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Research Papers

Improving Purge Air Cooling Effectiveness by Engineered End-Wall Surface Structures—Part I: Duct Flow

[+] Author and Article Information
Xin Miao

Department of Mechanical Engineering
and Aeronautics,
City, University of London,
Northampton Square,
London EC1V 0HB, UK
e-mail: Xin.Miao@city.ac.uk

Qiang Zhang

Department of Mechanical Engineering
and Aeronautics,
City, University of London,
Northampton Square,
London EC1V 0HB, UK
e-mail: Qiang.Zhang.1@city.ac.uk

Chris Atkin

Department of Mechanical Engineering
and Aeronautics,
City, University of London,
Northampton Square,
London EC1V 0HB, UK
e-mail: Chris.Atkin.1@city.ac.uk

Zhengzhong Sun

Department of Mechanical
Engineering and Aeronautics,
City, University London,
Northampton Square,
London, EC1V 0HB, UK
e-mail: Zhengzhong.Sun@city.ac.uk

Yansheng Li

Siemens Industrial Turbomachinery Limited,
Lincoln LN5 7FD, UK
e-mail: yansheng.li@siemens.com

1Correponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received January 31, 2018; final manuscript received July 11, 2018; published online August 20, 2018. Assoc. Editor: David G. Bogard.

J. Turbomach 140(9), 091001 (Aug 20, 2018) (12 pages) Paper No: TURBO-18-1013; doi: 10.1115/1.4040853 History: Received January 31, 2018; Revised July 11, 2018

Motivated by the recent advances in additive manufacturing, this study investigated a new turbine end-wall aerothermal management method by engineered surface structures. The feasibility of enhancing purge air cooling effectiveness through a series of small-scale ribs added onto the turbine end-wall was explored experimentally and numerically in this two-part paper. Part I presents the fundamental working mechanism and cooling performance in a 90 deg turning duct (part I), and part II of this paper validates the concept in a more realistic turbine cascade case. In part I, the turning duct is employed as a simplified model for the turbine passage without introducing the horseshoe vortex. End-wall heat transfer and temperature were measured by the infrared thermography. Computational fluid dynamics (CFD) simulation was also performed using ANSYS fluent to compliment the experimental findings. With the added end-wall rib structures, purge air flow was observed to be more attached to the end-wall and cover a larger wall surface area. Both experimental and numerical results reveal a consistent trend on improved film cooling effectiveness. The practical design optimization strategy is also discussed in this paper.

Copyright © 2018 by ASME
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References

