Patent ID: 7946816
Filing Date: 2011-05-24
Classification: F01D,F05D,Y02T

Abstract:
1. A turbine blade, comprising: an airfoil; and a tip shroud that is defined at one end of the turbine blade adjacent to the airfoil, the tip shroud having one or more hollow spaces defined therein; wherein all of the hollow spaces defined within the tip shroud are in fluid communication with each other and define a cooling cavity; wherein the airfoil includes a coolant passage defined therein, the coolant passage extending through the airfoil such that the coolant passage is in fluid communication with the cooling cavity; wherein the cooling cavity comprises a plurality of ribs formed therein, the ribs being sized and configured such that some of the ribs extend a partial way across the distance across the cooling cavity; wherein the cooling cavity comprises a pressure side cooling cavity, a suction side cooling cavity, and a coolant chamber, the coolant chamber comprising a chamber that resides substantially between the pressure side cooling cavity and the suction side cooling cavity; wherein the coolant chamber is in fluid communication with the coolant passage; and wherein the coolant chamber is in fluid communication with the pressure side cooling cavity and a suction side cooling cavity via a plurality of coolant chamber apertures.