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Research Papers

A Combined Experimental and Numerical Study of the Turbine Blade Tip Film Cooling Effectiveness Under Rotation Condition

[+] Author and Article Information
Mohsen Rezasoltani, Kun Lu

Turbomachinery Performance and
Flow Research Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123

Meinhard T. Schobeiri

Turbomachinery Performance and
Flow Research Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: tschobeir@tamu.edu

Je-Chin Han

Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 21, 2014; final manuscript received September 8, 2014; published online November 26, 2014. Editor: Ronald Bunker.

J. Turbomach 137(5), 051009 (May 01, 2015) (12 pages) Paper No: TURBO-14-1213; doi: 10.1115/1.4028745 History: Received August 21, 2014; Revised September 08, 2014; Online November 26, 2014

Detailed numerical and experimental investigations of film cooling effectiveness were conducted on the blade tips of the first rotor row pertaining to a three-stage research turbine. Four different blade tip ejection configurations were utilized to determine the impact of the hole arrangements on the film cooling effectiveness. Plane tip with tip hole cooling, squealer tip with tip hole cooling, plane tip with pressure side (PS) edge compound angle hole cooling, and squealer tip with PS-edge compound angle hole cooling. To avoid rotor imbalance, every pair is installed radially. Film cooling effectiveness measurements were performed for three blowing ratios (M) of 0.75, 1.25, and 1.75. Film cooling data was also obtained for three rotational speeds; 3000 rpm (reference condition), 2550 rpm and 2000 rpm. Film cooling measurements were performed using pressure sensitive paint (PSP) technique. In a parallel effort, extensive numerical investigations of the above configurations were performed to give a better view of flow behavior using a commercially available code. The experimental investigations were performed in the three-stage multipurpose turbine research facility at the Turbomachinery Performance and Flow Research Laboratory (TPFL), Texas A&M University.

