Research Papers

Scaling Three-Dimensional Low-Pressure Turbine Blades for Low-Speed Testing

[+] Author and Article Information
Matteo Giovannini

Department of Industrial Engineering,
University of Florence,
Via di S.Marta, 3,
Florence 50139, Italy
e-mail: matteo.giovannini@tgroup.unifi.it

Michele Marconcini, Filippo Rubechini, Andrea Arnone

Department of Industrial Engineering,
University of Florence,
Via di S.Marta, 3,
Florence 50139, Italy

Francesco Bertini

GE Avio,
Viale I Maggio, 56,
Rivalta di Torino (TO) 10040, Italy

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received January 8, 2016; final manuscript received March 18, 2016; published online May 10, 2016. Assoc. Editor: John Clark.

J. Turbomach 138(11), 111001 (May 10, 2016) (9 pages) Paper No: TURBO-16-1009; doi: 10.1115/1.4033259 History: Received January 08, 2016; Revised March 18, 2016

The present activity was carried out in the framework of the Clean Sky European Research Project ITURB (optimal high-lift turbine blade aeromechanical design), aimed at designing and validating a turbine blade for a geared open-rotor engine. A cold-flow, large-scale, low-speed (LS) rig was built in order to investigate and validate new design criteria, providing reliable and detailed results while containing costs. This paper presents the design of an LS stage and describes a general procedure that allows to scale three-dimensional (3D) blades for LS testing. The design of the stator row was aimed at matching the test-rig inlet conditions and at providing the proper inlet flow field to the blade row. The rotor row was redesigned in order to match the performance of the high-speed (HS) configuration, compensating for both the compressibility effects and different turbine flow paths. The proposed scaling procedure is based on the matching of the 3D blade loading distribution between the real engine environment and the LS facility one, which leads to a comparable behavior of the boundary layer and hence to comparable profile losses. To this end, the datum blade is parameterized, and a neural-network-based methodology is exploited to guide an optimization process based on 3D Reynolds-averaged Navier–Stokes (RANS) computations. The LS stage performance was investigated over a range of Reynolds numbers characteristic of modern low-pressure turbines (LPTs) by using a multi-equation, transition-sensitive, turbulence model. Some comparisons with experimental data available within the project finally proved the effectiveness of the proposed scaling procedure.

