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TECHNICAL PAPERS: Power

Direct Constrained Computational Fluid Dynamics Based Optimization of Three-Dimensional Blading for the Exit Stage of a Large Power Steam Turbine

[+] Author and Article Information
P. Lampart

Institute of Fluid Flow Machinery, Polish Academy of Sciences, Gdansk, Polande-mail: lampart@imp.gda.pl

S. Yershov

Institute of Mechanical Engineering Problems, Ukrainian Academy of Sciences, Kharkov, Ukrainee-mail: yershov@ipmach.kharkov.ua

J. Eng. Gas Turbines Power 125(1), 385-390 (Dec 27, 2002) (6 pages) doi:10.1115/1.1520157 History: Received April 26, 2001; Revised May 22, 2002; Online December 27, 2002
Copyright © 2003 by ASME
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References

Harrison,  S., 1992, The Influence of Blade Lean on Turbine Losses, ASME J. Turbomach., 114, pp. 184–190.
Singh, G., Walker, P. J., and Haller, B. R, 1995, “Development of Three-Dimensional Stage Viscous Time Marching Method for Optimization of Short Height Stages,” Europ. Conf. on Turbomachinery, Fluid Dynamics and Thermodynamic Aspects, Erlangen, Germany, Mar. 1–3.
Denton, J. D., and Xu, L., 1999, “The Exploitation of 3D Flow in Turbomachinery Design,” VKI LS 1999-02.
Wang, Z., 1999, “Three-Dimensional Theory and Design Method of Bowed-Twisted Blade and Its Application to Turbomachines,” VKI LS 1999-02.
Lampart,  P., and Gardzilewicz,  A., 1999, “Numerical Study of 3D Blading in HP Impulse Turbines,” Int. Symp. SYMKOM’99, Arturówek-Łódź, Poland, Oct. 5–8, Cieplne Maszyny Przepływowe, 115, pp. 297–310.
Lampart, P., Gardzilewicz, A., Rusanov, A., and Yershov, S., 1999, “The Effect of Stator Blade Compound Lean and Twist on Flow Characteristics of a Turbine Stage—Numerical Study Based on 3D NS Simulations,” 2nd Symp. on Comp. Technologies for Fluid/Thermal/Chemical Systems With Industrial Applications, ASME, New York, PVP-Vol. 397.2, pp. 195–204.
Demeulenaere,  A., and Van Den Braembussche,  R., 1998, “Three-Dimensional Inverse Method for Turbomachinery Blading Design,” ASME J. Turbomach., 120, pp. 247–254.
Damle, S., Dang, T., Stringham, J., and Razinsky, E., 1998, “Practical Use of 3D Inverse Method for Compressor Blade Design,” ASME Paper No. 98-GT-115.
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Pierret, S., 1999, “Three-Dimensional Blade Design by Means of an Artificial Neural Network and Navier-Stokes Solver,” VKI LS 1999-02.
Shahpar, S., 2000, “A Comparative Study of Optimization Methods for Aerodynamic Design of Turbomachinery Blades,” ASME Paper No. 2000-GT-523.
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Yershov, S., and Rusanov, A., 1996, “The High Resolution Method of Godunov’s Type for 3D Viscous Flow Calculations,” Proc. 3 Colloq. Proc. Simulation, A. Jokilaakso, ed., Espoo, Finland, June 13–16, pp. 69–85.
Yershov, S., and Rusanov, A., 1996, “The Application Package FlowER for Calculation of 3D Viscous Flows Through Multi-stage Turbomachinery,” Certificate of Ukrainian state agency of copyright and related rights, Kiev, Ukraine, Feb. 19.
Yershov, S., Rusanov, A., Gardzilewicz, A., and Lampart, P., 1999, “Calculations of 3D Viscous Compressible Turbomachinery Flows,” 2nd Symp. on Comp. Technologies for Fluid/Thermal/Chemical Systems With Industrial Applications, ASME, New York, PVP-Vol. 397.2, pp. 143–154.
Yershov, S., Shapochka, A., and Rusanov, A., 2000, “Code Optimus,” Rep. Sci. Group FlowER, No. 2/2000.
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Figures

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Original geometry of the LP exit stage: meridional view (top left), circumferential view of stator leading and trailing edges (top right), and stator and rotor profiles (bottom)
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Final geometry with optimized straight and compound circumferential leans: meridional view (left), circumferential view of stator leading and trailing edges (right)
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Final geometry with optimized straight and compound axial sweeps: meridional view (left), circumferential view of stator leading and trailing edges (right)
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Spanwise circumferentially averaged distribution of stage reaction, stator loss, rotor loss, and stage loss with the exit energy in the exit stage for three mass flow rates: 38 kg/s (left), 56 kg/s (center), 75 kg/s (right) for the original stage (1), stage with circumferential leans (2), and stage with axial sweeps (3)
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Mach number contours in the stator 10% of the blade span from the root for the mass flow rate of 56 kg/s for the original stage (left) and stage with circumferential leans (right)
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Mach number contours in the rotor 10% of the blade span from the root for the mass flow rates of 56 kg/s (top) and 75 kg/s (bottom) for the original stage (left) and stage with circumferential leans (right)
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Enthalpy-entropy diagram for a turbine stage

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