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Research Papers: Flows in Complex Systems

Assessment of Transition Modeling and Compressibility Effects in a Linear Cascade of Turbine Nozzle Guide Vanes

[+] Author and Article Information
Silvia Ravelli

Department of Engineering and
Applied Sciences,
University of Bergamo,
Marconi Street 5,
Dalmine 24044, Italy
e-mail: silvia.ravelli@unibg.it

Giovanna Barigozzi

Department of Engineering and
Applied Sciences,
University of Bergamo,
Marconi Street 5,
Dalmine 24044, Italy
e-mail: giovanna.barigozzi@unibg.it

Ernesto Casartelli

Lucerne University of Applied Sciences
and Arts (HSLU),
Technik & Architektur,
Technikumstrasse 21,
Horw 6048, Switzerland
e-mail: ernesto.casartelli@hslu.ch

Luca Mangani

Lucerne University of Applied Sciences
and Arts (HSLU),
Technik & Architektur,
Technikumstrasse 21,
Horw 6048, Switzerland
e-mail: luca.mangani@hslu.ch

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received October 5, 2016; final manuscript received November 23, 2016; published online March 16, 2017. Assoc. Editor: Kwang-Yong Kim.

J. Fluids Eng 139(5), 051104 (Mar 16, 2017) (13 pages) Paper No: FE-16-1656; doi: 10.1115/1.4035462 History: Received October 05, 2016; Revised November 23, 2016

The flow field in a linear cascade of highly loaded turbine nozzle guide vanes (NGVs) has been numerically investigated at low and high-subsonic regime, i.e., exit isentropic Mach number of M2is = 0.2 and 0.6, respectively. Extensive experimental data are available for an accurate assessment of the numerical procedure. Aerodynamic measurements include not only vane loading and pressure drop in the wake but also local flow features such as boundary layer behavior along both pressure and suction sides of the vane, as well as secondary flow structures downstream of the trailing edge (TE). Simulations were performed by using two computational fluid dynamics (CFD) codes, a commercial one and an open-source based in-house code. Besides computations with the well-established shear-stress transport (SST) k–ω turbulence model assuming fully turbulent flow, transition models were taken into account in the present study. The original version of the γ–Reθ model of Menter was employed. Suluksna–Juntasaro correlations for transition length (Flenght) and transition onset (Fonset) were also tested. The main goal was to establish essential ingredients for reasonable computational predictions of the cascade aerodynamic behavior, under both incompressible and compressible regime. This study showed that transition modeling should be coupled with accurate profiles of inlet velocity and turbulence intensity to get a chance to properly quantify aerodynamic losses via CFD method. However, additional weaknesses of the transition modeling have been put forward when increasing the outlet Mach number.

