Research Papers

Sensitivity Analysis on Turbine Blade Temperature Distribution Using Conjugate Heat Transfer Simulation

[+] Author and Article Information
Mohammad Alizadeh

e-mail: em.alizadeh@gmail.com

Ali Izadi

e-mail: aliizadi.ut@gmail.com
School of Mechanical Engineering,
College of Engineering,
University of Tehran,
Tehran, Iran

Alireza Fathi

K.N.T. University,
Tehran, Iran
e-mail: alireza.fathy@gmail.com

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received May 8, 2012; final manuscript received March 17, 2013; published online September 20, 2013. Assoc. Editor: Karen A. Thole.

J. Turbomach 136(1), 011001 (Sep 20, 2013) (13 pages) Paper No: TURBO-12-1045; doi: 10.1115/1.4024637 History: Received May 08, 2012; Revised March 17, 2013

Heat transfer parameters are the most critical variables affecting turbine blade life. Therefore, accurately predicting heat transfer parameters is essential. In this study, for precise prediction of the blade temperature distribution, a conjugate heat transfer procedure is used. This procedure involves three different physical aspects: flow and heat transfer in external domain and internal cooling passages and conduction within metal blade. For the external flow simulation and conduction within metal, three-dimensional solvers are used. However, three-dimensional modeling of blade cooling passages is time-consuming because of complex cooling passage geometries. Therefore, in the current work, a one-dimensional network method is used for the simulation of cooling passages. For validation of the numerical procedure, simulation results are compared with the available experimental data for a C3X vane. Results show good agreement against experimental data. The present paper investigates uncertainties of some parameters that affect turbine blade heat transfer, namely, (1) turbine inlet temperature and pressure, (2) upstream stator coolant mass flow rate and temperature, (3) rotor shroud heat transfer coefficient and fluid temperature over shroud, (4) rotor coolant inlet pressure and temperature (as a result of secondary air system), (5) blade metal thermal conductivity, and (6) blade coating thickness and thermal conductivity. Results show that turbine inlet temperature, pressure drop and temperature rise in the secondary air system (SAS) and coating parameters have significant effect on the blade temperature.

