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Numerical investigation of effect of inlet swirl and total-pressure distortion on performance and stability of an axial transonic compressor

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Abstract

This paper represents numerical simulation of flow inside an axial transonic compressor subject to inlet flow distortion, to evaluate its effect on compressor performance and stability. Two types of inlet distortion, namely inlet swirl and total pressure distortion are investigated. To study the effect of combined distortion patterns, different combinations of inlet swirl and total pressure distortion are also studied. Results for cases with total pressure distortion indicate that hub radial distortion improves stability range of the compressor while tip radial distortion deteriorates it. An explanation for this observation is presented based on redistribution of flow parameters caused by distortion and the way it interacts with stall inception mechanisms in a transonic axial compressor. Results also show that while co-swirl patterns slightly improve stability range of the compressor, counter-swirl patterns diminish it. Study of combined distortion cases reveals that superimposition of effects of each individual pattern could predict the effect of a combined pattern on compressor’s performance within an accuracy of 1%. However, it is unable to predict the associated effect on compressor’s stability.

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References

  1. SAE S-16 Committee. "ARP 1420." Revision B, ”Gas Turbine Inlet Flow Distortion Guidelines,” Society of Automotive Engineers (2002).

    Google Scholar 

  2. Sheoran, Y., B. Bouldin, and P. M. Krishnan. “Compressor Performance and Operability in Swirl Distortion.” Journal of Turbomachinery 134, no. 4 (2012): 041008.

    Article  Google Scholar 

  3. Fredrick, N., and M. Davis. “Investigation of the Effects of Inlet Swirl on Compressor Performance and Operability Using a Modified Parallel Compressor Model.” In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, Vancouver, Canada, (2011).

    Google Scholar 

  4. Nie, Chaoqun, Jingxuan Zhang, Zhiting Tong, and Hongwu Zhang. “The response of a low speed compressor on rotating inlet distortion.” Journal of Thermal Science 15, no. 4 (2006): 314–318.

    Article  ADS  Google Scholar 

  5. Davis, M., and A. Hale. “A parametric study on the effects of inlet swirl on compression system performance and operability using numerical simulations.” In ASME Turbo Expo 2007: Power for Land, Sea, and Air, pp. 1–10. Montreal, Canada, 2007.

    Chapter  Google Scholar 

  6. Khaleghi, H., G. Doulgeris, M. Boroomand, P. Pilidis, and A. M. Tousi. “A method for calculating inlet distortion effects on stability of split-flow fans.” Aeronautical Journal 113, no. 1147 (2009): 591–598.

    Article  Google Scholar 

  7. Iseler, Jens, A. Lesser, and R. Niehuis. “Numerical Investigation of a Transonic Axial Compressor Stage with Inlet Distortions.” In High Performance Computing in Science and Engineering, Garching/Munich 2009, pp. 185–195. 2010.

    Google Scholar 

  8. V. J. Fidalgo, C. Hall and Y. Colin, “A Study of Fan-Distortion Interaction Within the NASA Rotor 67 Transonic Stage,” J Turbomach, vol. 134, no. 5, p. 051011, 2012.

    Article  Google Scholar 

  9. Du, J., Lin, F., Chen, J., Morris, S. C., and Nie, C., “Numerical study on the influence mechanism of inlet distortion on the stall margin in a transonic axial rotor.” Journal of Thermal Science 21, no. 3 (2012): 209–214.

    Article  ADS  Google Scholar 

  10. Leinhos, D. C., Norbert R. Schmid, and Leonhard Fottner. “The influence of transient inlet distortions on the instability inception of a low-pressure compressor in a turbofan engine.” Journal of turbomachinery 123, no. 1 (2001): 1–8.

    Article  Google Scholar 

  11. Lin, F., M. Li and J. Chen, “Long-to-short length-scale transition: a stall inception phenomenon in an axial compressor with inlet distortion,” J Turbomach, vol. 128, no. 1, pp. 130–140, 2006.

    Article  Google Scholar 

  12. Naseri, A., M. Boroomand, and A. M. Tousi. “The Effect of Inlet Flow Distortion on Performance of a Micro-Jet Engine: Part 1—Development of an Inlet Simulator.” In ASME 2012 International Mechanical Engineering Congress and Exposition, pp. 317–324. Houston, USA, 2012.

    Google Scholar 

  13. Naseri, A., M. Boroomand, A. M. Tousi, and A. R. Alihosseini. “The Effect of Inlet Flow Distortion on Performance of a Micro-Jet Engine: Part 2—Engine Tests.” In ASME 2012 International Mechanical Engineering Congress and Exposition, pp. 311–316. Houston, USA, 2012.

