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Research Papers

Conjugate Heat Transfer Methodology for Thermal Design and Verification of Gas Turbine Cooled Components

[+] Author and Article Information
Lorenzo Winchler

Department of Industrial Engineering,
University of Florence,
via di Santa Marta 3,
Florence 50139, Italy
e-mail: lorenzo.winchler@htc.unifi.it

Antonio Andreini

Department of Industrial Engineering,
University of Florence,
via di Santa Marta 3,
Florence 50139, Italy
e-mail: antonio.andreini@htc.unifi.it

Bruno Facchini

Department of Industrial Engineering,
University of Florence,
via di Santa Marta 3,
Florence 50139, Italy
e-mail: bruno.facchini@htc.unifi.it

Luca Andrei

Baker Hughes, a GE company,
via Felice Matteucci 2,
Florence 50127, Italy
e-mail: luca.andrei@bhge.com

Alessio Bonini

Baker Hughes, a GE company,
via Felice Matteucci 2,
Florence 50127, Italy
e-mail: alessio.bonini@bhge.com

Luca Innocenti

Baker Hughes, a GE company,
via Felice Matteucci 2,
Florence 50127, Italy
e-mail: luca1.innocenti@bhge.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 17, 2018; final manuscript received August 1, 2018; published online October 15, 2018. Editor: Kenneth Hall.

J. Turbomach 140(12), 121001 (Oct 15, 2018) (8 pages) Paper No: TURBO-18-1161; doi: 10.1115/1.4041061 History: Received July 17, 2018; Revised August 01, 2018

Gas turbine design has been characterized over the years by a continuous increase of the maximum cycle temperature, justified by a corresponding increase of cycle efficiency and power output. In such way, turbine components heat load management has become a compulsory activity, and then, a reliable procedure to evaluate the blades and vanes metal temperatures is, nowadays, a crucial aspect for a safe components design. In the framework of the design and validation process of high pressure turbine cooled components of the BHGE NovaLTTM 16 gas turbine, a decoupled methodology for conjugate heat transfer prediction has been applied and validated against measurement data. The procedure consists of a conjugate heat transfer analysis in which the internal cooling system (for both airfoils and platforms) is modeled by an in-house one-dimensional thermo-fluid network solver, the external heat loads and pressure distribution are evaluated through 3D computational fluid dynamics (CFD) analysis and the heat conduction in the solid is carried out through a 3D finite element method (FEM) solution. Film cooling effect has been treated by means of a dedicated CFD analysis, implementing a source term approach. Predicted metal temperatures are finally compared with measurements from an extensive test campaign of the engine in order to validate the presented procedure.

