Patent ID: 8043058
Filing Date: 2011-10-25
Classification: F01D

Abstract:
1. A turbine blade for use in a gas turbine engine, the blade comprising: A blade tip having a single tip rail on the suction side of the blade tip and no tip rail on the pressure side of the tip; A tip floor extending from a front corner of the blade tip to the suction side tip rail; A cooling supply cavity formed between a pressure side wall and a suction side wall of the blade; A first diffusion cooling hole connected to the cooling supply cavity and opening onto the pressure side wall just below the tip corner, the opening oriented to discharge a first layer of film cooling air upward toward the tip corner; and, A second diffusion cooling hole connected to the cooling supply cavity and opening onto the tip corner on the tip floor side of the tip corner, the second diffusion cooling hole being curved toward the tip rail so as to discharge a second layer of film cooling air onto a surface of the tip floor not covered by the first layer of film cooling air.