Aerodynamic Characteristics of Steam Turbine Prismatic Blade Section

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For the needs of high-performance steam turbines producer the data of a blade section measurement have been analyzed in detail using an experimental and numerical approach. The blade section is used on prismatic blades in high and medium pressure steam turbine parts. The linear blade cascade was tested at four pitch/chord ratios at two different stagger angles. The blade cascade was tested under two levels of Reynolds number in the range of output izentropic Mach numbers from 0.4 to 0.9.The inlet of the test section was measured pitch-wise by five-hole probe to determine the inlet flow angle. The free stream turbulence of inlet flow was determined at 2.5% what is very close to the operating conditions on first high pressure stages. Two-dimensional flow field at the center of the blades was traversed pitch-wise downstream the cascade by means of a five-hole needle pressure probe to find out the overall integral characteristics. The blade loading was measured throughout surface pressure taps at the blade center. An in-house code based on a system of Favre-averaged Navier-Stokes equation closed by non-linear two-equation EARSM k-ω turbulence model was adopted for the predictions. The code utilizes an algebraic model of bypass transition valid for both attached and separated flows taking into account the effect of free-stream turbulence and pressure gradient. Results are presented by integral characteristic in means of kinetic energy loss coefficient and velocity or pressure distribution in the blade wakes or on the blade surface. In this article, the effect of investigated criteria and comparison of experimental and numerical approach are presented and discussed.

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Periodical:

Edited by:

Cyril Fischer

Pages:

48-56

Citation:

T. Jelínek et al., "Aerodynamic Characteristics of Steam Turbine Prismatic Blade Section", Applied Mechanics and Materials, Vol. 821, pp. 48-56, 2016

Online since:

January 2016

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$38.00

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[1] Moustapha H., et al: Axial and Radial Turbines, Concept NREC, Vermont, (2003).

[2] Dixon, S.L.: Fluid Mechanics, Thermodynamics of Turbomachinery, Pergamon Press, Ltd., Oxford, (2005).

[3] Hellsten A.: New two-equation turbulence model for aerodynamics applications. Ph.D. thesis, Helsinki University of Technology, (2004).

[4] Straka P., Příhoda J.: Application of the algebraic bypass-tranzition model for internal and external flows. Proc. Conf. Experimental Fluid Mechanics, TU Liberec, pp.636-641, (2010).

[5] Straka P., Příhoda J., Šafařík P.: Prediction of boundary layer transition in transonic blade cascade with suden change of surface curvature. Proc. Conf. Application of Experimental and Numerical Methods in Fluid Mechanics and Energy, University of Žilina, pp.261-268, (2012).

[6] AIAA Standard: Assessment of Experimental Uncertainty with Application to Wind Tunnel Testing, AIAA, S-071A-1999, (1999).

DOI: https://doi.org/10.2514/4.473647.001

[7] Hellsten, A., New Two-Equation TurbulenceModel for Aerodynamics Applications, PhD Thesis., (2004).

[8] Narashima R., The laminar-turbulent transition zone in the boundary layer, Progress in Aerospace Science, vol. 22, pp.29-80, (1985).

DOI: https://doi.org/10.1016/0376-0421(85)90004-1

[9] Gostelov, J. P., Blunden, A. R., Walker, G. J.: Effect of free-stream turbulence and adverse pressure gradient on boundary layer transition, ASME Paper 92-GT-380, (1992).

[10] Solomon, W. J., Walker, G. J., Gostelov, P. J.: The laminar-turbulent transition zone in the boundary layer, Trans. ASME, Journal of Turbomachinery, vol. 118, pp.744-751, (1996).

[11] Mayle R. E.,: The Role of Laminar-Turbulent Transition in Gas Turbine Engines, vol. 113, pp.509-537, (1991).

[12] Ainley D.G., Matheieson G.C.R., A method of performance estimation of axial-flow turbines., Aero Res Council Reports and Memoranda 2974, (1951).

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