Patent ID: 9334755
Filing Date: 2016-05-10
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. An airfoil component for a gas turbine engine comprising: an airfoil extending from a platform, the platform including a cooling passage defined by a surface, wherein the airfoil component is a turbine vane having an inner and an outer platform, wherein the turbine vane includes a pair of airfoils extending radially from the same inner platform, wherein the cooling passage is provided in the inner platform of the turbine vane, wherein the cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage, the first radially extending leg provides an inlet to the cooling passage, and the second radially extending leg is plugged; and chevron-shaped trip strips extending from the surface into the cooling passage at a trip strip height along a length, the trip strip height varying along the length, the circumferential passage including the trip strips, the trip strips arranged on either of opposing sides of the first radially extending leg with the chevron-shape on each of the opposing sides facing opposing directions.