Study on the Numerical Model of Transonic Wind Tunnel Test Section
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https://doi.org/10.1007/s11630-020-1277-3
Article ID: 1003-2169(2020)00-0000-00
Study on the Numerical Model of Transonic Wind Tunnel Test Section LOUDA Petr1,2*, PŘÍHODA Jaromír1 1. Institute of Thermomechanics of the Czech Academy of Sciences, Prague 8 18200, Czech Republic 2. Faculty of Mechanical Engineering, Czech Technical University, Prague 2 12135, Czech Republic © Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2020
Abstract: The authors consider numerical simulations of transonic flows through various turbine cascades in a confined channel which approximates boundaries of real wind tunnel. The boundaries of the wind tunnel are impermeable or there can be permeable tailboards to diminish shock wave reflections. The mathematical model is based on Favre-averaged Navier-Stokes equations closed by a turbulence model and model of transition to turbulence. The mathematical model is solved by an implicit finite volume method with multi-block grids. Several types of turbine blade cascades with subsonic or supersonic inlet are presented. The results are compared with optical measurements and simulations of periodic cascades. The validity of experimental reference flow parameters in relation to computed flow patterns is discussed.
Keywords: perforated wall model, transonic wind tunnel, turbine blade cascade
1. Introduction The measurements of 2D model cascades in transonic wind tunnel serve as valuable tool for research and design for turbomachinery. Similarly the methods of general purpose computational fluid dynamics are used, usually to simulate flow through infinite cascade. The correspondence between measurement and these simulations is not trivial since flow regime parameters derived from measurements and used directly to formulate numerical boundary conditions often do not lead to the same flow fields. In a finite, experimental cascade, parasitic shear layers and expansion or shock waves can in some cases impair the periodicity of the flow field. Also, in cases with supersonic inlet velocities the inlet shock wave in front of the cascade is reflected from the upper tunnel wall, again causing disturbances in periodicity and changes of the inlet flow field [1]. To remedy the deficiencies in the experiment, some tunnel
Received: Apr 01, 2019
AE: HEUY Dong Kim
walls can be ventilated or perforated tailboards are applied behind lateral blades. At the same time, the numerical simulation taking into account these boundary effects is of interest, since it gives insight into the origin of various wave structures in the flow field and potentially can improve the counter measures in experimental setup and also the formulation of periodic simulations. In this work, the authors develop computational model of the high-speed wind tunnel facility of the Institute of Thermomechanics in Prague. The model is tested against series of measurements of mid-section and tip blade profiles of rotor row in the last stage of low pressure cylinder of large output
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