Patent ID: 8202054
Filing Date: 2012-06-19
Classification: F01D,F05D

Abstract:
1. A blade for a gas turbine engine comprising: a main body comprising: an outer structure; a first internal partition, said outer structure and said first internal partition defining an entrance leg of a cooling circuit for receiving a cooling fluid; and a second internal partition including a metering slot extending to a lowermost portion of said outer structure, said first internal partition being located nearer to a leading edge than said second internal partition; wherein said outer structure, said first internal partition and said second internal partition defining an intermediate leg of said cooling circuit, said intermediate leg communicating with said entrance leg, and said second internal partition and said outer structure defining an exit leg of said cooling circuit that includes a substantial portion that is located adjacent to said intermediate leg, said metering slot formed between said intermediate leg and said exit leg and metering cooling fluid as it passes from said intermediate leg into said exit leg such that a pressure of the cooling fluid in said intermediate leg is greater than a pressure of the cooling fluid in said exit leg.