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References

Khajavi, M. R., and Shariat, M. H., 2004, “Failure of First Stage Gas Turbine Blades,” Eng. Failure Anal., 11(4), pp. 589–597. [CrossRef]
Han, J. C., Dutta, S., and Ekkad, S. V., 2000, Gas Turbine Heat Transfer and Cooling Technology, Taylor & Francis, New York.
Metzger, D. E., Bunker, R. S., and Chyu, M. K., 1989, “Cavity Heat Transfer on a Transverse Grooved Wall in a Narrow Flow Channel,” ASME J. Heat Transfer, 111(1), pp. 73–79. [CrossRef]
Kim, Y. W., and Metzger, D. E., 1995, “Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models,” ASME J. Turbomach., 117(1), pp. 12–21. [CrossRef]
Kim, Y. W., Downs, J. P., and Soechting, F. O., 1995, “A Summary of the Cooled Turbine Blade Tip Heat Transfer and Film Effectiveness Investigations Performed by Dr. D. E. Metzger,” ASME J. Turbomach., 117(1), pp. 1–11. [CrossRef]
Bunker, R. S., 2001, “A Review of Turbine Blade Tip Heat Transfer, Heat Transfer in Gas Turbine Systems,” Ann. N. Y. Acad. Sci., 934, pp. 64–79. [CrossRef] [PubMed]
Azad, G. S., Han, J. C., and Teng, S., 2000, “Heat Transfer and Pressure Distributions on a Gas Turbine Blade Tip,” ASME J. Turbomach., 122(4), pp. 717–724. [CrossRef]
Azad, G. S., Han, J. C., and Boyle, R. J., 2000, “Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade,” ASME J. Turbomach., 122(4), pp. 725–732. [CrossRef]
Bunker, R. S., Ameri, A. A., and Bailey, J. C., 2000, “Heat Transfer and Flow on the First-Stage Blade Tip of a Power Generation Gas Turbine: Part 1—Experimental Results,” ASME J. Turbomach., 122(2), pp. 263–271. [CrossRef]
Ameri, A. A., and Bunker, R. S., 2000, “Heat Transfer and Flow on the First-Stage Blade Tip of a Power Generation Gas Turbine: Part 2—Simulation Results,” ASME J. Turbomach., 122(2), pp. 272–277. [CrossRef]
Kwak, J. S., and Han, J. C., 2003, “Heat Transfer Coefficient and Film-Cooling Effectiveness on a Gas Turbine Blade Tip,” ASME J. Heat Transfer, 125(3), pp. 494–502. [CrossRef]
Kwak, J. S., and Han, J. C., 2003, “Heat Transfer Coefficient and Film-Cooling Effectiveness on the Squealer Tip of a Gas Turbine Blade,” ASME J. Turbomach., 125(4), pp. 648–657. [CrossRef]
Christophel, J. R., Thole, K. A., and Cunha, F. J., 2004, “Cooling the Tip of a Turbine Blade Using Pressure Side Holes—Part 1: Adiabatic Effectiveness Measurements,” ASME Paper No. GT2004-53251. [CrossRef]
Gao, Z., Narzary, D., Mhetras, S., and Han, J. C., 2009, “Effect of Inlet Flow Angle on Gas Turbine Blade Tip Film Cooling,” ASME J. Turbomach., 131(3), p. 031005. [CrossRef]
Park, J. S., Lee, D. H., Rhee, D. H., Cho, H. H., and Kang, S. H., 2010, “Heat Transfer and Effectiveness on the Film Cooled Tip and Inner Surface of a Turbine Blade,” ASME Paper No. GT2010-23203. [CrossRef]
Dring, R., Blair, M., and Joslyn, H., 1980, “An Experimental Investigation of Film Cooling on a Turbine Rotor Blade,” ASME J. Eng. Power, 102(1), pp. 81–87. [CrossRef]
Takeishi, K., Aoki, S., Sato, T., and Tsukagoshi, K., 1992, “Film Cooling on a Gas Turbine Rotor Blade,” ASME J. Turbomach., 114(4), pp. 828–834. [CrossRef]
Abhari, R., and Epstein, A., 1994, “Experimental Study of Film Cooling in a Rotating Transonic Turbine,” ASME J. Turbomach., 116(1), pp. 63–70. [CrossRef]
Acharya, S., and Moreaux, L., 2012, “Numerical Study of the Flow Past a Turbine Blade Tip: Effect of Relative Motion Between Blade and Shroud,” ASME Paper No. GT2012-69192. [CrossRef]
Yang, D., Yu, X., and Feng, Z., 2008, “Investigation of Leakage Flow and Heat Transfer in a Gas Turbine Blade Tip With Emphasis on the Effect of Rotation,” ASME Paper No. GT2008-51215. [CrossRef]
Lu, K., Schobeiri, M. T., and Han, J. C., 2013, “Numerical Simulation of Film Cooling on Rotating Blade Tips Within a High-Pressure Turbine,” ASME Paper No. GT2013-94806. [CrossRef]
Molter, S. M., Dunn, M. G., Haldeman, C. W., Bergholz, R. F., and Vitt, P., 2006, “Heat-Flux Measurements and Predictions for the Blade Tip Region of a High-Pressure Turbine,” ASME Paper No. GT2006-90048. [CrossRef]
Haldeman, C. W., Mathison, R. M., Dunn, M. G., Southworth, S., Harral, J. W., and Heltland, G., 2008, “Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part I: Experimental Approach,” ASME J. Turbomach., 130(2), p. 021015. [CrossRef]
Haldeman, C. W., Mathison, R. M., Dunn, M. G., Southworth, S., Harral, J. W., and Heltland, G., 2008, “Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part II: Experimental Results,” ASME J. Turbomach., 130(2), p. 021016. [CrossRef]
Ahn, J. Y., Schobeiri, M. T., Han, J. C., and Moon, H. K., 2007, “Effect of Rotation on Leading Edge Region Film Cooling of a Gas Turbine Blade With Three Rows of Film Cooling Holes,” Int. J. Heat Mass Transfer, 50(1–2), pp. 15–25. [CrossRef]
Ahn, J. Y., Schobeiri, M. T., Han, J. C., and Moon, H. K., 2006, “Film Cooling Effectiveness on the Leading Edge Region of a Rotating Turbine Blade With Two Rows of Film Cooling Holes Using Pressure Sensitive Paint,” ASME J. Heat Transfer, 128(9), pp. 879–888. [CrossRef]
Rezasoltani, M., Schobeiri, M. T., and Han, J. C., 2014, “Experimental Investigation of the Effect of Purge Flow on Film Cooling Effectiveness on a Rotating Turbine With Non-Axisymmetric Endwall Contouring,” ASME J. Turbomach.136(9), p. 091009. [CrossRef]
Schobeiri, M. T., Gilarranz, J., and Johansen, E., 1999, “Final Report on: Efficiency, Performance, and Interstage Flow Field Measurement of Siemens-Westinghouse HP-Turbine Blade Series 9600 and 5600,” TPFL-Westinghouse Report 1997-1.
Schobeiri, M. T., Suryanarayanan, A., Jermann, C., and Neuenschwander, T., 2004, “A Comparative Aerodynamic and Performance Study of a Three-Stage High Pressure Turbine With 3D Bowed Blades and Cylindrical Blades,” ASME Paper No. GT2004-53650. [CrossRef]
Suryanarayanan, A., Mhetras, S. P., Schobeiri, M. T., and Han, J. C., 2009, “Film-Cooling Effectiveness on a Rotating Blade Platform,” ASME J. Turbomach., 131(1), p. 011014. [CrossRef]
Han, J. C., and Rallabandi, A. P., 2010, “Turbine Blade Film Cooling Using PSP Technique,” Front. Heat Mass Transfer, 1(1), p. 013001. [CrossRef]
McLachlan, B., and Bell, J., 1995, “Pressure-Sensitive Paint in Aerodynamic Testing,” Exp. Therm. Fluid Sci., 10(4), pp. 470–485. [CrossRef]
Wright, L. M., Gao, Z., Varvel, T. A., and Han, J. C., 2005, “Assessment of Steady State PSP, TSP and IR Measurement Techniques for Flat Plate Film Cooling,” ASME Paper No. HT2005-72363. [CrossRef]
Rallabandi, A. P., Grizzle, J., and Han, J. C., 2011, “Effect of Upstream Step on Flat Plate Film Cooling Effectiveness Using PSP,” ASME J. Turbomach., 133(4), p. 041024. [CrossRef]
Coleman, H. W., and Steele, W. G., 1989, Experimentation and Uncertainty Analysis for Engineers, Wiley, New York.
Holman, J. P., 2000, Experimental Methods for Engineers, McGraw-Hill, New York.
Abdelfattah, S. A., and Schobeiri, M. T., 2010, “Experimental and Numerical Investigations of Aerodynamic Behavior of a Three-Stage HP-Turbine at Different Operating Conditions,” ASME Paper No. GT2010-23564. [CrossRef]
Ahn, J., Mhetras, S., and Han, J. C., 2005, “Film-Cooling Effectiveness on a Gas Turbine Blade Tip Using Pressure Sensitive Paint,” ASME J. Heat Transfer, 127(5), pp. 521–530. [CrossRef]

