The leading edge region of a first stage stator vane experiences high heat transfer rates especially near the endwall making it very important to get a better understanding of the formation of the leading edge vortex. In order to improve numerical predictions of the complex endwall flow, benchmark quality experimental data are required. To this purpose, this study documents the endwall heat transfer and static pressure coefficient distribution of a modern stator vane for two different exit Reynolds numbers (Reex = 6×105 and 1.2×106). In addition, laser Doppler velocimeter measurements of all three components of the mean and fluctuating velocities are presented for the stagnation plane in the leading edge region. Results indicate that the endwall heat transfer, pressure distribution and flowfield characteristics change with Reynolds number. The endwall pressure distributions show that lower pressure coefficients occur at the higher Reynolds number due to secondary flows. The stronger secondary flows cause enhanced heat transfer near the trailing edge of the vane at the higher Reynolds number. On the other hand the mean velocity, turbulent kinetic energy and vorticity results indicate that leading edge vortex is stronger and more turbulent at the lower Reynolds number. The Reynolds number also has an effect on the location of the separation point which moves closer to the stator vane at the lower Reynolds number.
|Original language||English (US)|
|Journal||American Society of Mechanical Engineers (Paper)|
|State||Published - Jan 1 1998|
|Event||Proceedings of the 1998 International Gas Turbine & Aeroengine Congress & Exhibition - Stockholm, Sweden|
Duration: Jun 2 1998 → Jun 5 1998
All Science Journal Classification (ASJC) codes
- Mechanical Engineering