Patent ID: 8469666
Filing Date: 2013-06-25
Classification: F01D

Abstract:
1. A turbine blade for use in a gas turbine engine, the blade comprising: a tip region with a squealer pocket formed by pressure side and suction side tip rails; a squealer pocket floor; a plurality of trenches spaced along an edge of the pressure side tip rail and opening onto the pressure side tip rail; each trench being formed by a bottom wall and two side walls; each trench having an open front face on the pressure side wall and an open top face on a tip rail crown; each trench being separated from an adjacent trench; each trench being connected to an internal cooling passage of the blade through a metering hole that opens onto the bottom wall of the trench; each of the metering holes is curved in a direction of a tip squealer pocket; each of the trenches has a curved blade tip crown that is curved toward the inside of the squealer pocket; each of the metering holes opens into the trench at an angle of from around 10 to 30 degrees to the blade wall surface.