0
Research Papers

A Technological Effect Modeling on Complex Turbomachinery Applications With an Overset Grid Numerical Method

[+] Author and Article Information
Lionel Castillon, Gilles Billonnet

ONERA—The French Aerospace Lab,
Meudon F-92190, France

Jacques Riou

Safran-SNECMA,
Villaroche 77550, France

Stéphanie Péron, Christophe Benoit

ONERA—The French Aerospace Lab,
Châtillon F-92320, France

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received December 6, 2013; final manuscript received July 7, 2014; published online July 29, 2014. Assoc. Editor: John Clark.

J. Turbomach 136(10), 101005 (Jul 29, 2014) (11 pages) Paper No: TURBO-13-1271; doi: 10.1115/1.4027997 History: Received December 06, 2013; Revised July 07, 2014

This paper presents an overview of numerical simulations performed at ONERA on turbomachinery configurations which include technological effects, such as tip clearance, hub disk leakage, circumferential and noncircumferential casing treatments (CTs), blade fillets, and cooling holes. An overset grid approach (Chimera technique) is used to simulate these geometrical effects with ONERA's structured computational fluid dynamics (CFD) solver elsA. Calculations performed on the different configurations enable to quantify the impact of these technological effects on the flow solution.

Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.

References

Lépine, J., 2003, “Fan and Low-Pressure Compressor Design: General Considerations Fan Aerodynamic Design Low-Pressure Compressor Aerodynamic Design,” Aero-Engine Design: A State of the Art (von Karman Lecture Series VKI LS 2003-06), von Karman Institute, Rhode-St-Genese, Belgium.
Rolls Royce, 1986, The Jet Engine, 4th ed., Rolls Royce, London, UK.
Heider, R., Duboue, J. M., Petot, B., Billonnet, G., and Couaillier, V., 1993, “Three-Dimensional Analysis of Turbine Rotor Flow Including Tip Clearance,” ASME Turbine and Aeroengine Congress and Exposition, Cincinnati, OH, May 24–27, ASME Paper No. 93-GT-111.
Inoue, M., and Furukawa, M., 2002, “Physics of Tip Clearance Flow in Turbomachinery,” ASME Joint U.S.-European Fluids Engineering Division Conference, Montreal, QC, Canada, July 14–18, ASME Paper No. FEDSM2002-31184. [CrossRef]
Inoue, M., Kuroumaru, M., and Furukawa, M., “Effect of Tip Clearance on Stall Evolution Process in a Low-Speed Axial Compressor Stage,” ASME Turbo Expo, Vienna, Austria, June 14–17, ASME Paper No. GT2004-53354. [CrossRef]
Shabbir, A., Celestina, M. L., Adamczyk, J. J., and Strazisar, A. J., 1997, “The Effect of Hub Leakage Flow on Two High Speed Axial Flow Compressor Rotors,” ASME Turbo Expo, Orlando, FL, June 2–5, ASME Paper No. 97-GT-346.
Paniagua, G., Dénos, R., and Almeida, S., 2004, “Effect of the Hub Endwall Cavity Flow-Field of a Transonic High Pressure Turbine,” ASME Turbo Expo, Vienna, Austria, June 14–17, pp. 1153–1163, ASME Paper No. GT2004-53458. [CrossRef]
Zess, G. A., and Thole, K. A., 2002, “Computational Design and Experimental Evaluation of Using a Leading Edge Fillet on a Gas Turbine Vane,” ASME J. Turbomach., 124(2), pp. 167–175. [CrossRef]
Pieringer, P., and Sanz, W., 2004, “Influence of the Fillet Between Blade and Casing on the Aerodynamic Performance of a Transonic Turbine Vane,” ASME Turbo Expo, Vienna, Austria, June 14–17, pp. 1045–1052, ASME Paper No. GT2004-53119. [CrossRef]
Shabbir, A., and Adamczyk, J. J., 2004, “Flow Mechanism for Stall Margin Improvement Due to Circumferential Casing Grooves on Axial Compressors,” ASME Turbo Expo, Vienna, Austria, June 14–17, pp. 557–569, ASME Paper No. GT2004-53903. [CrossRef]
Brignole, G., Danner, F., and Kau, H. P., 2008, “Time Resolved Simulation and Experimental Validation of the Flow in Axial Slot Casing Treatments for Transonic Axial Compressor,” ASME Turbo Expo, Berlin, Germany, June 9–13, pp. 363–374, ASME Paper No. GT2008-50593. [CrossRef]
Tartinville, B., and Hirsch, Ch., 2008, “Modeling of Film-Cooling for Turbine Blade Design,” ASME Turbo Expo, Berlin, Germany, June 9–13, pp. 2219–2228, ASME Paper No. GT2008-50316. [CrossRef]
Cambier, L., and Veuillot, J. P., 2008, “Status of the elsA CFD Software for Flow Simulation and Multidisciplinary Applications,” 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 7–10, AIAA Paper No. 2008-664. [CrossRef]
Cambier, L., and Gazaix, M., 2002, “elsA: An Efficient Object-Oriented Solution to CFD Complexity,” 40th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 14–17, AIAA Paper No. 2002-0108. [CrossRef]
