Patent ID: 8985940
Filing Date: 2015-03-24
Classification: F01D

Abstract:
1. A turbine blade for a gas turbine engine, comprising: at least one internal cooling path; and a first vane disposed at a first location in the at least one internal cooling path; and a second vane disposed at a second location in the at least one internal cooling path downstream from the first location; wherein each of the first vane and the second vane includes: a central portion; a first leg extending in a first direction from the central portion; and a second leg extending in a second direction from the central portion, wherein the central portion has a thickness greater than a thickness of the first leg or a thickness of the second leg, wherein the first vane is disposed adjacent a first corner of a wall forming the at least one internal cooling path, and the second vane is disposed adjacent a second corner of the wall forming the at least one internal cooling path, wherein a cross-sectional area of the first vane is greatest at a portion of the first vane closest to the first corner of the wall, and wherein a cross-sectional area of the second vane is greatest at a portion of the second vane closest to the second corner of the wall.