International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Rotor Blade Sweep Effect on the Performance of a Small Axial Supersonic Impulse Turbine

  • Jeong, Sooin (Industrial Liaison Innovation Center, Pusan National University) ;
  • Choi, Byoungik (Rolls-Royce University Technology Center in Thermal Management, Pusan National University) ;
  • Kim, Kuisoon (Department of Aerospace Engineering, Pusan National University)
  • Received : 2015.09.15
  • Accepted : 2015.12.10
  • Published : 2015.12.30
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Abstract

In this paper, a computational study was conducted in order to investigate the rotor blade sweep effect on the aerodynamics of a small axial supersonic impulse turbine stage. For this purpose, three-dimensional unsteady RANS simulations have been performed with three different rotor blade sweep angles ($-15^{\circ}$, $0^{\circ}$, $+15^{\circ}$) and the results were compared with each other. Both NTG (No tip gap) and WTG (With tip gap) models were applied to examine the effect on tip leakage flow. As a result of the simulation, the positive sweep model ($+15^{\circ}$) showed better performance in relative flow angle, Mach number distribution, entropy rise, and tip leakage mass flow rate compared with no sweep model. With the blade static pressure distribution result, the positive sweep model showed that hub and tip loading was increased and midspan loading was reduced compared with no sweep model while the negative sweep model ($-15^{\circ}$) showed the opposite result. The positive sweep model also showed a good aerodynamic performance around the hub region compared with other models. Overall, the positive sweep angle enhanced the turbine efficiency.

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References

  1. Lewis, R. and Hill, J., "The Influence of Sweep and Dihedral in Turbomachinery Blade Rows", Journal of mechanical Engineering Science, Vol. 13, No. 4, 1971, pp.266-285. DOI:10.1243/JMES_JOUR_1971_013_043_02
  2. Hill, J. and Lewis, R., "Experimental Investigations of Strongly Swept Turbine Cascades with Low Speed Flow", Journal of mechanical Engineering Science, Vol. 16, No. 1, 1974, pp. 32-40. DOI:10.1243/JMES_JOUR_1974_016_007_02
  3. Denton, J. and Xu, L., "The Exploitation of Threedimensional Flow in Turbomachinery Design", Proceedings of the Institution of Mechanical Engineers, Part C, Journal of Mechanical Engineering Science, Vol. 213, No. 2, 1999, pp. 125-137. DOI:10.1243/0954406991522220
  4. Wadia, A., Szucs, P. and Crall, D., "Inner Workings of Aerodynamic Sweep", ASME Journal of Turbomachinery, Vol. 120, 1998, pp. 671-682. DOI:10.1115/1.2841776
  5. Gümmer, V., Wenger, U. and Kau, H., "Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Compressors", ASME Journal of Turbomachinery, Vol. 123, 2001, pp. 40-48. DOI:10.1115/1.1330268
  6. Denton, J., "The Effects of Lean and Sweep on Transonic Fan Performance: A Computational Study", TASK QUARTERLY, Vol. 6, No. 1, 2002, pp. 7-23.
  7. Pullan, G. and Harvey, N. W., "Influence of Sweep on Axial Flow Turbine Aerodynamics at Midspan", ASME Journal of Turbomachinery, Vol. 129, No. 3, 2007, pp. 591-598. DOI:10.1115/1.2472397
  8. Pullan, G. and Harvey, N. W., "Influence of Sweep on Axial Flow Turbine Aerodynamics in the Endwall Region", ASME Journal of Turbomachinery, Vol. 130, No. 4, 2008, pp. 041011-1-041011-10. DOI:10.1115/1.2812337
  9. Yoon, S., Denton, J., Curtis, E., Longley, J. and Pullan, G., "Improving Intermediate Pressure Turbine Performance by Using a Nonorthogonal Stator", ASME Journal of Turbomachinery, Vol. 136, No. 1, 2014, pp. 021012-1-021012-8. DOI:10.1115/1.4023941
  10. Hah, C. and Shin, H., "Study of Near-Stall Flow Behavior in a Modern Transonic Fan with Compound Sweep", ASME Journal of Fluid Engineering, Vol. 134, 2012, pp. 071101-1-071101-7 DOI:10.1115/1.4006878
  11. Menter, F. R., "Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications", AIAA Journal, Vol. 32, No. 8, 1994, pp. 1598-1605. DOI:10.2514/3.12149
  12. Moffitt, T. P., "Design and Experimental Investigation of a Single-Stage Turbine with a Rotor Entering Relative Mach Number of 2", NACA RM E58F20a, 1958.
  13. Moffitt, T. P. and Klag, F. W., Jr., "Experimental Investigation of Partial- and Full-Admission Characteristics of a Two-Stage Velocity Compounded ", NASA TM X-410, 1960