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References

Kassab, A. , Divo, E. , Heidmann, J. , Steinthorsson, E. , and Rodriguez, F. , 2003, “ BEM/FVM Conjugate Heat Transfer Analysis of a Three-Dimensional Film Cooled Turbine Blade,” Int. J. Numer. Methods Heat Fluid Flow, 13(5), pp. 581–610. [CrossRef]
York, W. D. , and Leylek, J. H. , 2003, “ Three-Dimensional Conjugate Heat Transfer Simulation of an Internally-Cooled Gas Turbine Vane,” ASME Paper No. GT2003-38551.
Bohn, D. , Bonhoff, B. , and Schonenborn, H. , 1995, “ Combined Aerodynamic and Thermal Analysis of a High-Pressure Turbine Nozzle Guide Vane,” Report No. RWTH-CONV-174593.
Bohn, D. , Bonhoff, B. , Schonenborn, H. , and Wilhelmi, H. , 1995, “ Prediction of the Film-Cooling Effectiveness of a Gas Turbine Blades Using a Numerical,” AIAA Paper No. 95-7105.
Takahashi, T. , Watanabe, K. , Takahashi, T. , and Wilhelmi, H. , 2000, “ Thermal Conjugate Analysis of a First Stage Blade in a Gas Turbine,” ASME Paper No. GT2000-0251.
Kassab, A. , Divo, E. , Heidmann, J. , Steinthorsson, E. , and Rodriguez, F. , 2003, “ Conjugate Heat Transfer Effects on a Realistic Film Cooled Turbine Vane,” ASME Paper No. GT2003-38553.
Han, J. C. , Ortman, D. , and Lee, C. , 1982, “ A Computer Model for Gas Turbine Blade Cooling Analysis,” ASME Paper No. 82-JPGC-GT-6.
Kumar, B. , and Prasad, B. , 2006, “ A Combined CFD and Network Approach for a Simulated Turbine Blade Cooling System,” Indian J. Eng. Mater. Sci., 13, pp. 195–201.
Carcasci, C. , Facchini, B. , and Ferrara, G. , 1995, “ A Rotor Blade Cooling Design Method for Heavy Duty Gas Turbine Applications,” ASME Paper No. 95-CTP-90.
Carcasci, C. , and Facchini, B. , 1996, “ A Numerical Procedure to Design Internal Cooling of Gas Turbine Stator Blades,” Rev. Gén. Therm., 35(412), pp. 257–268. [CrossRef]
Arnone, A. , Liou, M. S. , and Povinelli, L. A. , 1992, “ Navier-Stokes Solution of Transonic Cascade Flow Using Non-Periodic C-Type Grids,” ASME J. Propul. Power, 8(2) pp. 410–417. [CrossRef]
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.
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,” National Aeronautics and Space Administration, Washington, DC, Technical Report No. NASA CR-168015. https://ntrs.nasa.gov/search.jsp?R=19830020105
Alizadeh, M. , Izadi, A. , and Fathi, A. , 2014, “ Sensitivity Analysis on Turbine Blade Temperature Distribution Using Conjugate Heat Transfer Simulation,” ASME J. Turbomach., 136(1), p. 011001. [CrossRef]
Andrei, L. , Andreini, A. , Facchini, B. , and Winchler, L. , 2014, “ An in House Developed Decoupled Procedure: Application and Validation on a Gas Turbine Vane With Different Cooling Configurations,” Energy Procedia, 45, pp. 1087–1096. [CrossRef]
Hylton, L. D. , Nirmalan, N. V. , Sultanian, B. K. , and Kaufman, R. M. , 1988, “ The Effects of Leading Edge and Downstream Film Cooling on Turbine Vane Heat Transfer,” National Aeronautics and Space Administration, Washington, DC, Technical Report No. NASA CR-182133. https://ntrs.nasa.gov/search.jsp?R=19890004383
Bonini, A. , Andreini, A. , Carcasci, C. , Facchini, B. , Ciani, A. , and Innocenti, L. , 2012, “ Conjugate Heat Transfer Calculations on GT Rotor Blade for Industrial Applications—Part I: Equivalent Internal Fluid Network Setup,” ASME Paper No. GT2012-69846.
Andrei, L. , Innocenti, L. , Andreini, A. , Facchini, B. , and Winchler, L. , 2017, “ Film Cooling Modeling for Gas Turbine Nozzles and Blades: Validation and Application,” ASME J. Turbomach., 139(1), p. 011004. [CrossRef]
Winchler, L. , 2016, “ Design Tools and Innovative Concepts for Gas Turbine Cooling Applications,” Ph.D. thesis, Università degli Studi di Firenze, Dipartimento di Ingegneria Industriale, Florence, Italy
L'Ecuyer, M. R. , and Soechting, F. O. , 1985, A Model for Correlating Flat Plate Film-Cooling Effectiveness for Rows of Round Holes, AGARD Heat Transfer and Cooling in Gas Turbines, Anatalia, Turkey, p.12.
Baldauf, S. , Scheurlen, M. , Schulz, A. , and Wittig, S. , 2002, “ Correlation of Film-Cooling Effectiveness From Thermographic Measurements at Engine-Like Conditions,” ASME J. Turbomach, 124(4), pp. 686–698. [CrossRef]
Florschuetz, L. , Truman, C. , and Metzger, D. , 1981, “ Streamwise Flow and Heat Transfer Distributions for Jet Array Impingement With Crossflow,” ASME J. Heat Transfer, 103, pp. 337–342. [CrossRef]
Faulkner, F. E. , 1971, “ Analytical Investigation of Chord Size and Cooling Methods on Turbine Blade Cooling Requirements,” National Aeronautics and Space Administration, Washington, DC, Technical Report No. NASA CR-120882. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19730009082.pdf
Metzger, D. , Shepard, W. , and Haley, S. , 1986, “ Row Resolved Heat Transfer Variations in Pin-Fin Arrays Including Effects of Non-Uniform Arrays and Flow Convergence,” ASME Paper No. 86-GT-132.
Goldstein, R. J. , 1971, “ Film Cooling,” Adv. Heat Transfer, 7, pp. 321–379. [CrossRef]
Gritsch, M. , Schulz, A. , and Wittig, S. , 2001, “ Effect of Crossflows on the Discharge Coefficient of Film Cooling Holes With Varying Angles of Inclination and Orientation,” J. Turbomach., 123(4), pp. 781–787. [CrossRef]
Reichert, A. W. , Brillert, D. , and Simon, H. , 1997, “ Loss Prediction for Rotating Passages in Secondary Air Systems,” ASME Paper No. 97-GT-215.
Da Soghe, R. , and Andreini, A. , 2013, “ Numerical Characterization of Pressure Drop Across the Manifold of Turbine Casing Cooling System,” J. Turbomach., 135(3), p. 031017. [CrossRef]
Mazzei, L. , Winchler, L. , and Andreini, A. , 2017, “ Development of a Numerical Correlation for the Discharge Coefficient of Round Inclined Holes With Low Crossflow,” Comput. Fluids, 152, pp. 182–192. [CrossRef]
Han, J. C. , Dutta, S. , and Ekkad, S. , 2013, Gas Turbine Heat Transfer and Cooling Technology, 2nd ed., CRC Press, Boca Raton, FL.
Andrei, L. , Andreini, A. , Bianchini, C. , and Facchini, B. , 2013, “ Numerical Benchmark of Nonconventional RANS Turbulence Models for Film and Effusion Cooling,” ASME J. Turbomach., 135(4), p. 041026. [CrossRef]
Seller, J. P. , 1963, “ Gaseous Film Cooling With Multiple Injection Stations,” AIAA J., 1(9), pp. 2154–2156. [CrossRef]