Figures

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Fig. 1

Turbine components with two independent cooling loops

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Fig. 2

Four different rotor blade tip configurations: plane tip with tip hole cooling (top-left), plane tip with PS-edge compound angle hole cooling (top-right), squealer tip with tip hole cooling (bottom-left) and squealer tip with PS-edge compound angle hole cooling (bottom-right)

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Fig. 3

Schematic of the blade tip film cooling system

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Fig. 4

Optical setup for PSP data acquisition

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Fig. 5

Computational domain and boundary conditions for mainstream

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Fig. 6

Detailed grid distribution of different configurations

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Fig. 7

Film cooling effectiveness measured for the blade tip at 3000 rpm for different blowing ratio. (a) Plane tip with tip hole cooling, (b) squealer tip with tip hole cooling, (c) plane tip with PS hole cooling, and (d) squealer tip with PS hole cooling.

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Fig. 8

Streamlines based on the relative velocity (CFD results) at 3000 rpm. (a) Plane tip with tip hole cooling, (b) squealer tip with tip hole cooling, (c) plane tip with PS hole cooling, and (d) squealer tip with PS hole cooling.

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Fig. 9

Distribution of the static pressure (CFD results) at: (a) plane tip with tip hole cooling, (b) squealer tip with tip hole cooling, (c) plane tip with PS hole cooling, and (d) squealer tip with PS hole cooling

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Fig. 10

Velocity triangles and relative inlet and exit flow angles for design speed and off-design rotating speeds

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Fig. 11

Effect of rotation on film cooling effectiveness measured for M = 1.25. (a) Plane tip with tip hole cooling, (b) squealer tip with tip hole cooling, (c) plane tip with PS hole cooling, and (d) squealer tip with PS hole cooling.

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Fig. 12

Pitch streamlines based on the relative velocity (CFD results) at different rpm. (a) Plane tip with tip hole cooling, (b) squealer tip with tip hole cooling, (c) plane tip with PS hole cooling, and (d) squealer tip with PS hole cooling.

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Fig. 13

Comparison of CFD results (top row) and experimental results (bottom row) at 3000 rpm, M = 1.25. ((a) and (e)) plane tip with tip hole cooling, ((b) and (f)) squealer tip with tip hole cooling, ((c) and (g)) plane tip with PS hole cooling, and ((d) and (h)) squealer tip with PS hole cooling.

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Fig. 14

Pitchwise-average film cooling effectiveness measured for four different configurations: different blowing ratio at 3000 rpm (top), different rpm at M = 1.25 (bottom)

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Fig. 15

Area-averaged film cooling effectiveness versus rotational speed at the blade tip region at M = 1.25

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Fig. 16

Area-averaged film cooling effectiveness versus blowing ratio at the blade tip region

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