Rolls-royce Corporation

Brian G Cooper

David Stroud

Arthur G Corfe

Jonathan P Towill

Sean Alan Walters

Kevin Paul Self

Caner Hasan Helvaci

Jonathan G Bird

A computer-based method of designing a guide vane formation is provided. The vane formation is for use in a gas turbine engine which has a cascade of circumferentially arranged identical guide vane formations. The vane formation has radially inner and radially outer chordal seals. The method allows the elimination of 'saw-tooth' leakage gaps between inner chordal seals of neighboring vane formations and between outer chordal seals of neighboring vane formations even when the inner and outer chordal seals are axially offset from each other.

Method of designing guide vane formations

An air-cooled component such as a turbine stator vane, has a row of cooling passages extending from the interior of the vane to the exterior. The passages are inclined to a plane perpendicular to the row. The angle of inclination of each passage varies with the position of the passage along the row. The arrangement assists in avoiding local overheating of the vane surface.

Air-cooled component

A vane assembly for a gas turbine engine, the vane assembly comprising an aerodynamic main body across which gas can flow in streamlines, the main body defining a chamber and a plurality of cooling apertures extending through the main body, the cooling apertures being arranged in a plurality of arrays, wherein the vane assembly is arrangeable so that each array is generally parallel to the streamlines, and the vane assembly further including a baffle arrangement provided in the chamber the baffle arrangement having a gas deflection surface which extends across a plurality of the arrays.

Vane apparatus for a gas turbine engine

A gas turbine engine is provided with turbine stators which have hollow aerofoils. The aerofoils are internally cooled by a flow of air the path of which is defined by walls. The wall has a curved deflector at its outer end which causes air to flow over the wall end and down the other side of the wall. An extension member ensures that the air does not break away from the surface of the wall and is preferably made from sheet metal so as to provide a light, easily made structure.

Cooling air cooled gas turbine aerofoil

The present invention relates to cooled gas turbine engine aerofoils particularly for turbine stator vanes or tubine rotor blades. The leading edge region of a hollow aerofoil is provided with rows of cooling air passages, which are arranged, in operation, to direct cooling air in the opposite direction to the local flow of the hot gas stream. The cooling air passages are substantially parallel, and have relatively large diameters to reduce the possibility of blockage of the cooling air passages by sand. An air guide tube in the hollow aerofoil is provided with large apertures at its leading edge to minimize the area for sand to adhere to.

Cooled gas turbine engine aerofoil

A variety of configurations for convergent-divergent film cooling holes are disclosed, together with the hole drilling methods necessary to achieve the configurations.

Film cooled components

A gas turbine engine turbine aerofoil blade includes an aerofoil portion having pressure and suction flanks. The flanks are internally interconnected by wall member which cooperates with the flanks to define first and second cooling passage portions which are interconnected by a bend portion. The wall member is locally thickened adjacent the bend portion. In the second cooling passage portion the locally thickened wall member portion progressively increases in thickness towards at least one of the flanks so as to eliminate any acute angle between the flanks and the thickened wall member portion adjacent thereto.

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Derby, United Kingdom

Brian G Cooper