Numerical simulation of turbine blade boundary layer and heat transfer and assessment of turbulence models
- Pennsylvania State Univ., University Park, PA (United States). Center for Gas Turbine and Power
The boundary layer development and convective heat transfer on transonic turbine nozzle vanes are investigated using a compressible Navier-Stokes code with three low-Reynolds-number {kappa}-{epsilon} models. The mean-flow and turbulence transport equations are integrated by a four-stage Runge-Kutta scheme. Numerical predictions are compared with the experimental data acquired at Allison Engine Company. An assessment of the performance of various turbulence models is carried out. The two modes of transition, bypass transition and separation-induced transition, are studied comparatively. Effects of blade surface pressure gradients, free-stream turbulence level, and Reynolds number on the blade boundary layer development, particularly transition onset, are examined. Predictions from a parabolic boundary layer code are included for comparison with those from the elliptic Navier-Stokes code. The present study indicates that the turbine external heat transfer, under real engine conditions, can be predicted well by the Navier-Stokes procedure with the low-Reynolds-number {kappa}-{epsilon} models employed.
- Sponsoring Organization:
- National Aeronautics and Space Administration, Washington, DC (United States); National Science Foundation, Washington, DC (United States)
- OSTI ID:
- 563935
- Journal Information:
- Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 4 Vol. 119; ISSN JOTUEI; ISSN 0889-504X
- Country of Publication:
- United States
- Language:
- English
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