    Google Scholar 

  14. Gunn, E. J., S. E. Tooze, C. A. Hall and Y. Colin, “An experimental study of loss sources in a fan operating with continuous inlet stagnation pressure distortion,” J Turbomach, vol. 135, no. 5, p. 051002, 2013.

    Article  Google Scholar 

  15. Castaneda, J., A. Mehdi, D. di Cugno, and V. Pachidis. “A preliminary numerical CFD analysis of transonic compressor rotors when subjected to inlet swirl distortion.” In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, pp. 417–429. Vancouver, Canada, 2011.

    Google Scholar 

  16. Cameron, J. D., M. A. Bennington, M. H. Ross, S. C. Morris, J. Du, F. Lin, and J. Chen. “The Influence of Tip Clearance Momentum Flux on Stall Inception in a High-Speed Axial Compressor.” Journal of Turbomachinery 135, no. 5 (2013): 051005.

    Article  Google Scholar 

  17. Strazisar, A. J., J. R. Wood, M. D. Hathaway, and K. L. Suder. “Laser anemometer measurements in a transonic axial-flow fan rotor.” NASA TP-2879, (1989).

    Google Scholar 

  18. Khaleghi, H., A. M. Tousi, M. Boroomand, and J. A. Teixeira. “Recirculation casing treatment by using a vaned passage for a transonic axial-flow compressor.” Proc IMechE, Part A: Journal of Power and Energy 221, no. 8 (2007): 1153–1162.

    Article  Google Scholar 

  19. Khaleghi, H., M. Boroomand, J. A. Teixeira, and A. M. Tousi. “A numerical study of the effects of injection velocity on stability improvement in high-speed compressors.” Proc IMechE, Part A: Journal of Power and Energy 222, no. 2 (2008): 189–198.

    Article  Google Scholar 

  20. Sammak, S. and M. Boroomand, “Three dimensional numerical analysis of flow within an isolated rotor with stepped blades,” Journal of Thermal Science 21, no. 5, pp. 420–427, 2012.

    Article  ADS  Google Scholar 

  21. Cumpsty, N. A. Compressor aerodynamics. Longman Scientific & Technical, London, 1989.

    Google Scholar 

  22. Vo, Huu Duc, Choon S. Tan, and Edward M. Greitzer. “Criteria for spike initiated rotating stall.” Journal of turbomachinery 130, no. 1 (2008): 011023.

    Article  Google Scholar 

  23. Moore, F. K., and E. M. Greitzer. “A theory of post-stall transients in axial compression systems: Part I—Development of equations.” Journal of engineering for gas turbines and power 108, no. 1 (1986): 68–76.

    Article  Google Scholar 

  24. Longley, J. P. “A review of nonsteady flow models for compressor stability.” Journal of turbomachinery 116, no. 2 (1994): 202–215.

    Article  ADS  Google Scholar 

  25. Wu, Y., Q. Li, W. Chu, H. Zhang and Z. Su, “Numerical investigation of the unsteady behaviour of tip clearance flow and its possible link to stall inception,” Proc IMechE, Part A: J Power and Energy, vol. 224, no. 1, pp. 85–96, 2010.

    Article  Google Scholar 

  26. Tan, C. S., I. Day, S. Morris, and A. Wadia. “Spike-type compressor stall inception, detection, and control.” Annual review of fluid mechanics 42 (2010): 275–300.

    Article  ADS  Google Scholar 

  27. Wu, Y., Q. Li, H. Zhang and W. Chu, “Numerical investigation into the mechanism of spike-type stall inception in an axial compressor rotor,” Proc IMechE, Part A: Journal of Power and Energy 226, no. 2, pp. 192–207, 2012.

    Article  Google Scholar 

  28. Khaleghi, H., M. Boroomand, A. M. Tousi, and J. A. Teixeira. “Stall inception in a transonic axial fan.” Proc IMechE, Part A: Journal of Power and Energy 222, no. 2 (2008): 199–208.

    Article  Google Scholar 

  29. Khaleghi, H., “Stall inception and control in a transonic fan, part A: Rotating stall inception,” Aerospace Science and Technology 41, pp. 250–258, 2015.

    Article  Google Scholar 

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Authors and Affiliations

  1. Aerospace Engineering Department, Amirkabir University of Technology, Tehran, Iran

    A. Naseri, M. Boroomand & S. Sammak

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  1. A. Naseri
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  2. M. Boroomand
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  3. S. Sammak
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Naseri, A., Boroomand, M. & Sammak, S. Numerical investigation of effect of inlet swirl and total-pressure distortion on performance and stability of an axial transonic compressor. J. Therm. Sci. 25, 501–510 (2016). https://doi.org/10.1007/s11630-016-0891-6

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  • DOI: https://doi.org/10.1007/s11630-016-0891-6

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