Effects of Winglet Geometry on the Aerodynamic Performance of Tip Leakage Flow in a Turbine Cascade

[+] Author and Article Information
Chao Zhou

State Key Laboratory for Turbulence and Complex Systems, College of Engineering, Peking University, Beijing 100871, China

Howard Hodson

Whittle Laboratory, Department of Engineering, University of Cambridge, Cambridge CB2 0DY, UK

Mark Stokes

Rolls-Royce plc, Derby DE24 8BJ, UK

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received June 27, 2012; final manuscript received August 14, 2012; published online June 26, 2013. Editor: David Wisler.

J. Turbomach 135(5), 051009 (Jun 26, 2013) (10 pages) Paper No: TURBO-12-1082; doi: 10.1115/1.4007831 History: Received June 27, 2012; Revised August 14, 2012

Experimental and numerical methods were used to investigate the aerodynamic performance of a winglet tip in a linear cascade. A flat tip and a cavity tip were studied as baseline cases. The flow patterns over the three tips were studied. For the cavity tip and the winglet tip, vortices appear in the cavity and the gutter. These vortices reduce the discharge coefficient of the tip leakage flow. The purpose of using a winglet tip is to reduce the driving pressure difference. The pressure side winglet of the winglet geometry studied in this paper has little effect in reducing the driving pressure difference. It is found that the suction side winglet reduces the driving pressure difference of the tip leakage flow near the leading edge, but increases the driving pressure difference from midchord to the trailing edge. This is also used to explain the findings and discrepancies in other studies. Compared with the flat tip, the cavity tip and the winglet tip achieve a reduction of loss. The effects of the rounding of the pressure side edge of the tips were studied to simulate the effects of deterioration. As the size of the pressure side edge radius increases, the tip leakage mass flow rate and the loss increase. The improvement of the aerodynamic performance by using a winglet remains similar when comparing with a flat tip or a cavity tip with the same pressure side radius.

Copyright © 2013 by ASME
Your Session has timed out. Please sign back in to continue.


