Rolls-royce Corporation

John Slinger

Wilfred H Wilkinson

Anthony G Gale

Edwin Pateman

David W Barrett

Christopher M Robson

A gas turbine engine turbine blade () has cooling air holes () arranged in groups, the holes () in one group and which span that part of the leading edge () that spans the hottest part of the blade (), are more closely spaced than the remainder of the holes (), thereby ensuring the provision of the most cooling air, where it is most needed.

Cooled turbine blade

A blade or vane structure for a gas turbine engine comprises a hollow aerofoil member and a cooling air entry tube within the hollow aerofoil member, the aerofoil and the tube comprising a unitary cast structure. To make this structure it is proposed that a lost wax casting process should be utilized, with the internal cavities formed using ceramic cores formed with the aid of temporary, disposable pieces which define the space eventually occupied by the tube.

Method of making an aerofoil member for a gas turbine engine

A blade or vane structure for a gas turbine engine comprises a hollow aerofoil member and a cooling air entry tube within the hollow aerofoil member, the aerofoil member and the tube comprising a unitary cast structure. To make this structure it is proposed that a lost wax casting process should be utilized, with the internal cavities formed using ceramic cores formed with the aid of temporary, disposable pieces which define the space eventually occupied by the tube.

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Spondon, United Kingdom

John Slinger