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ACARE, 2001, “ European Aeronautics: A Vision for 2020—Meeting Society’s Needs and Winning Global Leadership,” Advisory Council for Aeronautical Research in Europe, Report No. KI-34-01-827-EN-C.
Banieghbal, M. R. , Curtis, E. M. , Denton, J. D. , Hodson, H. P. , Huntsman, I. , Schulte, V. , Harvey, N. W. , and Steele, A. B. , 1995, “ Wake Passing in LP Turbine Blades,” AGARD Conference, Derby, UK, May 8–12, Technical Report No. AGARD-CP-571, pp. 23-1,23-12.
Howell, R. J. , Ramesh, O. N. , Hodson, H. P. , Harvey, N. W. , and Schulte, V. , 2001, “ High Lift and Aft-Loaded Profiles for Low-Pressure Turbines,” ASME J. Turbomach., 123(2), pp. 181–188. [CrossRef]
Howell, R. J. , Hodson, H. P. , Schulte, V. , Stieger, R. D. , Schiffer, H. P. , Haselbach, F. , and Harvey, N. W. , 2002, “ Boundary Layer Development in the BR710 and BR715 LP Turbines—The Implementation of High-Lift and Ultra-High-Lift Concepts,” ASME J. Turbomach., 124(3), pp. 385–392. [CrossRef]
Kyprianidis, G. K. , Grönstedt, T. , Ogaji, S. O. T. , Pilidis, P. , and Singh, R. , 2011, “ Assessment of Future Aero-Engine Designs With Intercooled and Intercooled Recuperated Cores,” ASME J. Eng. Gas Turbines Power, 133(1), p. 011701. [CrossRef]
Kurzke, J. , 2009, “ Fundamental Differences Between Conventional and Geared Turbofans,” ASME Paper No. GT2009-59745.
Wisler, D. C. , 1985, “ Loss Reduction in Axial Flow Compressors Through Low-Speed Model Testing,” ASME J. Eng. Gas Turbines Power, 107(2), pp. 354–363. [CrossRef]
Hodson, H. P. , and Dominy, R. G. , 1993, “ Advanced Methods for Cascade Testing, 3.1 Annular Cascades,” Technical Report AGARD-AG-328.
Houtermans, R. , Coton, T. , and Arts, T. , 2004, “ Aerodynamic Performance of a Very High Lift Low Pressure Turbine Blade With Emphasis on Separation Prediction,” ASME J. Turbomach., 126(3), pp. 406–413. [CrossRef]
Satta, F. , Simoni, D. , Ubaldi, M. , Zunino, P. , and Bertini, F. , 2009, “ Boundary Layer Development on a High-Lift LP Turbine Profile Under Passing-Wakes Conditions,” ASME Paper No. GT2009-59889.
Canepa, E. , Formosa, P. , Lengani, D. , Simoni, D. , Ubaldi, M. , and Zunino, P. , 2006, “ Influence of Aerodynamic Loading on Rotor-Stator Aerodynamic Interaction in a Two-Stage Low Pressure Research Turbine,” ASME J. Turbomach., 129(4), pp. 765–772. [CrossRef]
Glauert, H. , 1974, “ A Theory of Thin Aerofoils,” Aeronautical Research Committee, Reports and Memoranda No. 910.
Liepmann, H. W. , and Roshko, A. , 2001, Elements of Gasdynamics, Dover Publications, Mineola, NY.
Vera, M. , and Hodson, H. P. , 2002, “ Low-Speed Versus High-Speed Testing of LP Turbine Blade-Wake Interaction,” 16th Symposium on Measuring Techniques in Transonic and Supersonic Flows in Cascades and Turbomachines, Cambridge, UK, Sept. 23–24, Paper No. 7-2.
Marconcini, M. , Rubechini, F. , Pacciani, R. , Arnone, A. , and Bertini, F. , 2012, “ Redesign of High-Lift Low Pressure Turbine Airfoils for Low Speed Testing,” ASME J. Turbomach., 134(5), p. 051017. [CrossRef]
Arnone, A. , 1994, “ Viscous Analysis of Three-Dimensional Rotor Flow Using a Multigrid Method,” ASME J. Turbomach., 116(3), pp. 435–445. [CrossRef]
Arnone, A. , and Pacciani, R. , 1996, “ Rotor-Stator Interaction Analysis Using the Navier–Stokes Equations and a Multigrid Method,” ASME J. Turbomach., 118(4), pp. 679–689. [CrossRef]
Baldwin, B. S. , and Lomax, H. , 1978, “ Thin Layer Approximation and Algebraic Model for Separated Turbulent Flows,” AIAA Paper No. 78-257.
Spalart, P. R. , and Allmaras, S. R. , 1994, “ A One-Equation Turbulence Model for Aerodynamic Flows,” Rech. Aérosp., 1, pp. 5–21.
Wilcox, D. C. , 1998, Turbulence Modeling for CFD, 2nd ed., DCW Industries, La Cañada, CA.
Menter, F. R. , 1994, “ Two-Equations Eddy Viscosity Turbulence Models for Engineering Applications,” AIAA J., 32(8), pp. 1598–1605. [CrossRef]
Rung, T. , Lübcke, H. , Franke, M. , Xue, L. , Thiele, F. , and Fu, S. , 1999, “ Assessment of Explicit Algebraic Stress Models in Transonic Flows,” Engineering Turbulence Modelling and Experiments-4, W. Rodi and D. Laurence , eds., Elsevier, Amsterdam, The Netherlands, pp. 659–668.
Pacciani, R. , Marconcini, M. , Fadai-Ghotbi, A. , Lardeau, S. , and Leschziner, M. A. , 2011, “ Calculation of High-Lift Cascades in Low Pressure Turbine Conditions Using a Three-Equation Model,” ASME J. Turbomach., 133(3), p. 031016. [CrossRef]
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]
Pacciani, R. , Marconcini, M. , Arnone, A. , and Bertini, F. , 2014, “ Predicting High-Lift Low-Pressure Turbine Cascades Flow Using Transition-Sensitive Turbulence Closures,” ASME J. Turbomach., 136(5), p. 051007. [CrossRef]
Jameson, A. , 1991, “ Time Dependent Calculations Using Multigrid With Applications to Unsteady Flows Past Airfoils and Wings,” AIAA Paper No. 91-1596.
Curtis, E. M. , Hodson, H. P. , Banieghbal, M. R. , Denton, J. D. , Howell, R. J. , and Harvey, N. W. , 1997, “ Development of Blade Profiles for Low Pressure Turbine Applications,” ASME J. Turbomach., 119(3), pp. 531–538. [CrossRef]
Cichocki, A. , and Unbehauen, R. , 1994, Neural Networks for Optimization and Signal Processing, Wiley, New York.
Rubechini, F. , Schneider, A. , Arnone, A. , Cecchi, S. , and Malavasi, F. , 2012, “ A Redesign Strategy to Improve the Efficiency of a 17-Stage Steam Turbine,” ASME J. Turbomach., 134(3), p. 031021. [CrossRef]
Bellucci, J. , Rubechini, F. , Arnone, A. , Arcangeli, L. , Maceli, N. , and Dossena, V. , 2012, “ Optimization of a High-Pressure Steam Turbine Stage for a Wide Flow Coefficient Range,” ASME Paper No. GT2012-69529.
Rai, M. M. , 2002, “ Three-Dimensional Aerodynamic Design Using Artificial Neural Networks,” AIAA Paper No. 2002-0987.
Pianko, M. , and Wazelt, F. , 1982, “ Averaging Techniques in Non-Uniform Internal Flows,” Propulsion and Energetic Panel Working Group 14, Report No. AGARD-AR-182.
Infantino, D. , Satta, F. , Simoni, D. , Ubaldi, M. , Zunino, P. , and Bertini, F. , 2016, “ Experimental Analysis of the Aerodynamic Performance of an Innovative Low Pressure Turbine Rotor,” J. Therm. Sci., 25(1), pp. 22–31. [CrossRef]


