Patent ID: 7198458

Claim:
A fail safe cooling system for a turbine vane, comprising: a turbine vane having an outer radial end, an inner radial end and an outer peripheral surface defining an outer vane profile; a first layer of cooling holes extending substantially radially between the inner radial end and the outer radial end of the vane, the first layer of cooling holes being arranged along at least a portion of the vane; a second layer of cooling holes extending substantially radially between the inner radial end and the outer radial end of the vane, the second layer of cooling holes being arranged along at least a portion of the vane, the second layer of cooling holes being in fluid communication with the first layer of cooling holes near one of the radial ends, wherein the second layer is closer to the outer peripheral surface than the first layer; and at least one radial coolant supply passage in the vane extending from the outer radial end toward the inner radial end, the coolant supply passage being spaced inward from the first layer of cooling holes, wherein the coolant supply passage is in fluid communication with the first layer of cooling holes, whereby a coolant can pass sequentially from the first layer to the second layer of cooling holes with the direction of coolant flow through the first layer being opposite to the direction of coolant flow through the second layer.