Dey'D., 2001, “Aerodynamic Tip Desensitization in Axial Flow Turbines,” Ph.D. thesis, Pennsylvania State University, University Park, PA.
Zhou, C., and Hodson, H., 2011, “The Tip Leakage Flow of an Unshrouded High Pressure Turbine Blade With Tip Cooling,” ASME J. Turbomach., 133(4), p. 041028. [CrossRef]
Zhou, C., Hodson, H., Tibbott, I., and Stokes, M., 2011, “The Aero-Thermal Performance of a Cooled Winglet Tip in a High Pressure Turbine Cascade,” ASME Paper No. GT2011-46369. [CrossRef]
Booth, T. C., DodgeP. R., and HepworthH. K., 1981, “Rotor-Tip Leakage Part I—Basic Methodology,” ASME Paper No. 81-GT-71.
Heyes, F. J. G., Hodson, H. P., and DaileyG. M., 1992, “The Effect of Blade Tip Geometry on the Tip Leakage Flow in Axial Turbine,” ASME J. Turbomach., 114, pp. 643–651. [CrossRef]
Dishart, P. T., and Moore, J., 1990, “Tip Leakage Losses in a Linear Turbine Cascade,” ASME J. Turbomach., 112, pp. 599–608. [CrossRef]
Ameri, A. A., 2001, “Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped With a Mean-Camberline Strip,” ASME J. Turbomach., 123, pp. 704–708. [CrossRef]
Harvey, N. W., 2004, “Turbine Blade Tip Design and Tip Clearance Treatment,” VKI Lecture Series, January 19–23.
Ameri, A. A., Steinthorsson, E., and Rigby, D. L., 1998, “Effect of Squealer Tip on Rotor Heat Transfer and Efficiency,” ASME J. Turbomach., 120, pp. 753–759. [CrossRef]
Camci, C., Dey, D., and Kavurmacioglu, L., 2005, “Aerodynamics of Tip Leakage Flow Near Partial Squealer Rims in an Axial Flow Turbine Stage,” ASME J. Turbomach., 127, pp. 14–24. [CrossRef]
KeyN., and Arts, T., 2006, “Comparison of Turbine Tip Leakage Flow for Flat Tip and Squealer Tip Geometries at High-Speed Conditions,” ASME J. Turbomach., 128, pp. 213–220. [CrossRef]
Heyes, F., private communication.
Schabowski, Z., and Hodson, H., 2007, “The Reduction of Over Tip Leakage Loss in Unshrouded Axial Turbines Using Winglet and Squealers,” ASME Paper No. GT2007-27623. [CrossRef]
Liu, H. C., Booth, T. C., and Tall, W. A., 1979, “An Application of 3-D Viscous Flow Analysis to the Design of a Low-Aspect-Ratio Turbine,” ASME Paper No. 79-GT-53.
Yaras, M. I., and Sjolander, S. A., “Measurements of the Effects of Winglets on Tip-Leakage Losses in a Linear Turbine Cascade,” Paper No. ISABE 91-7011.
Harvey, N., Newman, D., and Haselbach, F., 2006, “An Investigation Into a Novel Turbine Rotor Winglet: Part I—Design and Model Rig Test Results,” ASME Paper No. GT2006-90456. [CrossRef]
Schabowski, Z., Hodson, H., Giacche, D., and Power, B., 2010, “Aeromechanical Optimisation of a Winglet-Squealer Tip for an Axial Turbine,” ASME Paper No. GT2010-23542. [CrossRef]
Dey, D., and Camci, C., 2001, “Aerodynamic Tip Desensitization of an Axial Turbine Rotor Using Tip Platform Extensions,” ASME Paper No. 2001-GT-0484.
Zhou, C., Hodson, H., Tibbott, I., and Stokes, M., 2011, “Effects of Endwall Motion on the Aero-Thermal Performance of a Winglet Tip in a HP Turbine,” ASME Paper No. GT2011-46373. [CrossRef]
O'Dowd, D., Zhang, Q., and He, L., 2013, “Aerothermal Performance of a Cooled Winglet at Engine Representative Mach and Reynolds Number,” ASME J. Turbomach., 135(1), p. 011041. [CrossRef]
MatsunumaT., 2006, “Effects of Reynolds Number and Freestream Turbulence on Turbine Tip Clearance Flow,” ASME J. Turbomach., 128, pp. 166–177. [CrossRef]
Holman, J. P., and Gajda, W. J. Jr., 1984, Experimental Methods for Engineers, 4th ed., McGraw-Hill, New York.
Zhou, C., and Hodson, H., 2012, “Squealer Geometry Effects on Aerothermal Performance of Tip-Leakage Flow of Cavity Tips,” J. Propulsion & Power, 28(3), pp. 556–567. [CrossRef]
Zhou, C., and Hodson, H., 2009, “Numerical Investigation of Thermal Performance of Unshrouded HP Turbine Blade Tips,” Int. J. Turbo Jet Engines, 26, pp. 277–284. [CrossRef]
Moore, J., and Tilton, J. S., 1988, “Tip Leakage Flow in a Linear Turbine Cascade,” ASME J. Turbomach., 110, pp. 18–26. [CrossRef]
RainsD. A., 1954, “Tip Clearance Flows in Axial Flow Compressors and Pumps,” Report No. 5, Hydrodynamics and Mechanical Engineering Laboratories, California Institute of Technology, Pasadena, CA.
Tallman, J., and LakshminarayanaB., 2001, “Numerical Simulation of Tip Leakage Flows in Axial Flow Turbines, With Emphasis on Flow Physics: Part II—Effect of Outer Casing Relative Motion,” ASME J. Turbomach., 123, pp. 323–333. [CrossRef]


Grahic Jump Location
Fig. 1

Winglet tips tested by Heyes

Grahic Jump Location
Fig. 3

Geometry of cavity tip and winglet tip

Grahic Jump Location
Fig. 5

Midspan Cp distribution, CFD

Grahic Jump Location
Fig. 4

Mesh of winglet tip, τ = 1.9%C

Grahic Jump Location
Fig. 7

Cp distribution on endwall, winglet tip, τ = 1.9%C

Grahic Jump Location
Fig. 6

Distributions of velocity at cut plane “A” in Fig. 7, V/V2, τ = 1.9%C, CFD

Grahic Jump Location
Fig. 9

Static pressure coefficient on suction side edge, CFD

Grahic Jump Location
Fig. 8

Endwall Cp distribution at line “B,” winglet tip, τ = 1.9%C

Grahic Jump Location
Fig. 14

Suction side winglet tips studied by Schabowski et al. [17]

Grahic Jump Location
Fig. 13

Mixed-out tip leakage loss, τ = 1.9%C

Grahic Jump Location
Fig. 12

Stagnation pressure coefficient at 45%Cx downstream trailing edge, τ = 1.9%C

Grahic Jump Location
Fig. 10

Tip leakage mass flow rate per unit area that exits gap, CFD, τ = 1.9%C

Grahic Jump Location
Fig. 11

Velocity distribution in middle of tip gap, winglet tip, V/V2, τ = 1.9%C, CFD

Grahic Jump Location
Fig. 15

Suction side winglet studied in Camic [18]

Grahic Jump Location
Fig. 16

Effects of size of tip gap, winglet tip, exp

Grahic Jump Location
Fig. 17

Mixed-out tip leakage loss versus gap, exp

Grahic Jump Location
Fig. 18

Effects of pressure side radius on loss, exp




Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In