Research Papers

Effects of Subgrid Scale Modeling on the Deterministic and Stochastic Turbulent Energetic Distribution in Large-Eddy Simulations of a High-Pressure Turbine Stage

[+] Author and Article Information
Dimitrios Papadogiannis

CFD Team,
42 Avenue Gaspard Coriolis,
Toulouse 31057, France
e-mail: dimitrios.papadogiannis@safran.fr

Florent Duchaine, Laurent Gicquel

CFD Team,
42 Avenue Gaspard Coriolis,
Toulouse 31057, France

Gaofeng Wang

School of Aeronautics and Astronautics,
Zhejiang University,
Zhejiang 310027, China

Stéphane Moreau

Département de Génie Mécanique,
University of Sherbrooke,
Sherbrooke QC J1K 2R1, Canada

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received January 7, 2015; final manuscript received November 26, 2015; published online April 12, 2016. Assoc. Editor: Graham Pullan.

J. Turbomach 138(9), 091005 (Apr 12, 2016) (10 pages) Paper No: TURBO-15-1003; doi: 10.1115/1.4032844 History: Received January 07, 2015; Revised November 26, 2015

This study focuses on the engine-representative MT1 transonic high-pressure turbine. Simulated by use of wall-modeled large-eddy simulations (LES) with three different subgrid scale (SGS) closures, mean pressure profiles across the blades as well as mean radial profiles at the rotor exit are found to be in good agreement with experimental data with only local differences between models. Unsteady flow features, inherently present in LES, are however affected by SGS modeling. This is evidenced by the relative energetic content of the deterministic to stochastic turbulent contributions evaluated, thanks to the triple decomposition analysis of the simulations. Origins of such differences are found to impact the entire radial distribution of the flow and activity, with deterministic and chaotic contributions distributed differently depending on the SGS model and reference frequency used to extract the deterministic signal. Such flow responses can be attributed to the different SGS capacities to satisfy basic turbulent flow features that translate in different dissipative and turbulent diffusive contributions of the three SGS models.

Copyright © 2016 by ASME
Your Session has timed out. Please sign back in to continue.


