), September 5-8, Delft, The Netherlands (2006)

    Google Scholar 

  24. Spiering, F.: Coupling of TAU and TRACE for parallel accurate flow simulations. In: Int. Symp. “Simulation of Wing and Nacelle Stall”, Braunschweig Germany (2012)

    Google Scholar 

  25. Spiering, F., Kelleners, P.: Coupling of flow solvers with variable accuracy of spatial discretization. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, pp. 415–423. Springer (2014), ISBN 978-3-319-03157-6. ISSN 1612-2909

    Google Scholar 

  26. Wartzek, F., Brandsttter, C., Holzinger, F., Schiffer, H.-P.: Realistic inlet distortion patterns interacting with a transonic compressor stage. In: Int. Symp. “Simulation of Wing and NacelleStall” (2014)

    Google Scholar 

  27. Yamada, K., Furukawa, M., Nakano, T., Inoue, M., Funazaki, K.: Unsteady Three-Dimensional Flow Phenomena Due to Breakdown of Tip Leakage Vortex in a Transonic Axial Compressor Rotor. ASME paper GT2004-53745 (2004)

    Google Scholar 

  28. Yang, H., Nrnberger, D., Weber, A.: A Conservative Zonal Approach with Applications toUnsteady Turbomachinery Flows. DGLR-JT2002-073 (2002)

    Google Scholar 

  29. Yang, H., Nrnberger, D., Nicke, E., Weber, A.: Numerical Investigation of Casing Treatment Mechanisms with a Conservative Mixed-Cell Approach. ASME paper GT2003-38483 (2003)

    Google Scholar 

  30. Yao, J., Gorrell, S.E., Wadia, A.R.: High-Fidelity Numerical Analysis of Per-Rev-Type Inlet Distortion Transfer in Multistage Fans - Part I: Simulations with Selected Blade Rows. J. of Turbomach 132(041015), 1–10 (2010)

    Google Scholar 

  31. Yao, J., Gorrell, S.E., Wadia, A.R.: High-Fidelity Numerical Analysis of Per-Rev-Type Inlet Distortion Transfer in Multistage Fans - Part II: Entire Component Simulation and Investigation. J. of Turbomach 132(041015), 11–17 (2010)

    Google Scholar 

Download references

Author information

Authors and Affiliations

  1. Institute for Jet Propulsion, Universität der Bundeswehr München, Werner-Heisenberg-Weg 39, 85577, Neubiberg, Germany

    Sebastian Barthmes, Jakob P. Haug, Andreas Lesser & Reinhard Niehuis

Authors
  1. Sebastian Barthmes
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Jakob P. Haug
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Andreas Lesser
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Reinhard Niehuis
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Jakob P. Haug .

Editor information

Editors and Affiliations

  1. Institute of Fluid Mechanics, Technische Universität Braunschweig, Braunschweig, Germany

    Rolf Radespiel

  2. Institute of Jet Propulsion, Universität der Bundeswehr München, Neubiberg, Germany

    Reinhard Niehuis

  3. Institute of Aerodynamics and Flow Technology, German Aerospace Center (DLR), Braunschweig, Germany

    Norbert Kroll

  4. Institute of Fluid Mechanics, Technische Universität Braunschweig, Braunschweig, Germany

    Kathrin Behrends

Rights and permissions

Reprints and permissions

Copyright information

© 2016 Springer International Publishing Switzerland

About this paper

Cite this paper

Barthmes, S., Haug, J.P., Lesser, A., Niehuis, R. (2016). Unsteady CFD Simulation of Transonic Axial Compressor Stages with Distorted Inflow. In: Radespiel, R., Niehuis, R., Kroll, N., Behrends, K. (eds) Advances in Simulation of Wing and Nacelle Stall. FOR 1066 2014. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 131. Springer, Cham. https://doi.org/10.1007/978-3-319-21127-5_18

Download citation

  • DOI: https://doi.org/10.1007/978-3-319-21127-5_18

  • Published:

  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-21126-8

  • Online ISBN: 978-3-319-21127-5

  • eBook Packages: EngineeringEngineering (R0)

Publish with us

Policies and ethics

Search

Navigation