Patent ID: 7056093

Claim:
A gas turbine aerofoil of the type having at least one internal cavity for conveying cooling fluid through the aerofoil for cooling the aerofoil in use, the aerofoil comprising: at least one internal cavity adjacent the aerofoil leading edge; at least one impingement cooling passage extending from, and in flow communication with, the least one internal cavity; and at least one film cooling hole extending from, and in flow communication with, the at least one impingement cooling passage, wherein the at least one impingement cooling passage extends into the aerofoil wall in the region of the leading edge and opens into, and terminates in, the at least one film cooling hole, the at least one film cooling hole passes through the aerofoil wall from the pressure surface side to the suction surface side of the aerofoil at a position downstream of the leading edge such that, in use, cooling fluid from the at least one internal cavity exits the at least one impingement cooling passage into the at least one film cooling hole as an impingement jet against the internal surface of the at least one film cooling hole in the region of the leading edge and exits the at least one film cooling hole as a film on the external surface of the aerofoil downstream of the leading edge.