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Research Papers

Measurements of Hub Flow Interaction on Film Cooled Nozzle Guide Vane in Transonic Annular Cascade

[+] Author and Article Information
Lamyaa A. El-Gabry

Mechanical Engineering Department,
The American University in Cairo,
New Cairo 11835, Egypt;
Research Fellow
Department of Energy Technology,
Royal Institute of Technology (KTH),
Stockholm 10044, Sweden

Ranjan Saha, Jens Fridh, Torsten Fransson

Department of Energy Technology,
Royal Institute of Technology (KTH),
Stockholm 10044, Sweden

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 5, 2014; final manuscript received November 14, 2014; published online January 28, 2015. Editor: Kenneth C. Hall.

J. Turbomach 137(8), 081004 (Aug 01, 2015) (9 pages) Paper No: TURBO-14-1287; doi: 10.1115/1.4029242 History: Received November 05, 2014; Revised November 14, 2014; Online January 28, 2015

An experimental study has been performed in a transonic annular sector cascade of nozzle guide vanes (NGVs) to investigate the aerodynamic performance and the interaction between hub film cooling and mainstream flow. The focus of the study is on the endwalls, specifically the interaction between the hub film cooling and the mainstream. Carbon dioxide (CO2) has been supplied to the coolant holes to serve as tracer gas. Measurements of CO2 concentration downstream of the vane trailing edge (TE) can be used to visualize the mixing of the coolant flow with the mainstream. Flow field measurements are performed in the downstream plane with a five-hole probe to characterize the aerodynamics in the vane. Results are presented for the fully cooled and partially cooled vane (only hub cooling) configurations. Data presented at the downstream plane include concentration contour, axial vorticity, velocity vectors, and yaw and pitch angles. From these investigations, secondary flow structures such as the horseshoe vortex, passage vortex, can be identified and show the cooling flow significantly impacts the secondary flow and downstream flow field. The results suggest that there is a region on the pressure side (PS) of the vane TE where the coolant concentrations are very low suggesting that the cooling air introduced at the platform upstream of the leading edge (LE) does not reach the PS endwall, potentially creating a local hotspot.

