Design Innovation Papers

Aerodynamic Optimization of High-Pressure Turbines for Lean-Burn Combustion System

[+] Author and Article Information
Shahrokh Shahpar

e-mail: Shahrokh.Shahpar@Rolls-Royce.com

Stefano Caloni

e-mail: Stefano.Caloni@Rolls-Royce.com
CFD Methods, Design System Engineering,
Rolls-Royce plc,
Derby DE24 8BJ, UK

Contributed by the Turbomachinery Committee of ASME for publication in the Journal of Engineering for Gas Turbines and Power. Manuscript received October 3, 2012; final manuscript received October 25, 2012; published online April 23, 2013. Editor: Dilip R. Ballal.

J. Eng. Gas Turbines Power 135(5), 055001 (Apr 23, 2013) (11 pages) Paper No: GTP-12-1388; doi: 10.1115/1.4007977 History: Received October 03, 2012; Revised October 25, 2012

Modern lean-burn combustors make use of high flow swirl to maintain flame stability. The swirling flow can persist downstream of the turbine first vane, changing the loading on the rotor, leading to a reduction in efficiency. This paper presents the results of an automatic optimization study carried out to mitigate the effect of high swirling flow on a high pressure turbine stage. A high-fidelity computational fluid dynamics (CFD)-based design optimization using a multipoint approximation (response surface) method is carried out to produce a new vane and a new rotor configuration with a significantly improved aerodynamic performance. It is demonstrated that the novel optimization methodology can cope well with a number of near equality constraints needed for a practical design.

Copyright © 2013 by ASME
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ACARE, 2001, European Aeronautics—A Vision for 2020, European Commission, Luxembourg.
Lazic, W., Doerr, T., Bake, S., Bank, R. V. D., and Rackwitz, L., 2008, “Development of Lean-Burn Low-NOx Combustion Technology at Rolls-Royce Deutschland,” Proc. of ASME Turbo Expo 2008, Berlin, Germany, June 9–13, ASME Paper No. GT2008-51115. [CrossRef]
Li, G., and Gutmark, E. J., 2004, “Effects of Swirler Configurations on Flow Structures and Combustion Characteristics,” ASME Paper No. GT2004-53674. [CrossRef]
Huang, Y., and Yang, V., 2005, “Effects of Swirl on Combustion Dynamics in a Lean-Premixed Swirl-Stabilized Combustor,” Proc. Combust. Inst., 30, pp. 1775–1782. [CrossRef]
Qureshi, I., Smith, A. D., and Povey, T., 2011, “HP Vane Aerodynamics and Heat Transfer in the Presence of Aggressive Swirl,” Proc. ASME IGTI Turbo Expo 2011, Vancouver, Canada, June 6–10, ASME Paper No. GT2011-46037. [CrossRef]
Qureshi, I., Smith, A. D., and Povey, T., 2011, “Effect of Aggressive Inlet Swirl on Heat Transfer and Aerodynamics in an Unshrouded Transonic HP Turbine,” Proc. ASME IGTI Turbo Expo 2011, Vancouver, Canada, June 6–10, ASME Paper No. GT2011-46038. [CrossRef]
Jouini, D. B. M., Sjolander, S. A., and Moustapha, S. H., 2001, “Aerodynamic Performance of a Transonic Turbine Cascade at Off-Design Conditions,” ASME J. Turbomach., 123, pp. 510–518. [CrossRef]
Corriveau, D., and Sjolander, S. A., 2004, “Influence of Loading Distribution on the Performance of Transonic High Pressure Turbine Blades,” ASME J. Turbomach., 126, pp. 288–296. [CrossRef]
Corriveau, D., and Sjolander, S. A., 2007, “Influence of Loading Distribution on the Off-Design Performance of High Pressure Turbine Blades,” ASME J. Turbomach., 129, pp. 563–571. [CrossRef]
Krishnamoorthy, V., and Sukhatme, S. P., 1989, “The Effect of Freestream Turbulence on Gas Turbine Blade Heat Transfer,” ASME J. Turbomach., 111, pp. 497–501. [CrossRef]
Hilditch, M. A., Fowler, A., Jones, T. V., Chana, K. S., Oldfield, M. L. G., Ainsworth, R. W., Hogg, S. I., Anderson, S. J., and Smith, G. C., 1994, “Installation of a Turbine Stage in the Pyestock Isentropic Light Piston Facility,” ASME Paper No. 94-GT-277.
Shahpar, S., and Lapworth, L., 2003, “PADRAM: Parametric Design and Rapid Meshing System for Turbomachinery Optimisation,” ASME Turbo Expo, Atlanta, GA, June 16–19, ASME Paper No. GT2003-38698. [CrossRef]
Shahpar, S., 2005, “SOPHY: An Integrated CFD Based Automatic Design Optimisation System,” Paper No. ISABE-2005-1086.
Shahpar, S., 2007, “Towards Robust CFD Based Design Optimisation of Virtual Engine,” NATO RTO–AVT-147, Athens, Greece.
Lapworth, L., 2004, “Hydra-CFD: A Framework for Collaborative CFD Development,” International Conference on Scientific and Engineering Computation (IC-SEC), Singapore, June 30–July 2.
Shahpar, S., 2002, “SOFT: A New Design and Optimisation Tool for Turbomachinery,” Evolutionary Methods for Design, Optimisation and Control, K. C.Ginnakoglou, D. T.Tsahalis, J.Periaux, and T.Fogarty, eds., CIMNE, Barcelona, Spain.
Polynkin, A., Toropov, V., and Shahpar, S., 2008, “Adaptive and Parallel Capabilities in the Multipoint Approximation Method,” 12th AIAA-ISSMO MDO Conference, Victoria, British Columbia, Canada, September 10–12, Paper No. AIAA-2008-5803. [CrossRef]
Polynkin, A., Toropov, V., and Shahpar, S., 2010, “Multidisciplinary Optimization of Turbomachinery Based on Metamodel Built by Genetic Programming,” Proceedings of the 13th AIAA/ISMO Multidisciplinary Analysis and Optimization Conference, Fort Worth, TX, September 13–15. [CrossRef]
Shahpar, S., 2005, “Automatic Aerodynamic Design Optimisation of Turbomchinery Components—An Industrial Prospective,” Invited Lecture at VKI Lecture Series, Belgium.
Shahpar, S., 2010, “Optimisation Strategies Used in Turbomachinery Design,” VKI Lecture Series, Introduction to Optimization Methods and Tools for Multidisciplinary Design in Aeronautics and Turbomachinery, June.
Okui, H., Verstraete, T., Van Den Braembussche, R. A., and Alsalihi, A., 2011, “Three Dimensional Design and Optimization of a Transonic Rotor in Axial Flow Compressors,” ASME Paper No. GT2011-45425. [CrossRef]
Aulich, M., and Siller, U., 2011, “High-Dimensional Constrained Multi-objective Optimization of a Fan Stage,” ASME Paper No. GT2011-45618. [CrossRef]
Arabnia, M., Sivashanmugam, V. K., and Wahid Ghaly, W., 2011, “Optimization of an Axial Turbine Rotor for High Aerodynamic Inlet Blockage,” ASME Paper No. GT2011-46757. [CrossRef]
Shahpar, S., 2010, “High Fidelity Multi-Stage Design Optimisation of Multi-Stage Turbine Blades Using a Mid-Range Approximation Method,” 13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference, Fort Worth, TX, September 13–15, Paper No. AIAA-2010-9367. [CrossRef]
Denton, J. D., and Xu, L., 2002, “The Effects of Lean and Sweep on Transonic Fan Performance,” ASME Paper No. GT2002-30327. [CrossRef]