Han, J. C. , 2004, “Recent Studies in Turbine Blade Cooling,” Int. J. Rotating Mach., 10(6), pp. 443–457.
Bunker, R. S. , Metzger, D. E. , and Wittig, S. , 1992, “Local Heat Transfer in Turbine Disk Cavities—Part I: Rotor and Stator Cooling With Hub Injection of Coolant,” ASME J. Turbomach., 114(1), p. 211. [CrossRef]
Bunker, R. S. , Metzger, D. E. , and Wittig, S. , 1992, “Local Heat Transfer in Turbine Disk Cavities—Part II: Rotor Cooling With Radial Location Injection of Coolant,” ASME J. Turbomach., 114(1), pp. 221–228. [CrossRef]
Wilson, M. , Arnold, P. D. , Lewis, T. W. , Mirzaee, I. , Rees, D. A. S. , and Owen, J. M. , 1997, “Instability of Flow and Heat Transfer in a Rotating Cavity With a Stationary Outer Casing,” Eurotherm 55 (Heat Transfer in Single Phase Flow), Santorini, Greece, Sept. 1.
McLean, C. , Camci, G. , and Glezer, B. , 2001, “Mainstream Aerodynamic Effects Due to Wheelspace Coolant Injection in a High-Pressure Turbine Stage,” ASME J. Turbomach., 123(4), pp. 687–703. [CrossRef]
McLean, C. , Camci, C. , and Glezer, B. , 2001, “Mainstream Aerodynamic Effects Due to Wheelspace Coolant Injection in a High-Pressure Turbine Stage—Part II: Aerodynamic Measurements in the Rotational Frame,” ASME J. Turbomach., 123(4), pp. 697–703. [CrossRef]
Girgis, S. , Vlasic, E. , Lavole, J. P. , and Moustapha, S. H. , 2002, “The Effect of Secondary Air Injection on the Performance of a Transonic Turbine Stage,” ASME Paper No. GT2002-30340.
Reid, K. , Denton, J. , Pullan, G. , Curtis, E. , and Longley, J. , 2006, “The Effect of Stator-Rotor Hub Sealing Flow on the Mainstream Aerodynamics of a Turbine,” ASME Paper No. GT2006-90838.
Roy, R. P. , Squires, K. D. , Gerendas, M. , Song, S. , Howe, W. J. , and Ansari, A. , 2000, “Flow and Heat Transfer at the Hub Endwall of Inlet Vane Passages—Experiments and Simulations,” ASME Paper No. 2000-GT-0198.
Burd, S. W. , Satterness, C. J. , and Simon, T. W. , 2000, “Effects of Slot Bleed Injection Over a Contoured End Wall on Nozzle Guide Vane Cooling Performance—Part II: Thermal Measurements,” ASME Paper No. 2000-GT-0200.
Oke, R. , Simon, T. , Shih, T. , Zhu, B. , Lin, Y. L. , and Chyu, M. , 2001, “Measurements Over a Film-Cooled Contoured Endwall With Various Coolant Injection Rates,” ASME Paper No. 2001-GT-0140.
Dénos, R. , and Paniagua, G. , 2002, “Influence of the Hub Endwall Cavity Flow on the Time-Averaged and Time-Resolved Aero-Thermodynamics of Axial HP Turbine Stage,” ASME Paper No. GT2002-30185.
Wright, L. M. , Gao, Z. , Yang, H. , and Han, J. C. , 2008, “Film Cooling Effectiveness Distribution on a Gas Turbine Blade Platform With Inclined Slot Leakage and Discrete Film Hole Flows,” ASME J. Heat Transfer, 130(7), p. 071702. [CrossRef]
Wright, L. M. , Blake, S. A. , and Han, J. C. , 2006, “Film Cooling Effectiveness Distributions on a Turbine Blade Cascade Platform With Stator-Rotor Purge and Discrete Film Hole Flows,” ASME Paper No. IMECE2006-15092.
Popovic, I. , and Hodson, H. P. , 2010, “Aerothermal Impact of the Interaction Between Hub Leakage and Mainstream Flows in Highly-Loaded HP Turbine Blades,” ASME Paper No. GT2010-22311.
Miao, X. , Zhang, Q. , Atkin, C. , and Sun, Z. , 2016, “End-Wall Secondary Flow Control Using Engineered Residual Surface Structure,” ASME Paper No. GT2016-57347.
Miao, X. , Zhang, Q. , Wang, L. , Jiang, H. , and Qi, H. , 2015, “Application of Riblets on Turbine Blade Endwall Secondary Flow Control,” J. Propul. Power, 31(6), pp. 1578–1585. [CrossRef]
Camci, C. , and Rizzo, D. H. , 2002, “Secondary Flow and Forced Convection Heat Transfer Near Endwall Boundary Layer Fences in a 90 Turning Duct,” Int. J. Heat Mass Transfer, 45(4), pp. 831–843. [CrossRef]
Schulz, A. , 2000, “Infrared Thermography as Applied to Film Cooling of Gas Turbine Components,” Meas. Sci. Technol., 11(7), p. 948. [CrossRef]
O'Dowd, D. O. , Zhang, Q. , He, L. , Ligrani, P. M. , and Friedrichs, S. , 2011, “Comparison of Heat Transfer Measurement Techniques on a Transonic Turbine Blade Tip,” ASME J. Turbomach., 133(2), p. 021028. [CrossRef]
Zhang, Q. , He, L. , Wheeler, A. P. S. , Ligrani, P. M. , and Cheong, B. C. Y. , 2011, “Overtip Shock Wave Structure and Its Impact on Turbine Blade Tip Heat Transfer,” ASME J. Turbomach., 133(4), p. 041001. [CrossRef]
Oldfield, M. L. , 2008, “Impulse Response Processing of Transient Heat Transfer Gauge Signals,” ASME J. Turbomach., 130(2), p. 021023. [CrossRef]
Zhang, Q. , O'Dowd, D. O. , He, L. , Oldfield, M. L. G. , and Ligrani, P. M. , 2011, “Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps—Part I: Tip Heat Transfer,” ASME J. Turbomach., 133(4), p. 041027. [CrossRef]
Zhang, Q. , He, L. , Cheong, B. C. Y. , and Tibbott, I. , 2013, “Aerothermal Performance of a Cooled Winglet at Engine Representative Mach and Reynolds Numbers,” ASME J. Turbomach., 135(1), p. 011041.
Ma, H. , Zhang, Q. , He, L. , Wang, Z. , and Wang, L. , 2017, “Cooling Injection Effect on a Transonic Squealer Tip—Part I: Experimental Heat Transfer Results and CFD Validation,” ASME J. Eng. Gas Turbines Power, 139(5), p. 052506. [CrossRef]
Moffat, R. J. , 1988, “Describing the Uncertainties in Experimental Results,” Exp. Therm. Fluid Sci., 1(1), pp. 3–17. [CrossRef]
Devore, J. L. , 2011, Probability and Statistics for Engineering and the Sciences, Cengage Learning, Boston, MA.
Sen, B. , Schmidt, D. L. , and Bogard, D. G. , 1996, “Film Cooling With Compound Angle Holes: Heat Transfer,” ASME J. Turbomach., 118(4), pp. 807–813.
Knost, D. , and Thole, K. , 2005, “Adiabatic Effectiveness Measurements of Endwall Film-Cooling for a First-Stage Vane,” ASME J. Turbomach., 127(2), pp. 297–305. [CrossRef]
Nicklas, M. , 2001, “Film-Cooled Turbine Endwall in a Transonic Flow Field—Part II: Heat Transfer and Film-Cooling Effectiveness,” ASME J. Turbomach., 123(4), pp. 720–729. [CrossRef]
Wright, L. M. , Blake, S. , and Han, J. C. , 2007, “Effectiveness Distributions on Turbine Blade Cascade Platforms Through Simulated Stator-Rotor Seals,” J. Thermophys. Heat Transfer, 21(4), pp. 754–762. [CrossRef]