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Bohn, D. E., and Tummers, C., 2003, “Numerical 3-D Conjugate Flow and Heat Transfer Investigation of a Transonic Convection-Cooled Thermal Barrier Coated Turbine Guide Vane With Reduced Cooling Fluid Mass Flow,” ASME Paper No. GT2003-38431. [CrossRef]
York, W. D., and Leyek, J. H., 2003, “Three-Dimensional Conjugate Heat Transfer Simulation of an Internally Cooled Gas Turbine Vane,” ASME Paper No. GT2003-38551. [CrossRef]
Luo, J., and Razinsky, E. H., 2007, “Conjugate Heat Transfer Analysis of a Cooled Turbine Vane Using the v2-f Turbulence Model,” ASME J. Turbomach., 129, pp. 773–781. [CrossRef]
Ledezma, G. A., Laskowsky, G. M., and Tolpadi, A. K., 2008, “Turbulence Model Assessment for Conjugate Heat Transfer in a High Pressure Turbine Vane Model,” ASME Paper No. GT2008-50498. [CrossRef]
Wang, Z., Yan, P., Guo, Z., and Han, W., 2008, “BEM/FDM Conjugate Heat Transfer Analysis of a Two-Dimensional Air-Cooled Turbine Blade Boundary Layer,” J. Thermal Sci., 17(3), pp. 199–206. [CrossRef]
Qiang, W., Zhaoyuan, G., Chi, Z., Guotai, F., and Zhongqi, W., 2009, “Coupled Heat Transfer Simulation of a High-Pressure Turbine Nozzle Guide Vane,” Chin. J. Aeronaut., 22, pp. 230–236. [CrossRef]
Wang, Z., Yan, P., Huang, H., and Han, W., 2009, “Coupled BEM and FDM Conjugate Analysis of a Three-Dimensional Air-Cooled Turbine Vane,” ASME Paper No. GT2009-59030. [CrossRef]
Bohn, D., Kusterer, K., and Tanaka, T. S. R., 2004, “Conjugate Calculations for a Film-Cooled Blade Under Different Operating Conditions,” ASME Paper No. GT2004-53719. [CrossRef]
Sipatov, A., Gomzikov, L., Latyshev, V., and Gladysheva, N., 2009, “Three Dimensional Heat Transfer Analysis of High Pressure Turbine,” ASME Paper No. GT2009-59163. [CrossRef]
Mangani, L., Cerutti, M., Maritano, M., and Spel, M., 2010, “Conjugate Heat Transfer Analysis of NASA C3X Film Cooled Vane With an Object-Oriented CFD Code,” ASME Paper No. GT2010-23458. [CrossRef]
Ni, R. H., Humber, W., Fan, G., Johnson, P. D., Downs, J., Clark, J. P., and Koch, P. J., 2011, “Conjugate Heat Transfer Analysis of a Film-Cooled Turbine Vane,” ASME Paper No. GT2011-45920. [CrossRef]
Dewey, R., and Hulshof, H., 2000, Combustion Turbine F-Class Life Management: General Electric FA First Stage Blade Analysis, EPRI Solutions, Palo Alto, CA.
Zecchi, S., Arcangeli, L., Facchini, B., and Coutandin, D., 2004, “Features of a Cooling System Simulation Tool Used in Industrial Preliminary Design Stage,” ASME Paper No. GT2004-53547. [CrossRef]
Takahashi, T., Watanabe, K., and Sakai, T., 2005, “Conjugate Heat Transfer Analysis of a Rotor Blade With Rib-Roughened Internal Cooling Passages,” ASME Paper No. GT2005-68227. [CrossRef]
Coutandin, D., Taddei, S., and Facchini, B., 2006, “Advanced Double Wall Cooling System Development for Turbine Vanes,” ASME Paper No. GT2006-90784. [CrossRef]
Amaral, S., Verstraete, T., Braembussche, R. V. D., and Arts, T., 2010, “Design and Optimization of the Internal Cooling Channels of a High Pressure Turbine Blade—Part I: Methodology,” ASME J. Turbomach., 132, pp. 021013. [CrossRef]
Haubert, R. C., HsiaSr., E., Maclin, H. M., Noe, M. E., and Brooks, R. O., 1980, “High Pressure Turbine Blade Life Sensitivity,” AIAA Paper No. 80-1112. [CrossRef]
Roos, T., 2005, “NGV Trailing Edge Ejection Slot Size Sensitivity Study,” Paper No. ISABE-2005-1158.
Espinosa, F., Portugal, A., Narzary, D., Cadena, F., Han, J., Kubiak, J., Blake, S., and Lara, H., 2008, “Influence of Cooling Flow Rate Variation on Gas Turbine Blade Temperature Distributions,” ASME Paper No. GT2008-50103. [CrossRef]
Hylton, L. D., Mihelc, M. S., Turner, E. R., Nealy, D. A., and York, R. E., 1983, “Analytical and Experimental Evaluation of the Heat Transfer Distribution Over the Surfaces of Turbine Vanes,” NASA Report No. CR-168015.
Meitner, P. L., 1990, “Computer Code for Predicting Coolant Flow and Heat Transfer in Turbomachinery,” NASA TP-2985, AVSCOM TP 89-C-008.
Meitner, P. L., 2003, “Procedure for Determining 1-D Flow Distributions in Arbitrarily Connected Passages Without the Influence of Pumping,” ASME Paper No. GT2003-38061. [CrossRef]
Dees, J. E., Bogard, D. G., Ledezma, G. A., Laskowski, G. M., and Tolpadi, A. K., 2010, “Experimental Measurements and Computational Predictions for an Internally Cooled Simulated Turbine Vane With 90 Degree Rib Turbulators,” ASME Paper No. GT2010-23004. [CrossRef]
Bianchini, C., Facchini, B., Mangani, L., and Maritano, M., 2008, “Generic Grid Interface Development and Application to Conjugate Heat Transfer Analysis,” Open Source CFD International Conference, Berlin, December 4–5.
Facchini, B., Bianchini, C., and Mangani, L., 2009, “Conjugate Heat Transfer Analysis of an Internally Cooled Turbine Blade With an Object Oriented CFD Code,” Eighth European Conference on Turbomachinery, Graz, Austria, March 23–27.
Brown, W. F., Mindlin, H., and Ho, C. Y., 1997, Aerospace Structural Metals Handbook CINDAS/USAF CRDA Handbooks Operation, Purdue University, West Lafayette, IN.
Han, J. C., and Chandra, P. R., 1988, “Local Heat/Mass Transfer and Pressure Drop Two-Pass Rib-Roughened Channel for Turbine Airfoil Cooling,” NASA Technical Report, NASA CR-1 79635 2 AVSCOM TR-87-C-14.
Yeh, F. C., and Stepka, F. S., 1984, “Review and Status of Heat-Transfer Technology for Internal Passages of Air-Cooled Turbine Blades,” NASA Technical Paper, NASA TP-2232.
Maldonado, J. J., 1994, “Numerical Comparison of Convective Heat Transfer Augmentation Devices Used in Cooling Channels of Hypersonic Vehicles,” NASA-TM- 106546.
Han, J. C., Park, J. S., and Ibrahim, M. Y., 1986, “Measurement of Heat Transfer and Pressure Drop in Rectangular Channels With Turbulence Promoters,” NASA Technical Report, NASA CR-4015 AVSCOM TR-86-C-25.
Sundberg, J., 2006, “Heat Transfer Correlations for Gas Turbine Cooling,” M.Sc. thesis, Linköping University, Linköping, Sweden.
Crawford, N. M., Cunningham, G., and Spedding, P. L., 2003, “Prediction of Pressure Drop for Turbulent Fluid Flow in 90 Degree Bends,” J. Process Mech. Eng., 217, pp. 153–155. [CrossRef]
Mori, Y., and Nakayama, W., 1967, “Study on Forced Convective Heat Transfer in Curved Pipes (2nd Report, Turbulent Region),” Int. J. Heat Mass Transfer, 10, pp. 37–59. [CrossRef]
Brigham, B. A., 1985, “The Effect of Channel Convergence in a Heat Transfer in a Passage With Short Pin Fins,” NASA-TM-83801.
Damerow, W. P., Murtaugh, J. P., and Burggraf, F., 1972, “Experimental and Analytical Investigation of the Coolant Flow Characteristics in Cooled Turbine Airfoils,” NASA Technical Paper, NASA-CR-120883.
Hay, N., and Lampard, D., 1998, “Discharge Coefficient of Turbine Cooling Holes: A Review,” ASME J. Turbomach., 120, pp. 314–319. [CrossRef]
Martini, P., Schulz, A., and Bauer, H. J., 2006, “Film Cooling Effectiveness and Heat Transfer on the Trailing Edge Cutback of Gas Turbine Airfoils With Various Internal Cooling Designs,” ASME J. Turbomach., 128, pp. 196–205. [CrossRef]
Brink, R. C., 1989, “Material Property Evaluation of Thick Thermal Barrier Coating Systems,” ASME J. Eng. Gas Turb. Power, 111, pp. 570–577. [CrossRef]
Lu, T. J., Levi, C. G., Wadley, H. N. G., and Evans, A. G., 2001, “Distributed Porosity as a Control Parameter for Oxide Thermal Barriers Made by Physical Vapor Deposition,” J. Am. Ceramic Soc., 84(12), pp. 2937–2946. [CrossRef]


