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Research Papers: Gas Turbines: Turbomachinery

The Effects of Tip Leakage Flow on the Performance of Multistage Compressors Used in Small Core Engine Applications

[+] Author and Article Information
Reid A. Berdanier

Mem. ASME
School of Mechanical Engineering,
Purdue University,
500 Allison Road,
West Lafayette, IN 47907
e-mail: rberdani@purdue.edu

Nicole L. Key

Associate Professor
Mem. ASME
School of Mechanical Engineering,
Purdue University,
500 Allison Road,
West Lafayette, IN 47907
e-mail: nkey@purdue.edu

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received August 4, 2015; final manuscript received August 31, 2015; published online November 11, 2015. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(5), 052605 (Nov 11, 2015) (10 pages) Paper No: GTP-15-1395; doi: 10.1115/1.4031625 History: Received August 04, 2015; Revised August 31, 2015

Large rotor tip clearances and the associated tip leakage flows are known to have a significant effect on overall compressor performance. However, detailed experimental data reflecting these effects for a multistage compressor are limited in the open literature. As design trends lead to increased overall compressor pressure ratio for thermal efficiency benefits and increased bypass ratios for propulsive benefits, the rear stages of the high-pressure compressor will become physically small. Because rotor tip clearances cannot scale exactly with blade size due to the margin needed for thermal growth considerations, relatively large tip clearances will be a reality for these rear stages. Experimental data have been collected from a three-stage axial compressor to assess performance with three-tip clearance heights representative of current and future small core machines. Trends of overall pressure rise, stall margin, and efficiency are evaluated using clearance derivatives, and the summarized data presented here begin to narrow the margin of tip clearance sensitivities outlined by previous studies in an effort to inform future compressor designs. Furthermore, interstage measurements show stage matching changes and highlight specific differences in the performance of rotor 1 and stator 2 compared to other blade rows in the machine.

