Research Papers

Design Optimization of Casing Grooves Using Zipper Layer Meshing

[+] Author and Article Information
Ning Qin

e-mail: n.qin@sheffield.ac.uk

Yibin Wang

Department of Mechanical Engineering,
University of Sheffield,
Mappin Street,
Sheffield S1 3JD,
South Yorkshire, UK

Shahrokh Shahpar

CFD Methods,
Design System Engineering,
Rolls Royce plc.,
Derby DE24 8BJ,
Derbyshire, UK

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 6, 2012; final manuscript received February 28, 2013; published online September 26, 2013. Assoc. Editor: Aspi Wadia.

J. Turbomach 136(3), 031002 (Sep 26, 2013) (12 pages) Paper No: TURBO-12-1185; doi: 10.1115/1.4024650 History: Received September 06, 2012; Revised February 28, 2013

A new algorithm, named the zipper layer method, has been developed to link multiblock meshes for groove-casing optimization applications. Numerical results for a turbomachinery rotor flow case are included to demonstrate the solution behavior across the zipper layer mesh. By using this new meshing methodology, the optimization of the casing groove geometries in relation to stall margin and efficiency of a transonic rotor is conducted. Six grooves are parameterized by their independent depths and a width to gap ratio. An advanced response surface method based on the Sobol design of experiment (DoE) and the Kriging response surface model (RSM) are used for the optimization. A leave-one-out cross-validation (LOOCV) method is used to calculate the quality of the response surface metric. The final optimized groove configuration is obtained through an optimization cycle using the Rolls-Royce SOPHY (SOFT-PADRAM-HYDRA) software (Shahpar, S., 2005, “SOPHY: An Integrated CFD Based Automatic Design Optimisation System,” Report No. ISABE-2005-1086), which not only improves the stall margin (SM) of the rotor but also maintains its peak efficiency.

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Hembera, M., Kau, H.-P., and Johann, E., 2008, “Simulation of Casing Treatments of a Transonic Compressor Stage,” Int. J. Rotat. Mach., 2008, p. 657202. [CrossRef]
Osborn, W. M., Lewis, G. W., Jr., and Heidelberg, L. J., 1971, “Effect of Several Porous Casing Treatments on Stall Limit and on Overall Performance of an Axial-Flow Compressor Rotor,” NASA TN D-6537.
Inoue, M., Kuroumaru, M., and Fukuhara, M., 1986, “Behavior of Tip Leakage Flow Behind an Axial Compressor Rotor,” ASME J. Eng. Gas Turb. Power, 108, pp. 7–13. [CrossRef]
Inoue, M., and Kuroumaru, M., 1989, “Structure of Tip Clearance Flow in an Isolated Axial Compressor Rotor,” ASME J. Turbomach., I l l(3), pp. 250–256. [CrossRef]
McDougall, N. M., Cumpsty, N. A., and Hynes, T. P., 1990, “Stall Inception in Axial Compressors,” ASME J. Turbomach., 112, pp. 116–125. [CrossRef]
McDougall, N. M., 1990, “A Comparison Between the Design Point and Near Stall Performance of an Axial Compressor,” ASME J. Turbomach., 112, pp. 109–115. [CrossRef]
Stauter, R. C., 1993, “Measurement of the Three-Dimensional Tip Region Flow Field in an Axial Compressor,” ASME J. Turbomach., 115, pp. 468–476. [CrossRef]
Ameri, A. A., and Steinthorsson, E., 1995, “Prediction of Unshrouded Rotor Blade Tip Heat Transfer,” ASME International Gas Turbine and Aeroengine Congress & Exposition, Houston, June 5–8, ASME Paper No. 95-GT-142.
Adamczyk, J. J., Celestina, M. L., and Greitzer, E. M., 1993, “The Role of Tip Clearance in High-Speed Fan Stall,” ASME J. Turbomach., 115(1), pp. 28–38. [CrossRef]
Suder, K. L., and Celestina, M. L., 1996, “Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor,” ASME J. Turbomach., 118, pp. 218–229. [CrossRef]
Thompson, D. W., King, P. I., and Rabe, D. C., 1998, “Experimental Investigation of Stepped Tip Gap Effects on the Performance of a Transonic Axial Flow Compressor Rotor,” ASME J. Turbomach., 120, pp. 477–486. [CrossRef]
Shabbir, A., and Adamczyk, J. J., 2005, “Flow Mechanism for Stall Margin Improvement Due to Circumferential Casing Grooves on Axial Compressors,” ASME J. Turbomach., 127, pp. 708–717. [CrossRef]
Ito, Y., Watanabe, T., and Himeno, T., 2008, “Effects of Endwall Contouring on Flow Instability of Transonic Compressor,” Int. J. Gas Turb. Propul. Power Sys., 2(1), pp. 24–29.
Beheshti, B. H., Teixeria, J. A., Ghorbanian, K., and Farhanieh, B., 2004, “Parametric Study of Tip Clearance—Casing Treatment on Performance and Stability of a Transonic Axial Compressor,” ASME J. Turbomach., 126, pp. 527–535. [CrossRef]
Huang, X., Chen, H., Shi, K., and Fu, S., 2009, “CFD Investigation on Circumferential Grooves Casing Treatment of a Transonic Compressor,” XIX International Symposium on Air Breathing Engines (ISABE 2009), Montreal, Canada, September 7–11, Paper No. ISABE-2009-1185.
Chen, H., Huang, X., and Fu, S., 2006, “CFD Investigation on Stall Mechanisms and Casing Treatment of a Transonic Compressor,” 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Sacramento, CA, July 9–12, AIAA Paper No. 2006-4799. [CrossRef]
Choi, K.-J., Kim, J.-H., and Kim, K.-Y., 2010, “Design Optimization of Circumferential Casing Grooves for a Transonic Axial Compressor to Enhance Stall Margin,” Proceedings of ASME Turbo Expo 2010: Power for Land, Sea and Air, Glasgow, UK, June 14–18, ASME Paper No. GT2010-22396. [CrossRef]
Qin, N., Carnie, G., LeMoigne, A., LiuX., and Shahpar, S., 2009, “Buffer Layer Method for Linking Two Non-Matching Multi-Block Structured Grids,” 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, FL, January 5–8, AIAA Paper No. 2009-1361. [CrossRef]
Shahpar, S., 2005, “SOPHY: An Integrated CFD Based Automatic Design Optimisation System,” Report No. ISABE-2005-1086.
Sobol, I. M., 1979, “On the Systematic Search in a Hypercube,” SIAM J. Numer. Anal., 16, pp. 790–793. [CrossRef]
Forrester, A. I. J., Sobester, A., and Keane, A. J., 2008, Engineering Design Via Surrogate Modelling: A Practical Guide, Wiley, Chichester, UK.
Dunham, J., 1998, “CFD Validation for Propulsion System Component,” Paper No. AGARD-AR-355.
Shahpar, S., and Lapworth, L., 2003, “PADRAM: Parametric Design and Rapid Meshing System for Turbomachinery Optimisation,” ASME Paper No. GT2003-38698. [CrossRef]
Lapworth, L., 2004, “Hydra-CFD: A Framework of Collaborative CFD Development,” International Conference on Scientific and Engineering Computation, Singapore, June 30–July 2.
Shahpar, S., 2005, “Design of Experiments, Screening and Response Surface Modelling to Minimise the Design Cycle Time,” (Invited Lecture at VKI), von Karman Institute for Fluid Dynamics, Brussels, Belgium.
Shahpar, S., 2000, “A Comparative Study of Optimisation Methods for Aerodynamic Design of Turbomachinery Blades,” ASME Paper No. 2000-GT-523.
Reid, L., and Moore, R. D., 1978, “Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82,” NASA TP-1338.
Shahpar, S., Qin, N., Carnie, G., and Wang, Y., 2011, “A Turbomachine Comprising an Annular Casing and a Bladed Rotor,” GB Patent No. 1101811.6.