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Fig. 1

Conjugate heat transfer algorithm

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Fig. 2

Solution algorithm of the 1D network method

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Fig. 3

C3X geometry and the 1D elements of ten coolant channels

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Fig. 4

View of numerical mesh on plane of constant spanwise coordinates

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Fig. 5

Predicted and measured pressure distribution on the midspan plane

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Fig. 6

Nondimensional temperature distribution on the midspan plane

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Fig. 7

Temperature contours of the vane on (a) pressure side (b) suction side

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Fig. 8

CAD model of simulated blade and its internal cooling passages

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Fig. 9

Schematic view of the rotor blade cooling passages network

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Fig. 10

Boundary connections between 1D code and 3D model

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Fig. 11

Blade temperature distribution for the reference case

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Fig. 12

Flow field and metal temperature distribution at 70% span

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Fig. 13

The diagram of different regions of blade. (a) Defined regions for averaging, (b) shroud surface on which HTC and bulk temperature is applied (light gray).

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Fig. 14

Computational domain and locations of boundary conditions

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Fig. 15

The effects of turbine inlet temperature on the blade temperature

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Fig. 16

The effects of turbine inlet pressure on the blade temperature

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Fig. 17

Blade temperature distribution versus vane coolant mass flow rate

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Fig. 18

Blade temperature distribution versus its upstream vane coolant temperature

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Fig. 19

The flow from outer casing

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Fig. 20

Blade temperature variation versus shroud heat transfer coefficient

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Fig. 21

Blade temperature variation versus coolant temperature over shroud

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Fig. 22

Blade temperature variation versus pressure drop at the coolant inlet

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Fig. 23

Blade temperature variation versus coolant inlet temperature

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Fig. 24

Blade temperature variation versus blade metal thermal conductivity

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Fig. 25

Blade temperature variation versus coating thickness

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Fig. 26

Blade temperature variation versus coating thermal conductivity




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