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References

Storer, J. A. , and Cumpsty, N. A. , 1994, “ An Approximate Analysis and Prediction Method for Tip Clearance Loss in Axial Compressors,” ASME J. Turbomach., 116(4), pp. 648–656. [CrossRef]
Ruden, P. , 1944, “ Investigation of Single Stage Axial Fans,” Report No. NACA TM 1062.
Williams, A. D. , 1960, “ The Effect of Tip Clearance Flows on Performance of Axial Flow Compressors,” Engineer's thesis, Aeronautical Engineering Department, California Institute of Technology, Pasadena, CA.
Hutton, S. P. , 1956, “ Three-Dimensional Motion in Axial-Flow Impellers,” Proc. Inst. Mech. Eng., 170(1), pp. 863–873. [CrossRef]
Moore, R. D. , and Osborn, W. M. , 1977, “ Effects of Tip Clearance on Overall Performance of Transonic Fan Stage With and Without Casing Treatment,” Report No. NASA TM X-3479.
Inoue, M. , Kuroumaru, M. , and Fukuhara, M. , 1986, “ Behavior of Tip Leakage Flow Behind an Axial Compressor Rotor,” ASME J. Eng. Gas Turbines Power, 108(1), pp. 7–14. [CrossRef]
McDougall, N. M. , 1990, “ A Comparison Between the Design Point and Near-Stall Performance of an Axial Compressor,” ASME J. Turbomach., 112(1), pp. 109–115. [CrossRef]
Goto, A. , 1992, “ Three-Dimensional Flow and Mixing in an Axial Flow Compressor With Different Rotor Tip Clearances,” ASME J. Turbomach., 114(3), pp. 675–685. [CrossRef]
Wisler, D. C. , 1985, “ Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing,” ASME J. Eng. Gas Turbines Power, 107(2), pp. 354–363. [CrossRef]
Jefferson, J. L. , and Turner, R. C. , 1958, “ Some Shrouding and Tip Clearance Effects in Axial Flow Compressors,” Int. Shipbuild. Progress, 5, pp. 78–101.
Lindsey, W. H. , 1949, “ The Development of the Armstrong Siddeley Mamba Engine,” J. R. Aeronaut. Soc., 53, pp. 137–180.
Koch, C. C. , 1981, “ Stalling Pressure Rise Capability of Axial Flow Compressor Stages,” J. Eng. Power, 103(4), pp. 645–656. [CrossRef]
Freeman, C. , 1985, “ Effect of Tip Clearance Flow on Compressor Stability and Engine Performance,” Tip Clearance Effects in Axial Turbomachines (VKI Lecture Series 1985-05), C. H. Sieverding, ed., von Karman Institute for Fluid Dynamics, Rhode-St-Genèse, Belgium.
Tschirner, T. , Johann, E. , Müller, R. , and Vogeler, K. , 2006, “ Effects of 3D Aerofoil Tip Clearance Variation on a 4-Stage Low Speed Compressor,” ASME Paper No. GT2006-90902.
Spencer, E. A. , 1956, “ The Performance of an Axial-Flow Pump,” Proc. Inst. Mech. Eng., Part C, 170(1), pp. 874–908.
Wennerstrom, A. J. , 1984, “ Experimental Study of a High-Throughflow Transonic Axial Compressor Stage,” ASME J. Eng. Gas Turbines Power, 106(3), pp. 552–560. [CrossRef]
Lemmon, E. W. , Huber, M. L. , and McLinden, M. O. , 2013, NIST Standard Reference Database 23: Reference Fluid Thermodynamic and Transport Properties-refprop, Version 9.1, National Institute of Standards and Technology, Standard Reference Data Program, Gaithersburg, MD.
Fulayter, R. D. , 2004, “ An Experimental Investigation of Resonant Response of Mistuned Fan and Compressor Rotors Utilizing NSMS,” Ph.D. dissertation, School of Mechanical Engineering, Purdue University, West Lafayette, IN.
Wisler, D. C. , and Beacher, B. F. , 1989, “ Improved Compressor Performance Using Recessed Clearance (Trenches),” J. Propul., 5(4), pp. 469–475. [CrossRef]
Brossman, J. R. , 2012, “ An Investigation of Rotor Tip Leakage Flows in the Rear-Block of a Multistage Compressor,” Ph.D. dissertation, School of Mechanical Engineering, Purdue University, West Lafayette, IN.
Berdanier, R. A. , and Key, N. L. , 2015, “ Experimental Investigation of Factors Influencing Operating Rotor Tip Clearance in Multistage Compressors,” Int. J. Rotating Mach., 2015, p. 146272. [CrossRef]
Berdanier, R. A. , Smith, N. R. , Fabian, J. C. , and Key, N. L. , 2015, “ Humidity Effects on Experimental Compressor Performance—Corrected Conditions for Real Gases,” ASME J. Turbomach., 137(3), p. 031011. [CrossRef]
American Society of Mechanical Engineers, 2004, Flow Measurement, ASME, New York, Standard No. PTC 19.5, pp. 19–27. [PubMed] [PubMed]
Wisler, D. C. , 1998, “ Axial-Flow Compressor and Fan Aerodynamics,” Handbook of Fluid Dynamics, R. W. Johnson , ed., CRC Press, Boca Raton, FL.
Wennerstrom, A. J. , 1989, “ Low Aspect Ratio Axial Flow Compressors: Why and What It Means,” ASME J. Turbomach., 111(4), pp. 357–365. [CrossRef]
Lou, F. , Fabian, J. , and Key, N. L. , 2014, “ The Effect of Gas Models on Compressor Efficiency Including Uncertainty,” ASME J. Eng. Gas Turbines Power, 136(1), p. 012601. [CrossRef]
Sakulkaew, S. , Tan, C. S. , Donahoo, E. , Cornelius, C. , and Montgomery, M. , 2013, “ Compressor Efficiency Variation With Rotor Tip Gap From Vanishing to Large Clearance,” ASME J. Turbomach., 135(3), p. 031030. [CrossRef]
Smith, N. R. , and Key, N. L. , 2015, “ Flow Visualization for Investigating Stator Losses in a Multistage Axial Compressor,” Experiments Fluids, 56(5), p. 94. [CrossRef]

Figures

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Fig. 1

Schematic of compressor tip clearance casing geometry configurations

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Fig. 2

Compressor measurement plane locations

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Fig. 3

Compressor TPR map

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Fig. 4

Change of stall conditions with tip clearance height (100% Nc)

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Fig. 5

Flow range change with tip clearance height

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Fig. 6

Peak total-to-static pressure rise coefficient difference as a function of tip clearance height

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Fig. 7

Isentropic compressor efficiency at four corrected rotational speeds, Nc

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Fig. 8

Isentropic efficiency for specified 100% Nc speedline points as a function of tip clearance height

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Fig. 9

Radial stagnation pressure profiles at HL

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Fig. 10

Radial stagnation pressure profiles at NS

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Fig. 11

Detailed total pressure traverse measurements at stator 2 exit, axial measurement plane 6 (top), compared with qualitative flow visualization photographs of surface flows on stator 2 (bottom). Data collected at HL.

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Fig. 12

Stage total-to-static pressure rise characteristics at 100% corrected speed

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Fig. 13

Comparison of rotor and stage efficiency differences with tip clearance height at NL and HL

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