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Fig. 1

Optimization loop using the SOPHY system

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Fig. 2

Schematic of zooming of trust regions in MAM

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Fig. 3

SILOET turbine stage geometry (ST1)

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Fig. 4

PADRAM multiblock mesh for the (a) NGV and (b) rotor, (c) detailed close-up of the NGV trailing edge and (d) rotor TE

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Fig. 5

PADRAM high stagger mesh topology

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Fig. 6

Vane and rotor radial positions where the design modifications are applied

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Fig. 7

Skew parameter effect on the blade geometry, radial distribution of the design parameter (on the left), original shape (in the middle), the modified shape (on the right)

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Fig. 8

Sweep applied to the vane geometry

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Fig. 9

Lean applied to the vane geometry

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Fig. 10

PADRAM recambering at the LE and TE

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Fig. 11

Film cooling rows and TE coolant slot on the original and the modified blade

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Fig. 12

Gas turbine engine scheme

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Fig. 13

SILOET inlet boundary conditions—vane LE positions shown by dash lines

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Fig. 14

Streamlines for uniform condition (on the left) and with swirl boundary condition (on the right)

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Fig. 15

Loading of NGVs with uniform and swirl inlet conditions

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Fig. 16

The MAM optimization history—no Hydra-PADRAM failure in the whole optimization

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Fig. 17

Optimum NGV shape superimposed on the datum

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Fig. 18

Static pressure distributions for the datum and optimum vane sections

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Fig. 19

Radial distribution of the axial and tangential velocities at the vane exit plane

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Fig. 20

Contours of axial velocity (datum design on the left, optimum on the right)

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Fig. 21

CPL difference between baseline and optimum

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Fig. 22

Shape of the optimized rotor, LE and TE views

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Fig. 23

Static pressure distributions for the datum and optimum rotor blade sections

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Fig. 24

Entropy contour at 95% span of rotor blade (datum is shown on left, optimized blade on the right)



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