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Fig. 1

HS (a) and LS (b) turbine flow path

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Fig. 2

Scaling procedure validation for the T106C cascade [15]. (a) Pressure coefficient distribution (Re2s = 1.6 × 105). (b) Kinetic energy loss coefficient as a function of streamwise distance Reynolds number.

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Fig. 3

Pressure coefficient distributions at HS and LS conditions: (a) 10% span, (b) 50% span, and (c) 90% span

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Fig. 4

Blade parameterization

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Fig. 5

LS rotor redesign: pressure coefficient distributions at midspan and near endwalls for the optimum of OPT-02 campaign: (a) 10% span, (b) 50% span, and (c) 90% span

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Fig. 7

Pressure coefficient distributions at different sections along the span for the LS blade. Local shape refinements allow to match HS distributions near endwalls (OPT-03 campaign results). (a) 10% span, (b) 50% span, and (c) 90% span.

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Fig. 8

LS blade geometry: (a) three-dimensional LS blade, (b) 30% span, (c) 50% span, and (d) 70% span

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Fig. 11

Spanwise distribution of the total pressure coefficient at stator inlet

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Fig. 10

Skin friction coefficient distribution for the HS and the LS blade for Re2s = 0.15 × 10−5 at rotor midspan

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Fig. 9

Kinetic energy loss coefficient for the HS and the LS blade as a function of the isentropic exit Reynolds number

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Fig. 14

Rotor pressure losses as a function of the exit Reynolds number

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Fig. 13

Pitchwise mass-averaged radial distributions of the relative flow angle at the rotor inlet and outlet

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Fig. 12

Pressure coefficient distributions for the LS rotor blade: Re2s = 0.8 × 105. (a) 25% span, (b) 50% span, and (c) 75% span.



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