Benoit, C., Jeanfaivre, G., and Canonne, E., 2005, “Synthesis of ONERA Chimera Method Developed in the Frame of CHANCE Program,” 31st European Rotorcraft Forum, Florence, Italy, September 13–15.
Jeanfaivre, G., Benoit, C., and Lepape, M. C., 2002, “Improvement of the Robustness of the Chimera Method,” 40th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 14–17, AIAA Paper No. 2002-3290. [CrossRef]
Benek, J. A., Steger, J. L., and Dougherty, F. C., 1983, “A Flexible Grid Embedding Technique With Application to the Euler Equations,” 6th Computational Fluid Dynamics Conference, Danvers, MA, July 13–15, AIAA Paper No. 83-1944. [CrossRef]
Benek, J. A., Steger, J. L., and Dougherty, F. C., 1983, “A Chimera Grid Scheme,” ASME Mini-Symposium on Advances in Grid Generation, Houston, TX, June 20–22.
Bonet, J., and Peraire, J., 1991, “An Alternating Digital Tree (ADT) Algorithm for 3D Geometric Searching and Intersection Problems,” Int. J. Numer. Methods Eng., 31(1), pp. 1–17. [CrossRef]
Schwarz, Th., 2000, “Development of a Wall Treatment for Navier–Stokes Computations Using Overset Grid Technique,” 26th European Rotorcraft Forum, The Hague, Netherlands, September 26–29.
Meakin, R. L., 2001, “Object X-Rays for Cutting Holes in Composite Overset Structured Grids,” 15th AIAA Computational Fluid Dynamics Conference, Anaheim, CA, June 11–14, AIAA Paper No. 2001-2537. [CrossRef]
Dunham, J., ed., 1998, “CFD Validation for Propulsion System Components,” Advisory Group for Aerospace Research & Development (AGARD), Neuilly-sur-Seine, France, Report No. AGARD-AR-355.
Strazisar, A. J., 1994, “Data Report and Data Diskette for NASA Transonic Compressor Rotor 37,” NASA Lewis Research Center, Cleveland, OH.
Gerolymos, G. A., Tsanga, G., and Vallet, I., 1998, “Near-Wall k-ε Computation of Transonic Turbomachinery Flows With Tip Clearance,” AIAA J., 36(10), pp. 1769–1777. [CrossRef]
Castillon, L., and Legras, G., 2013, “Overset Grid Method for Simulation of Compressors With Nonaxisymmetric Casing Treatment,” J. Propul. Power, 29(2), pp. 460–465. [CrossRef]
Legras, G., Trébinjac, I., Gourdain, N., Ottavy, X., and Castillon, L., 2012, “A Novel Approach to Evaluate the Benefits of Casing Treatment in Axial Compressors,” Int. J. Rotating Mach., 2012, p. 975407. [CrossRef]
Lin, F., Ning, F., and Liu, H., 2008, “Aerodynamics of Compressor Casing Treatment: Part I—Experiment and Time-Accurate Numerical Simulation,” ASME Turbo Expo, Berlin, Germany, June 9–13, pp. 731–744, ASME Paper No. GT2008-51541. [CrossRef]
Ning, F., and Xu, L., 2008, “Aerodynamics of Compressor Casing Treatment: Part II—A Quasy-Steady Model for Casing Treatment Flows,” ASME Turbo Expo, Berlin, Germany, June 9–13, pp. 745–756, ASME Paper No. GT2008-51542. [CrossRef]
Numeca, 2013, “Autogrid5: Automated Grid Generator for Turbomachinery,” version 9, Numeca international, Brussels, Belgium, http://www.numeca.com
Jonsson, M., and Ott, P., 2007, “Heat Transfer Experiments on a Heavily Film Cooled Nozzle Guide Vane,” 7th European Turbomachinery Conference, Athens, Greece, March 5–9, pp. 1011–1020.
Charbonnier, D., Ott, P., Jonsson, M., Köbke, Th., and Cottier, F., “Comparison of Numerical Investigations With Measured Heat Transfer Performance of a Film Cooled Turbine Vane,” ASME Turbo Expo, Berlin, Germany, June 9–13, pp. 571–582, ASME Paper No. GT2008-50623. [CrossRef]
Choi, D., 1993, “A Navier–Stokes Analysis of Film Cooling in a Turbine Blade,” 31st Aerospace Sciences Meeting & Exhibit, Reno, NV, January 11–14, AIAA Paper No. 93-158. [CrossRef]
Yamane, T., and Yamamoto, K., “Introduction of Combined Usage of Overset Grid Method in Conjugate Heat Transfer Simulation,” ASME Turbo Expo, Orlando, FL, June 8–12, pp. 737–746, ASME Paper No. GT2009-59832. [CrossRef]
Davis, R. L., Dannenhoffer, J. F., and Clark, J. P., 2011, “Conjugate Design/Analysis Procedure for Film-Cooled Turbine Airfoil Sections,” AIAA J. Propul. Power, 27(1), pp. 61–70. [CrossRef]
Davis, R. L., and Clark, J. P., 2013, “Geometry/Grid Generation for 3D Multi-Disciplinary Simulations in Multi-Stage Turbomachinery,” 43rd Fluid Dynamics Conference, San Diego, CA, June 24–27, AIAA Paper No. 13-2727. [CrossRef]
Paniagua, G., Yasa, T., de la Loma, A., and Castillon, L., 2008, “Unsteady Strong Shock Interactions in a Transonic Turbine: Experimental and Numerical Analysis,” J. Propul. Power, 24(4), pp. 722–731. [CrossRef]
Martegoutte, J., 2005, “Modélisation numérique des effets technologiques en turbomachines par la technique chimère du code elsA,” Rapport de stage de fin d’étude, ONERA, Châtillon, France.