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References

Horloc, J. H. , and Denton, J. D. , 2005, “ A Review of Some Early Design Practice Using Computational Fluid Dynamics and a Current Perspective,” ASME J. Turbomach., 127(1), pp. 5–13. [CrossRef]
De Palma, P. , 2006, “ Numerical Simulations of Three-Dimensional Transitional Compressible Flows in Turbomachinery Cascade,” Int. J. Numer. Methods Heat Fluid Flow, 16(4), pp. 509–529. [CrossRef]
Bhaskaran, R. , and Lele, S. K. , 2011, “ Heat Transfer Prediction in High Pressure Turbine Cascade With Free-Stream Turbulence Using LES,” AIAA Paper No. 2011-3266.
Papadogiannis, D. , Duchaine, F. , Sicot, F. , Gicquel, L. , Wang, G. , and Moreau, S. , 2014, “ Large Eddy Simulation of a High Pressure Turbine Stage: Effects of Sub-Grid Scale Modeling and Mesh Resolution,” ASME Paper No. GT2014-25876.
Elsner, W. , 2007, “ Transition Modelling in Turbomachinery,” J. Theor. Appl. Mech., 45(3), pp. 539–556.
Michelassi, V. , Wissink, J. G. , Frohlich, J. , and Rodi, W. , 2003, “ Large Eddy Simulation of a Flow Around a Turbine Blade With Incoming Wakes,” AIAA J., 41(11), pp. 2143–2156. [CrossRef]
Wheeler, A. P. S. , Sandberg, R. D. , Sandham, N. D. , Pichler, R. , Michelassi, V. , and Laskowski, G. , 2016, “ Direct Numerical Simulations of a High-Pressure Turbine Vane,” ASME J. Turbomach., 138(7), p. 071003. [CrossRef]
Menter, F. R. , and Langtry, R. B. , 2012, “ Transition Modelling for Turbomachinery Flows,” Low Reynolds Number Aerodynamics and Transition, InTech, Rijeka, Croatia.
Menter, F. R. , Langtry, R. B. , Likki, S. R. , Suzen, Y. B. , Huang, P. G. , and Volker, S. , 2006, “ A Correlation-Based Transition Model Using Local Variables—Part I: Model formulation,” ASME J. Turbomach., 128(3), pp. 413–422. [CrossRef]
Langtry, R. B. , 2006, “ A Correlation-Based Transition Model Using Local Variables for Unstructured Parallelized CFD Codes,” Ph.D. thesis, University of Stuttgart, Stuttgart, Germany.
Langtry, R. B. , Menter, F. R. , Likki, S. R. , Suzen, Y. B. , Huang, P. G. , and Volker, S. , 2006, “ A Correlation-Based Transition Model Using Local Variables—Part II: Test Cases and Industrial Applications,” ASME J. Turbomach., 128(3), pp. 423–434. [CrossRef]
Turgut, O. H. , and Camci, C. , 2011, “ A Computational Validation of Turbine Nozzle Guide Vane Aerodynamic Experiments in an HP Turbine Stage,” ASME Paper No. IMECE2011-64352
Turgut, O. H. , and Camci, C. , 2016, “ Factors Influencing Computational Predictability of Aerodynamic Losses in a Turbine Nozzle Guide Vane Flow,” ASME J. Fluids Eng., 138(5), p. 051103. [CrossRef]
Petersen, A. , 2014, “ Numerical Transition Prediction in a Straight Turbine Cascade,” WCCM XI—ECCM V—ECFD VI (Sixth European Conference on Computational Fluid Dynamics), Barcelona, Spain, July 20–25.
Marconcini, M. , Pacciani, R. , and Arnone, A. , 2015, “ Transition Modelling Implications in the CFD Analysis of a Turbine Nozzle Vane Cascade Tested Over a Range of Mach and Reynolds Numbers,” J. Therm. Sci., 24(6), pp. 526–534. [CrossRef]
Nix, A. C. , Smith, A. C. , Diller, T. E. , Ng, W. F. , and Thole, K. A. , 2002, “ High Intensity, Large Length-Scale Freestream Turbulence Generation in a Transonic Turbine Cascade,” ASME Paper No. GT-2002-30523.
Malan, P. , Suluksna, K. , and Juntasaro, E. , 2009, “ Calibrating the γ-Reθ Transition Model for Commercial CFD,” AIAA Paper No. 2009-1142.
Barigozzi, G. , and Ravelli, S. , 2011, “ The Effect of Turbulence Models on CFD Predictions of the Flowfield in a Turbine Nozzle Vane Cascade,” Tenth International Symposium on Experimental Computational Aerothermodynamics of Internal Flows, Brussels, Belgium, Paper No. ISAIF10-104.
CD-adapco, 2014, “ STAR CCM+ User Guide Version 10.04,” Siemens, Munich, Germany.
Suluksna, K. , Dechaumphai, P. , and Juntasaro, E. , 2009, “ Correlations for Modeling Transitional Boundary Layers Under Influences of Freestream Turbulence and Pressure Gradient,” Int. J. Heat Fluid Flow, 30(1), pp. 66–75. [CrossRef]
Marusic, I. , and Kunkel, G. J. , 2003, “ Streamwise Turbulence Intensity Formulation for Flat-Plate Boundary Layers,” Phys. Fluids, 15(8), pp. 2461–2464. [CrossRef]
OpenCFD, 2005, “ OpenFoam Programmer Guide,” OpenCFD Limited, ESI Group, Paris, France.
OpenCFD, 2005, “ OpenFoam User Guide,” OpenCFD Limited, ESI Group, Paris, France.
Van Doormaal, J. P. , and Raithby, G. D. , 1985, “ An Evaluation of the Segregated Approach for Predicting Incompressible Fluid Flows,” ASME Paper No. 85-HT-9.
Hanimann, L. , Mangani, L. , Casartelli, E. , Mokulys, T. , and Mauri, S. , 2014, “ Development of a Novel Mixing Plane Interface Using a Fully Implicit Averaging for Stage Analysis,” ASME. J. Turbomach., 136(8), p. 081010. [CrossRef]
Mangani, L. , 2008, “ Development and Validation of an Object Oriented CFD Solver for Heat Transfer and Combustion Modeling in Turbomachinery Application,” Ph.D. thesis, Dipartimento di Energetica, Universita` degli Studi di Firenze, Florence, Italy.
Mangani, L. , Facchini, B. , and Bianchini, C. , 2009, “ Conjugate Heat Transfer Analysis of an Internally Cooled Turbine Blades With an Object Oriented CFD Code,” European Turbomachinery Conference ETC09, Istanbul, Turkey, pp. 627–637.
Mangani, L. , and Maritano, M. , 2010, “ Conjugate Heat Transfer Analysis of NASA C3X Film Cooled Vane With an Object-Oriented CFD Code,” ASME Paper No. GT2010-23458.
Mangani, L. , Bianchini, C. , Andreini, A. , and Facchini, B. , 2007, “ Development and Validation of a C++ Object Oriented CFD Code for Heat Transfer Analysis,” Thermal Engineering and Summer Heat Transfer Conference, pp. 1–16, Paper No. AJ-1266.
Langtry, R. B. , and Menter, F. R. , 2005, “ Transition Modeling for General CFD Applications in Aeronautics,” AIAA Paper No. 2005-522.
Langtry, R. B. , and Menter, F. R. , 2009, “ Correlation-Based Transition Modeling for Unstructured Parallelized Computational Fluid Dynamics Codes,” AIAA J., 47(12), pp. 2894–2906. [CrossRef]
Langtry, R. B. , Sengupta, K. , Yeh, D. T. , and Dorgan, A. J. , 2015, “ Extending the Gamma-Rethetat Correlation Based Transition Model for Crossflow Effects,” AIAA Paper No. 2015-2474.
Spalart, P. R. , and Rumsey, C. L. , 2007, “ Effective Inflow Conditions for Turbulence Models in Aerodynamic Calculations,” AIAA J., 45(10), pp. 2544–2553. [CrossRef]
Mayle, R. E. , 1991, “ The Role of Laminar-Turbulent Transition in Gas Turbine Engines,” ASME J. Turbomach., 113(4), pp. 509–536. [CrossRef]
Kost, F. H. , and Holmes, A. T. , 1985, “ Aerodynamic Effect of Coolant Ejection in the Rear Part of Transonic Rotor Blades,” Heat Transfer and Cooling in Gas Turbines, Bergen, Norway, Paper No. AGARD CP 390.
Perdichizzi, A. , and Dossena, V. , 1993, “ Incidence Angle and Pitch-Chord Effects on Secondary Flows Downstream of a Turbine Cascade,” ASME J. Turbomach., 115(3), pp. 383–391. [CrossRef]
Perdichizzi, A. , 1990, “ Mach Number Effects on Secondary Flow Development Downstream of a Turbine Cascade,” ASME J. Turbomach., 112(4), pp. 643–651. [CrossRef]
Sieverding, C. H. , and Wilputte, Ph. , 1981, “ Influence of Mach Number and End Wall Cooling on Secondary Flows in a Straight Nozzle Cascade,” J. Eng. Power, 103(2), pp. 257–263. [CrossRef]

