| The continuing trend toward high gas turbine inlet temperature has resulted in a high heat load on turbine components. The blade tip is one of the most critical regions because of the high heat load and difficulty in cooling. Therefore, the detailed information of heat transfer coefficient and film cooling effectiveness is important. A hue detection based transient liquid crystal technique has been developed to measure the heat transfer coefficient on the blade tip and near tip regions of the blade. The heat transfer coefficient and film cooling effectiveness also were measured on the blade tip. Both the plane tip and squealer tip of the blade were considered. The pressure on the shroud was also measured and presented. The effects of the gap clearance, the shape of the tip, and the blowing ratio on the heat transfer coefficient and film cooling effectiveness were investigated. The heat transfer coefficients on the tip and the shroud surface increased as the tip gap clearance increased. The heat transfer coefficient on the cavity of the squealer tip is much lower than that on the plane tip surface. The film cooling effectiveness on the squealer tip is higher than that on the plane tip. |