Figures

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Fig. 1

Blade and nozzle network cooling design flow chart, film cooling modeled from correlations

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Fig. 2

Blade and nozzle network cooling design flow chart

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Fig. 3

Film cooling modeling: injection volumes shape [18]: (a) cylinder and (b) delimited cylinder

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Fig. 4

Film cooling modeling application on a real nozzle: comparison of adiabatic effectiveness maps between PSP (a) and FCM (b) [18]

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Fig. 5

Film cooling modeling application on a real nozzle: span-wise averaged ηad profiles comparison [18]

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Fig. 6

NovaLT16 conceptual internal cooling network: (a) first cavity network scheme (LE) and (b) second cavity network scheme (trailing edge)

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Fig. 7

Dimensionless adiabatic wall temperatures on different span sections

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Fig. 8

Dimensionless external HTC distributions on different span sections

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Fig. 9

Map of dimensionless external HTC on the studied sector surfaces

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Fig. 10

Map of dimensionless external Taw values corrected by film cooling on a portion of PS: comparison between correlations (a) and FiCUS (b) correction

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Fig. 11

Taw values corrected by a different film cooling approach compared with raw data on span = 50%

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Fig. 12

Comparison between experimental and calculated massflow

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Fig. 13

Comparison between experimental data and numerical temperature profiles at 50% span location

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Fig. 14

Comparison between experimental data and numerical temperature profile at 15% span location

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Fig. 15

Comparison between experimental data and numerical temperature profile at 85% span location

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