Tucker, P. , 2011, “ Computation of Unsteady Turbomachinery Flows—Part 2: LES and Hybrids,” Prog. Aerosp. Sci., 47(7), pp. 546–569. [CrossRef]
Menzies, K. , 2009, “ Large Eddy Simulation Applications in Gas Turbines,” Philos. Trans. R. Soc., 367(1899), pp. 2827–2838. [CrossRef]
Collado-Morata, E. , Gourdain, N. , Duchaine, F. , and Gicquel, L. , 2012, “ Structured vs Unstructured LES for the Prediction of Free-Stream Turbulence Effects on the Heat Transfer of a High Pressure Turbine Profile,” J. Heat Mass Transfer, 55(21–222), pp. 5754–5768. [CrossRef]
Pope, S. B. , 2000, Turbulent Flows, Cambridge University Press, Cambridge, UK.
Chapman, D. , 1979, “ Computational Aerodynamics Development and Outlook,” AIAA J., 17(12), pp. 1293–1313. [CrossRef]
Michelassi, V. , Wissink, J. , Froehlich, J. , and Rodi, W. , 2003, “ Large Eddy Simulation of Flow Around Low-Pressure Turbine Blade With Incoming Wakes,” AIAA J., 41(11), pp. 2143–2156. [CrossRef]
Duchaine, F. , Maheu, N. , Moureau, V. , Balarac, G. , and Moreau, S. , 2013, “ Large-Eddy Simulation and Conjugate Heat Transfer Around a Low-Mach Turbine Blade,” ASME J. Turbomach., 136(5), p. 051015. [CrossRef]
Gourdain, N. , 2013, “ Validation of Large-Eddy Simulation for the Prediction of Compressible Flow in an Axial Compressible Stage,” ASME Paper No. GT2013-94550.
McMullan, W. , and Page, G. , 2012, “ Towards Large Eddy Simulation of Gas Turbine Compressors,” Prog. Aerosp. Sci., 52, pp. 30–47. [CrossRef]
Wang, G. , Papadogiannis, D. , Duchaine, F. , Gourdain, N. , and Gicquel, L. , 2013, “ Towards Massively Parallel Large Eddy Simulation of Turbine Stages,” ASME Paper No. GT2013-94852.
Wang, G. , Moreau, S. , Duchaine, F. , Gourdain, N. , and Gicquel, L. , 2013, “ LES of the MT1 HP Turbine Using Turbo AVBP,” 21st Annual Conference of the CFD Society of Canada, Sherbrooke, QC, Canada, May 6–9.
Wang, G. , Duchaine, F. , Papadogiannis, D. , Duran, I. , Moreau, S. , and Gicquel, L. , 2014, “ An Overset Grid Method for Large Eddy Simulation of Turbomachinery Stages,” J. Comput. Phys., 274, pp. 333–355. [CrossRef]
de Laborderie, J. , Moreau, S. , and Berry, A. , 2013, “ Compressor Stage Broadband Noise Prediction Using a Large-Eddy Simulation and Comparisons With a Cascade Response Model,” AIAA Paper No. 2013-2042.
Wang, G. , Moreau, S. , Duchaine, F. , de Laborderie, J. , and Gicquel, L. , 2014, “ LES Investigation of Aerodynamics Performance in an Axial Compressor Stage,” 22nd Annual Conference of the CFD Society of Canada, Toronto, Canada, June 1–4.
Beard, P. , Smith, A. , and Povey, T. , 2011, “ Experimental and Computational Fluid Dynamics Investigation of the Efficiency of an Unshrouded Transonic High Pressure Turbine,” J. Power Energy, 225(8), pp. 1166–1179. [CrossRef]
Salvadori, S. , Montomoli, F. , Martelli, F. , Adami, P. , Chana, K. , and Castillon, L. , 2011, “ Aerothermal Study of the Unsteady Flow Field in a Transonic Gas Turbine With Inlet Temperature Distortions,” ASME J. Turbomach., 133(3), p. 031030. [CrossRef]
Qureshi, I. , Smith, A. D. , and Povey, T. , 2012, “ HP Vane Aerodynamics and Heat Transfer in the Presence of Aggressive Inlet Swirl,” ASME J. Turbomach., 135(2), p. 021040. [CrossRef]
Simone, S. , Montomoli, F. , Martelli, F. , Chana, K. , Qureshi, I. , and Povey, T. , 2012, “ Analysis on the Effect of a Nonuniform Inlet Profile on Heat Transfer and Fluid Flow in Turbine Stages,” ASME J. Turbomach., 134(1), p. 011012. [CrossRef]
Sagaut, P. , 2002, Large Eddy Simulation for Incompressible Flows, Springer, Berlin.
Smagorinsky, J. , 1963, “ General Circulation Experiments With the Primitive Equations—I: The Basic Experiment,” Mon. Weather Rev., 91(3), pp. 99–164. [CrossRef]
Nicoud, F. , and Ducros, F. , 1999, “ Subgrid-Scale Modelling Based on the Square of the Velocity Gradient Tensor,” Flow, Turbul. Combust., 62(3), pp. 183–200. [CrossRef]
Nicoud, F. , Baya-Toda, H. , Cabrit, O. , Bose, S. , and Lee, J. , 2011, “ Using Singular Values to Build a Subgrid-Scale Model for Large Eddy Simulations,” Phys. Fluids, 23(8), p. 085106. [CrossRef]
Moind, P. , and Kim, J. , 1982, “ Numerical Investigation of Turbulent Channel Flow,” J. Fluid Mech., 118, pp. 341–377. [CrossRef]
Piomelli, U. , Zang, T. , Speziale, C. G. , and Hussaini, M. Y. , 1990, “ On the Large-Eddy Simulation of Transitional Wall-Bounded Flows,” Phys. Fluids, 2(2), pp. 257–265. [CrossRef]
Germano, M. , Piomelli, U. , Moin, P. , and Cabot, W. , 1991, “ A Dynamic Sub-Grid Scale Eddy Viscosity Model,” Phys. Fluids, A(3), pp. 1760–1765. [CrossRef]
Bocquet, S. , Sagaut, P. , and Jouhaud, J. , 2012, “ A Compressible Wall Model for Large Eddy Simulation With Application to Prediction of Aerothermal Quantities,” Phys. Fluids, 24(6), p. 065103. [CrossRef]
Hosseini, S. , Fruth, F. , Vogt, D. , and Gransson, T. , 2011, “ Effect of Scaling of a Blade Row Sectors on the Prediction of Aerodynamic Forcing in a Highly-Loaded Transonic Turbine Stage,” ASME Paper No. GT2011-45813.
Mayorca, M. , Andrade, J. D. , Vogt, D. , Martensson, H. , and Fransson, T. , 2010, “ Effect of Scaling of a Blade Row Sectors on the Prediction of Aerodynamic Forcing in a Highly-Loaded Transonic Turbine Stage,” ASME J. Turbomach., 133(2), p. 021013.
Schoenfeld, T. , and Rudgyard, M. , 1999, “ Steady and Unsteady Flow Simulations Using the Hybrid Flow Solver AVBP,” AIAA J., 37(11), pp. 1378–1385. [CrossRef]
Duchaine, F. , Jaure, S. , Poitou, D. , Quemerais, E. , Staffelbach, G. , Morel, T. , and Gicquel, L. , 2013, “ High Performance Conjugate Heat Transfer With the Openpalm Coupler,” V International Conference on Coupled Problems in Science and Engineering (COUPLED 2013), Ibiza, Spain, June 17–19.
Lax, P. , and Wendroff, B. , 1964, “ Difference Schemes for Hyperbolic Equations With High Order of Accuracy,” Commun. Pure Appl. Math., 17(3), pp. 381–398. [CrossRef]
Poinsot, T. , and Lele, S. , 1992, “ Boundary Conditions for Direct Simulations of Compressible Viscous Flows,” J. Comput. Phys., 101(1), pp. 104–129. [CrossRef]
Koupper, C. , Poinsot, T. , Gicquel, L. , and Duchaine, F. , 2013, “ On the Ability of Characteristic Boundary Conditions to Comply With Radial Equilibrium in Turbomachinery Simulations,” AIAA J., 52(12), pp. 2829–2839. [CrossRef]
Jaegle, F. , Cabrit, O. , Mendez, S. , and Poinsot, T. , 2010, “ Implementation Methods of Wall Functions in Cell-Vertex Numerical Solvers,” Flow, Turbul. Combust., 85(2), pp. 245–272. [CrossRef]
Haller, G. , 2005, “ An Objective Definition of a Vortex,” J. Fluid Mech., 525, pp. 1–26. [CrossRef]
You, D. , Wang, M. , Moin, P. , and Mittal, R. , 2007, “ Large-Eddy Simulation Analysis of Mechanisms for Viscous Losses in a Turbomachinery Tip-Clearance Flow,” J. Fluid Mech., 586, pp. 177–204. [CrossRef]
Adamczyk, J. , 1984, “ Model Equation for Simulating Flows in Multistage Turbomachinery,” ASME Paper No. 85-GT226.
Adamczyk, J. , 2000, “ Aerodynamic Analysis of Multi-Stage Turbomachinery Flows in Support of Aerodynamic Design,” ASME J. Turbomach., 122(2), pp. 189–217. [CrossRef]
Hussain, A. , and Reynolds, W. , 1970, “ The Mechanics of an Organized Wave in Turbulent Shear Flow,” J. Fluid Mech., 41(2), pp. 241–258. [CrossRef]


