Patent ID: 9506351
Filing Date: 2016-11-29
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. A durable gas turbine vane, comprising: an inner band, an outer band, and at least one vane extending between the inner and outer bands; the at least one vane further comprising a leading edge, a trailing edge, a suction side and a pressure side; the suction side being disposed laterally opposite the pressure side; wherein the suction side and the pressure side extend between the leading edge to the trailing edge thereby defining a chord-wise airfoil shape for the at least one vane; the at least one vane being curved along an axial direction; the suction side including a blunter region and a high curvature region; the high curvature region spaced from said blunter region; the blunter region having at least two rows of linear cooling apertures; the cooling apertures being formed upon and extending into a surface of the blunter region; and, the apertures extending at an angle θ, wherein θ is within a range of from zero to 40 degrees with respect to the surface of the blunter region.