Heat-transfer coefficients of a turbine blade-tip and near-tip regions
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The detailed distribution of heat transfer coefficients on a gas turbine blade tip was measured using a hue detection based transient liquid crystals technique. The heat transfer coefficients on the shroud and near tip region of the pressure and suction sides of a blade were also measured. Tests were performed on a five-bladed linear cascade with a blow down facility. The blade was a 2-dimensional model of a first stage gas turbine rotor blade with a profile of GE-E3 aircraft gas turbine engine rotor blade. The Reynolds number based on the cascade exit velocity and axial chord length of a blade was 1.1106, and the total turning angle of the blade was 97.7. The overall pressure ratio was 1.23 and the inlet and exit Mach number were 0.25 and 0.59, respectively. The turbulence intensity level at the cascade inlet was 9.7%. The heat transfer measurements were made at the three different tip gap clearances of 1.0%, 1.5% and 2.5% of blade span. Results showed that, in general, the heat transfer coefficient on the tip was higher than that on the shroud and on the near tip region of the pressure and suction side. Results also showed that the heat transfer coefficients on the tip and the shroud increased as the tip gap clearance increased. But the heat transfer coefficients on the near tip region of the pressure and suction sides were not sensitive to the tip gap clearance. 2002 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
