Patent ID: 8641368
Filing Date: 2014-02-04
Classification: F01D,F05D

Abstract:
1. An industrial engine turbine rotor blade comprising: an airfoil extending from a platform and a root with a neck formed between the platform and the root; the airfoil having a pressure side wall and a suction side wall; a cooling air supply channel passing through the blade from the root to a blade tip; a bracket located under a pressure side of the platform and covering a section of an underside of the platform and a section of the pressure side of the neck; the bracket having a cooling air supply hole extending from the neck to the platform that connects to the cooling air supply channel and an impingement cavity formed under the platform; the cooling air supply hole within the bracket is directed to produce impingement cooling to an underside of the platform; and, a plurality of film cooling holes connected to the bracket impingement cavity and opening onto a surface of the platform on the pressure side.