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References

Langston, L. S., Nice, L. M., and Hooper, R. M., 1977, “Three Dimensional Flow Within a Turbine Cascade Passage,” ASME J. Eng. Gas Turbines Power, 99(1), pp. 21–28. [CrossRef]
Gregory-Smith, D. G., Graves, C. P., and Walsh, J. A., 1988, “Growth of Secondary Losses and Vorticity in an Axial Turbine Cascade,” ASME J. Turbomach., 110(1), pp. 1–8. [CrossRef]
Sieverding, C. H., 1985, “Recent Progress in the Understanding of Basic Aspects of Secondary Flows in Turbine Blade Passages,” ASME J. Eng. Gas Turbines Power, 107(2), pp. 248–257. [CrossRef]
Langston, L. S., 2001, “Secondary Flows in Axial Turbines—A Review,” Ann. N. Y. Acad. Sci., 934(1), pp. 11–26. [CrossRef] [PubMed]
Simon, T. W., and Piggush, J. D., 2006, “Turbine Endwall Aerodynamics and Heat Transfer,” AIAA J. Propul. Power, 22(2), pp. 301–312. [CrossRef]
Acharya, S., and Mahmood, G. I., 2006, “Turbine Blade Aerodynamics,” The Gas Turbine Handbook, Vol. 1.0, National Energy Technology Laboratory (NETL)—DOE, Morgantown, WV, Chap. 4.3.
Denton, J. D., 1993, “Loss Mechanism in Turbomachines,” ASME J. Turbomach., 115(4), pp. 621–656. [CrossRef]
Thole, K. A., Sinha, A. K., Bogard, D. G., and Crawford, M. E., 1990, “Mean Temperature Measurements of Jets in Crossflow for Gas Turbine Film Cooling Applications,” Rotating Machinery Transport Phenomena, J. H. Kim and W. J. Yang, eds., Hemisphere Publishing Corporation, New York.
Sinha, A. K., Bogard, D. G., and Crawford, M. E., 1991, “Film-Cooling Effectiveness Downtream of a Single Row of Holes With Variable Density Ratio,” ASME J. Turbomach., 113(3), pp. 442–449. [CrossRef]
Foster, N. W., and Lampard, D., 1980, “The Flow and Film Cooling Effectiveness Following Injection Through a Row of Holes,” ASME J. Eng. Gas Turbines Power, 102(3), pp. 584–588. [CrossRef]
Kohli, A., and Bogard, D. G., 1997, “Adiabatic Effectiveness, Thermal Fields, and Velocity Fields for Film Cooling With Large Angle Injection,” ASME J. Turbomach., 119(2), pp. 352–358. [CrossRef]
Foster, N. W., and Lampard, D., 1975, “Effect of Density and Velocity Ratio of Discrete Hole Film Cooling,” AIAA J., 13(8), pp. 1112–1114. [CrossRef]
Pietrzyk, J. R., Bogard, D. G., and Crawford, M. E., 1990, “Effect of Density Ratio on the Hydrodynamics of Film Cooling,” ASME J. Turbomach., 112(3), pp. 437–443. [CrossRef]
Pietrzyk, J. R., Bogard, D. G., and Crawford, M. E., 1989, “Hydrodynamic Measurements of Jets in Crossflow for Gas Turbine Film Cooling Application,” ASME J. Turbomach., 111(2), pp. 139–145. [CrossRef]
El-Gabry, L., Thurman, D., Poinsatte, P., and Heidmann, J., 2013, “Detailed Velocity and Turbulence Measurements in an Inclined Large-Scale Film Cooling Array,” ASME J. Turbomach., 135(6), p. 061013. [CrossRef]
Thurman, D., E-Gabry, L., Poinsatte, P., and Heidmann, J., 2011, “Turbulence and Heat Transfer Measurements in an Inclined Large Scale Film Cooling Array—Part II, Temperature and Heat Transfer Measurements,” ASME Paper No. GT2011-46498. [CrossRef]
Day, C. R. B., Oldfield, L. G., and Lock, G. D., 2000, “Aerodynamic Performance of an Annular Cascade of Film Cooled Nozzle Guide Vanes Under Engine Representative Conditions,” Exp. Fluids, 29(2), pp. 117–129. [CrossRef]
Jones, T. V., 1999, “Theory for the Use of Foreign Gas in Simulating Film Cooling,” Int. J. Heat Fluid Flow, 20(3), pp. 349–354. [CrossRef]
Burns, W. K., and Stollery, J. L., 1969, “The Influence of Foreign Gas Injection and Slot Geometry on Film Cooling Effectiveness,” Int. J. Heat Mass Transfer, 12(8), pp. 935–951. [CrossRef]
Narzary, D. P., Liu, K. C., Rallabandi, A. P., and Hau, J. C., 2010 “Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique,” ASME Turbo Expo 2010: Power for Land, Sea, and Air, ASME Paper No. GT 2010-22781.
Walters, D. K., and Leylek, J. H., 2000 “Impact of Film-Cooling Jets on Turbine Aerodynamic Losses,” ASME J. Turbomach., 122(3), pp. 537–545. [CrossRef]
Roux, J., 2004, “Experimental Investigation of Nozzle Guide Vanes in a Sector of an Annular Cascade,” Licentiate Thesis, Department of Energy Technology, Royal Institute of Technology, Stockholm, Sweden.
Putz, F. M., 2010, “Load, Secondary Flow, and Turbulence Measurements on Film Cooled Nozzle Guide Vanes in a Transonic Annular Sector Cascade,” M.Sc. thesis, KTH Royal Institute of Technology, Stockholm, Sweden, EGI-2010-067 MSC EKV 806.
Anderson, J. D., 2004, “Modern Compressible Flow With Historical Perspective,” 3rd ed., McGraw-Hill, New York.
Gregory-Smith, D. G., and Cleak, J. G. E., 1992, “Secondary Flow Measurements in a Turbine Cascade With High Inlet Turbulence,” ASME J. Turbomach., 114(1), pp. 173–183. [CrossRef]
Goldstein, R. J., and Spore, R. A., 1988, “Turbulent Transport on the Endwall in the Region Between Adjacent Turbine Blades,” ASME J. Heat Transfer, 110(4a), pp. 862–869. [CrossRef]

Figures

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Fig. 1

Sketch annular cascade upstream of test section [23]

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Fig. 2

(a) Cut-through of cascade at midspan [23]. (b) Cooling holes on test NGV [23].

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Fig. 3

Distribution of blowing ratio for the vane cooling holes at mass flux ratio 7.75%

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Fig. 4

Airfoil Mach number distribution at 25%, 50%, and 75% span

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Fig. 5

Endwall Mach number distribution from CFD simulation

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Fig. 6

Normalized inlet total pressure

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Fig. 7

Total pressure distribution at 20% span

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Fig. 8

Exit flow angle distribution for fully air cooled vane

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Fig. 9

Pitch angle distribution for fully air cooled vane

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Fig. 10

Flow vector for fully air-cooled vane

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Fig. 11

Near hub vorticity for fully air-cooled vane

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Fig. 12

Comparison of velocity vector for fully air cooled (black) and hub air cooled (red)

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Fig. 13

Vorticity distribution for partially cooled with air

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Fig. 14

Velocity vectors for air cooled (black) and CO2 cooled (red)

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Fig. 15

Vorticity distribution for CO2 cooled

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Fig. 16

CO2 concentration measurement repeatability

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Fig. 17

CO2 concentration and flow vectors for CO2 cooled vane matching BR (run 5)

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Fig. 18

CO2 concentration and flow vectors for CO2 cooled vane matching MR (run 6)

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Fig. 19

CO2 concentration and vorticity (thin line) for CO2 cooled vane matching BR (run 5)

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Fig. 20

CO2 concentration and vorticity (thin line) for CO2 cooled matching MR (run 6)

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Fig. 21

Percent difference of CO2 between matched blowing ratio and momentum ratio

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Fig. 22

Pitch and yaw angle definition [22]

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