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Fig. 1

Blade geometry details extracted from AGARD report [22]

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Fig. 2

Outline of NASA Rotor 37 mesh generated in PADRAM with 2.5 mm radius fillet at root of blade

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Fig. 4

Zipper layer mesh for NASA Rotor 37 with five grooves

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Fig. 5

A cut-through the zipper layer mesh in the middle of the blade

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Fig. 6

Original structured multiblock mesh

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Fig. 7

Mesh in Fig. 6 with zipper layer and new mesh generated in PADRAM on the casing side

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Fig. 8

Comparison of the total pressure ratio

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Fig. 9

Comparison of the total pressure ratios along the span

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Fig. 10

Numerical versus experimental data for validation of Rotor 37 flow

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Fig. 11

Comparison of convergence histories at peak efficiency condition (a) MB structured mesh (b) zipper layer mesh

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Fig. 12

Entropy and tip leakage vortex

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Fig. 13

Comparison of static pressure at 98% span

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Fig. 15

(a) Four groove (and two zero height groove) configuration from LPtau DoE; (b) five groove (and one zero height groove) configuration from LPtau DoE; (c) (d) six-groove configuration from LPtau DoE

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Fig. 16

Comparison of CFD data for groove casing treatment for Rotor 37 when compared to mesh without groove casing treatment

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Fig. 17

Optimized groove configuration based on optimum results from optimizer SOFT

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Fig. 18

Convergence histories of Rotor 37 for (a) flow residual (b) inlet mass flow rate

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Fig. 19

Pressure distribution on blade surface at 99% span at the stall point of the structured MB mesh with zipper layer with groove position indicated by black vertical lines

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Fig. 20

Relative Mach number contour near blade tip for the rotor (a) without casing treatment and (b) with casing treatment

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Fig. 21

The spill forward region is indicated by the red circle for the rotor by means of entropy contours (a) without casing treatment and (b) with casing treatment

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Fig. 22

Tip leakage vortex path indicated via the stream lines emanating from the blade tip leading edge shown with entropy contours slices at varying axial position along the blade: (a) without grooves (b) with grooves

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Fig. 23

Mass averaged Rotor 37 profiles at stall point of structured MB mesh with zipper layer, at station 4, for (a) total pressure ratio (b) adiabatic efficiency




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