Figures

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Fig. 2

Inlet boundary layer profile (X/cax = −1.6)

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Fig. 3

View of the structured grid

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Fig. 4

Contours of y+ on vane surface, at M2is = 0.6

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Fig. 5

Inlet freestream turbulence profiles

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Fig. 6

Normalized profile Mis distributions at low Mach number (M2is = 0.2)

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Fig. 7

Normalized profile Mis distributions at high Mach number (M2is = 0.6)

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Fig. 8

Predicted skin friction coefficient distributions at M2is values of 0.2 and 0.6

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Fig. 9

Acceleration parameter

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Fig. 10

Blade-to-blade Mach number distribution at M2is = 0.2

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Fig. 11

Contours of intermittency at M2is = 0.2

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Fig. 12

Profile of Reθc at M2is = 0.2

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Fig. 13

Predicted and measured boundary layer profiles along the vane SS at M2is = 0.2

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Fig. 14

Predicted and measured boundary layer profiles along the vane PS at M2is = 0.2

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Fig. 15

Contours of intermittency at M2is = 0.6

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Fig. 16

Profile of Reθc at M2is = 0.6

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Fig. 17

Predicted and measured boundary layer profiles along the vane SS (left) and PS (right) at M2is = 0.6

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Fig. 18

Predicted and measured normalized total pressure loss profile at M2is values of 0.2 (left) and 0.6 (right), X/cax = 1.53

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Fig. 19

Predicted and measured contours of kinetic energy loss coefficient ζ at X/cax = 1.53 and M2is = 0.2

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Fig. 20

Predicted and measured contours of kinetic energy loss coefficient ζ at X/cax = 1.53 and M2is = 0.6

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Fig. 21

SS flow visualizations at M2is values of 0.2 (left) and 0.6 (right)

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Fig. 22

SS contours of computed skin friction coefficient cf at M2is values of 0.2 (left) and 0.6 (right)

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