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ホーム アーカイブ 役員 今後の会合 American Society of Thermal and Fluids Engineering

NUMERICAL STUDY OF CONTOURED ENDWALL FLOW AND HEAT TRANSFER WITH COMBUSTOR COOLANT AND FILM COOLING FLOWS FOR A TURBINE NOZZLE GUIDE VANE

Mahmood H. Alqefl
University of Minnesota-Twin Cities, Minneapolis, MN, 55455, USA

Yong Kim
Solar Turbines Inc., San Diego, CA, 92186 USA

Hee-Koo Moon
Aero/Thermal & Heat Transfer, Solar Turbines, Inc., San Diego, California 92186-5376 USA

Luzeng Zhang
Solar Turbines Inc., San Diego, CA, 92186 USA

Terrence W. Simon
Department of Mechanical Engineering, University of Minnesota, 111 Church St. S.E., Minneapolis, Minnesota 55455, USA

DOI: 10.1615/TFEC2017.cfd.018417
pages 757-766

要約

High pressure gas turbine components require advanced cooling schemes to manage thermal loading. The complex nature of the flow in the vicinity of the hub endwall requires careful design for proper film cooling coverage. The secondary vortex flows wash coolant across and away from the endwall while enhancing mixing of endwall boundary layer flow with the mainstream. Therefore, strong understanding of aero-thermal interactions associated with secondary flows and film cooling flows is important to assist in developing better cooling methods. Results of a numerical study of a first stage nozzle guide vane with an axisymmetrically-contoured endwall are presented. The model is of a linear, two-passage cascade that matches the geometry of a previous experimental study. The cascade model includes a film cooling slot on the endwall upstream of the passage inlet. Steady Reynolds Averaged Navier Stokes (RANS) equations are employed for this study using the commercial software ANSYS Fluent. The inlet conditions are forced to match the measured approach flow conditions of the experiment, which include an inlet temperature profile simulating the effects of the combustor liner coolant. Results for temperature fields and endwall adiabatic effectiveness distributions are compared with the corresponding experimental data. It is found that, while overall flow features are captured by the numerical model, the over-dissipative nature of the RANS turbulence model inaccurately under-predicts the turbulent mixing of film coolant with the mainstream flow. This results in an over-prediction of coolant coverage over the endwall. The results document the effects of a common problem with RANS modeling in large-length-scale, highly-turbulent, turbomachinery passage flows.

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