Figures

Grahic Jump Location
Fig. 1

Meridian view of a compressor stage with technological effects [1]

Grahic Jump Location
Fig. 2

Cooled gas turbine stage (figure extracted from Ref. [2])

Grahic Jump Location
Fig. 3

Illustration of the Chimera approach on a jet in a cross flow configuration; (a) geometry to compute, (b) coincident matching grid, (c) Chimera overset grids, and (d) Chimera overset grids with buffer intermediate grid

Grahic Jump Location
Fig. 4

Detailed view of NASA 37 forward center body and rotor disk interface [22]

Grahic Jump Location
Fig. 5

View of the Chimera grids used for hub disk leakage simulation

Grahic Jump Location
Fig. 6

View of the relative Mach number in the interaction zone between the primary flow and the cavity jet

Grahic Jump Location
Fig. 7

Effect of hub disk leakage injection on the radial distribution of downstream pitchwise averaged total pressure and temperature

Grahic Jump Location
Fig. 8

Streamlines emanating from the cavity

Grahic Jump Location
Fig. 9

View of patch grid approach for tip leakage simulation

Grahic Jump Location
Fig. 10

Compression rate and isentropic efficiency as a function of the mass-flow

Grahic Jump Location
Fig. 11

Radial (95% span height) and axial slices of relative Mach number contour in the tip zone

Grahic Jump Location
Fig. 12

Meridian view of the grid used for the CTs configuration

Grahic Jump Location
Fig. 13

Impact of CTs on the compressor map

Grahic Jump Location
Fig. 14

Radial velocity at blade tip (red: Vr > 0, blue: Vr < 0)

Grahic Jump Location
Fig. 15

Cross-sectional view of the test section (left), and sketch of the slot type CT (Lin et al. [27])

Grahic Jump Location
Fig. 16

Left: BUAA overset grids. Right: snapshot of the radial velocity distribution near the casing.

Grahic Jump Location
Fig 17

Experimental and computed compressor maps

Grahic Jump Location
Fig. 18

View of the computational grid

Grahic Jump Location
Fig. 19

Impact of the blade fillet on the entropy distribution downstream of the rotor

Grahic Jump Location
Fig. 20

View of the vane geometry with cooling row locations

Grahic Jump Location
Fig. 21

View of the mesh in the cooling zone (black: grid of the channel, red: buffer grids, and blue: cooling hole grids). Top: 3D view, bottom: blade to blade view.

Grahic Jump Location
Fig. 22

Plane normal to the wall on suction side. Static temperature distribution. (a) No buffer grid, (b) buffer grid 1, and (c) buffer grid 2.

Grahic Jump Location
Fig. 23

Spanwise averaged heat transfer coefficients

Grahic Jump Location
Fig. 24

Comparison between Chimera approach and generalized boundary conditions

Grahic Jump Location
Fig. 25

Comparison of Chimera approach and boundary conditions (left—B.C., right—Chimera)

Tables

Errata

Discussions

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