Abstract: A method of CT scanning a plurality of aerofoil blades. The method includes the steps of: providing a rotatable support arranged for rotation about an axis of rotation and within an energy beam; mounting a plurality of aerofoil blades to the support in spaced-apart relationship to one another so as to form at least one array around the axis of rotation; and rotating the support about the axis within the beam. Each blade has an aerofoil section and is mounted to the support such that the span of its aerofoil section is substantially parallel to the axis of rotation, and the blades are arranged such that no line orthogonal to the axis of rotation intersects the aerofoil section of more than one blade.

Abstract: A method of CT scanning a plurality of aerofoil blades that includes providing a rotatable support arranged for rotation about an axis of rotation and within an energy beam; mounting a plurality of aerofoil blades to the support in spaced-apart relationship to one another to form at least one array around the axis of rotation; and rotating the support about the axis within the beam. Each blade has an aerofoil section and is mounted to the support. The method also provides an elongate identification element on the rotatable support, the identification element being arranged such that its longitudinal axis is parallel to the axis of rotation and having a transverse cross-sectional shape along at least part of its. Each edge feature corresponds to and is directed towards a respective said blade to thereby facilitate identification of individual the blades in a CT output obtained via the method.

Abstract: A method for designing a baffle including using patterns to produce an array of shell moulds, generating a 3-D image of the outer surface of each shell mould in the array of shell moulds, stacking the individual 3-D images for a plurality of the shell moulds to produce a conglomerate shell mould profile, determining a maximum cross sectional area of the conglomerate shell mould profile in a plane orthogonal to a direction along which the shell moulds are to be drawn through the baffle, defining a baffle profile segment which is consistent with a substantial portion of the conglomerate shell mould profile at the maximum cross sectional area, scaling the baffle profile segment to provide an offset clearance between the baffle profile segment and the maximum cross sectional area of the conglomerate shell mould profile, and reproducing the baffle profile segment to provide an array of baffle profile segments.

Abstract: A method for sentencing a manufactured component as a pass or fail is described. The method involves zoning a two-dimensional image of the component, weighting individual zones according to their importance in the load bearing function and comparing overall weighted dimensions against those of a pre-defined compliant component design. By considering the internal and external dimensions and offsetting variations between zones, a more accurate assessment of compliance can be achieved. It is envisaged that components which might otherwise have been rejected and scrapped may be accepted resulting in material and cost savings.

Abstract: A method for designing a baffle including using patterns to produce an array of shell moulds, generating a 3-D image of the outer surface of each shell mould in the array of shell moulds, stacking the individual 3-D images for a plurality of the shell moulds to produce a conglomerate shell mould profile, determining a maximum cross sectional area of the conglomerate shell mould profile in a plane orthogonal to a direction along which the shell moulds are to be drawn through the baffle, defining a baffle profile segment which is consistent with a substantial portion of the conglomerate shell mould profile at the maximum cross sectional area, scaling the baffle profile segment to provide an offset clearance between the baffle profile segment and the maximum cross sectional area of the conglomerate shell mould profile, and reproducing the baffle profile segment to provide an array of baffle profile segments.

Abstract: A method for sentencing a manufactured component as a pass or fail is described. The method involves zoning a two-dimensional image of the component, weighting individual zones according to their importance in the load bearing function and comparing overall weighted dimensions against those of a pre-defined compliant component design. By considering the internal and external dimensions and offsetting variations between zones, a more accurate assessment of compliance can be achieved. It is envisaged that components which might otherwise have been rejected and scrapped may be accepted resulting in material and cost savings.

Abstract: A method of CT scanning a plurality of aerofoil blades that includes providing a rotatable support arranged for rotation about an axis of rotation and within an energy beam; mounting a plurality of aerofoil blades to the support in spaced-apart relationship to one another to form at least one array around the axis of rotation; and rotating the support about the axis within the beam. Each blade has an aerofoil section and is mounted to the support. The method also provides an elongate identification element on the rotatable support, the identification element being arranged such that its longitudinal axis is parallel to the axis of rotation and having a transverse cross-sectional shape along at least part of its. Each edge feature corresponds to and is directed towards a respective said blade to thereby facilitate identification of individual the blades in a CT output obtained via the method.

Abstract: A method of CT scanning a plurality of aerofoil blades. The method includes the steps of: providing a rotatable support arranged for rotation about an axis of rotation and within an energy beam; mounting a plurality of aerofoil blades to the support in spaced-apart relationship to one another so as to form at least one array around the axis of rotation; and rotating the support about the axis within the beam. Each blade has an aerofoil section and is mounted to the support such that the span of its aerofoil section is substantially parallel to the axis of rotation, and the blades are arranged such that no line orthogonal to the axis of rotation intersects the aerofoil section of more than one blade.