Grahic Jump Location
Fig. 4

Isentropic Mach number across the stator at 10% (a), 50% (b), and 90% (c) span

Grahic Jump Location
Fig. 5

Static pressure across the rotor blade

Grahic Jump Location
Fig. 1

Mesh view of the stator (a), rotor (b), and rotor tip (c) mesh

Grahic Jump Location
Fig. 2

Q criterion of an instantaneous LES solution within the turbine stage obtained for case 1: (a) boundary layer separation, (b) stator wake, (c) horseshoe vortex, (d) corner vortex, (e) tip vortex, and (f) rotor wake

Grahic Jump Location
Fig. 3

Q criterion of an instantaneous solution across the rotor obtained for case 1: C—horseshoe vortex; D—corner vortex; E—tip vortex; E1—induced vortex; E2—tip-separation vortex; and E3—induced vortex

Grahic Jump Location
Fig. 9

Instantaneous views of (||∇ρ||/ρ) at midspan (a)–(c) and FFT’s of the pressure signal for the identified probe (d)–(f) for case 1 (a) and (d), case 2 (b) and (e), and case 3 (c) and (f)

Grahic Jump Location
Fig. 6

Radial profiles for cases 1, 2, and 3 at the rotor exit: (a) near field and (b) far field

Grahic Jump Location
Fig. 7

Vorticity of the mean velocity field at the rotor exit (near field plane) for case 1 (a), case 2 (b), and case 3 (c)

Grahic Jump Location
Fig. 8

Total pressure field at the rotor exit (near field plane) for case 1 (a), case 2 (b), and case 3 (c)

Grahic Jump Location
Fig. 10

PSD of the temporal axial velocity signal of a probe in stator’s wake

Grahic Jump Location
Fig. 11

Radial profiles of the unsteady activity obtained at the rotor/stator interface for all the three LES and based on a triple decomposition using (a) the rotor-BPF (9.5 kHz) and (b) the stator-BPF (4.75 kHz)

Grahic Jump Location
Fig. 12

Radial profiles of the unsteady activity obtained at the exit of the rotor (near field plane in Fig. 6) for all the three LES and based on a triple decomposition using (a) the rotor-BPF (9.5 kHz) and (b) the stator-BPF (4.75 kHz)



Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In