Figures

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Fig. 1

A schematic of the experiment facility employed in the present study

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Fig. 2

Inlet end-wall turbulent boundary layer velocity profile

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Fig. 3

IR camera calibration curve

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Fig. 4

(a) Time histories of the cold purge air, end-wall and inlet temperatures, and (b) variations of wall heat flux and surface temperature for one selected location, during one typical transient measurement

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Fig. 5

(a) R2 distribution for linear regression, and (b) relative uncertainty (%U) in Tad distribution

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Fig. 6

The computational domain and grids employed in the present study

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Fig. 7

Spanwise-averaged total pressure loss coefficient Cp

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Fig. 8

Total pressure loss coefficient Cp distributions for cases with and without single fence obtained at 90 deg plane of the duct

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Fig. 9

An iso-temperature surface with θ=0.6

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Fig. 10

Nondimensional temperature θ distribution at three angular cross sections

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Fig. 11

Streamwise vorticity distributions at three angular cross sections

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Fig. 12

Distributions of Aerodynamic loss coefficient at the exit plane

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Fig. 13

Film cooling effectiveness (experimental data)

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Fig. 14

Film cooling effectiveness (CFD results)

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Fig. 15

Laterally film cooling effectiveness η¯ along the duct passage for both experimental and CFD results

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Fig. 16

Film cooling effectiveness variation along the radius direction

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Fig. 17

Heat transfer coefficient (experimental data)

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Fig. 18

Heat transfer coefficient (CFD)

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Fig. 19

Distributions of NHFR (experimental data)

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Fig. 20

Distributions of NHFR (CFD results)

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Fig. 21

Nondimensional temperature θ distribution near the purge air entry region for ribbed surface

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Fig. 22

Distributions of film cooling effectiveness

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Fig. 23

Cooling fluid streamlines near the end-wall ribs

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Fig. 24

Distributions of net heat load reduction along the duct passage

Tables

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