Turbine vane with near wall multiple impingement cooling

摘要

A turbine vane with a low flow near wall multiple impingement cooling circuit in which a thin thermal skin is bonded over a main support spar that together forms a series of chordwise extending collection and impingement chambers extending from the leading edge region to the trailing edge region of the airfoil. Cooling air from a cooling air supply cavity flows through feed holes and into a first one of the collection chambers located in the leading edge region, and then through impingement cooling holes for backside impingement cooling of the airfoil wall. the series of collection and impingement is repeated along the airfoil wall until the spent impingement air is discharged through exit holes on both sides of the trailing edge region.