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Influence of non-uniform admission on the work of the first group of stages

100%

Krzyślak P. , Flaszyński P.

1999

tom nr 115

251--258

The paper present results of the 3D flow calculations over a delivery channel domain of the turbine working with throttle governing. Based on the results, especially, the strong non-uniform mass flow rate distribution at the outlet plane of calculated channel, it was made an analysis of flow conditions and the mass flow distribution in blade passages of the first group of turbine stages.

Numerical simulation of 3D flow through a control valve

100%

Badur J. , Banaszkiewicz M. , Karcz M. , Winowiecki M.

1999

tom nr 115

31--36

The paper deals with numerical calculations of 3D flow through a control valve. The presented calculations were performed using commercial code FLUENT/UNS. The results of numerical simulations were compared with experimental data.

Experimental and computational studies of stall on a helicopter rotor airfoil

88%

Surmacz K.

tom Vol. 23, No. 3

511--517

In the case of forward flight of a helicopter, the flow field around rotating blades of a rotor is highly threedimensional and very complex. Helicopter blades work across a wide range of angles of attack and airspeed. The stall occurs on the retreating blade in forward flight and causes dissymmetry of lift on a rotor disc. The investigation of the stall phenomenon has been performed using experimental and computational methods. Experimental analysis was made at the Ohio State University 6’’x 22’’ unsteady transonic wind tunnel. Research in the wind tunnel was performed using two methods: oil visualization (over a wide range of alpha and Ma) and pressure measurements. Computational part of the research has been done using Computational Fluid Dynamics tool. 2- and 3-dimensional calculations performed using ANSYS FLUENT software. In both experimental and computational cases, the 3D flow around a section of a rotor blade based on the SSC-A09 airfoil was analysed. The test article of the research was a section, which was located in the tip region of the main rotor blade of UH-60M Black Hawk helicopter. The research was conducted for a wide range of angles of attack and at several velocities. The most interesting part of the analysis concerned on unsteady flow conditions corresponding to stall.

Numerical simulation of 3D flow in axial turbomachines

63%

Yershov S. , Rusanov A. V. , Gardzielewicz A. , Lampart P. , Świrdyczuk J.

TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk

1998

tom Vol. 2, No 2

319-347

The paper is intended to describe a method for the calculation of 3D viscous compressible (subsonic or supersonic) flow in axial turbomachines described in the form of thin-layer Reynolds-averaged Navier-Stokes equations. The method draws on Godunov-type upwind differencing and ENO reconstruction suggested by Harten (1987), so as to assure monotonicity preservation and high accuracy of computational results. The computational efficiency is achieved thanks to the implementation of a simplified H-type multi-grid approach and delta -form implicit step. Turbulent effects are simulated with the help of a modified algebraic model of Baldwin-Lomax (1978). This method was at the foundation of a computer code-a complex software package to calculate 3D flow in multi-stage turbomachines that allows us to obtain local characteristics, like temperature, pressure, density or velocity distributions, as well as global characteristics, such as flow rates, stage reaction, flow efficiency for the considered turbine/compressor stage. The paper also gives selected results of computation of a number of turbomachinery cascades, showing that these results agree reasonably well with the available experimental data.