Flow and Heat Transfer Prediction On Turbine Rotor Blade with Various Tip Configurations

Numerical study is performed to simulate the leakage flow and heat transfer on a flat tip, a double squealer tip and a single suction-side squealer tip of a scaled up GE-E3blade. Calculations were performed first for a stationary blade at a pressure ratio of 1.2 and compared with the available experimental data. The predicted heat transfer coefficients are in reasonable agreement with the experimental data on the blade tip and suction side, but the heat transfer coefficients were overpredicted on the pressure side. Numerical simulations were then performed for stationary and rotating blades under high temperature, high pressure ratio, and high Mach number conditions to investigate the blade tip heat transfer characteristics under more realistic engine operating conditions. A systematic comparison of various tip configurations were made to facilitate a more detailed understanding of the leakage flow structures around the blade tip. The simulation results show that the heat transfer coefficient decreases with increasing squealer cavity depth, but the shallow squealer cavity is the most effective configuration to reduce the heat load in the Made tip region. In general, rotation produced a somewhat stronger tip leakage flow and a slight increase of the area averaged Stanton number on the blade tip region. Copyright 2005 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Flow and Heat Transfer Prediction On Turbine Rotor Blade with Various Tip Configurations Conference Paper