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: There is disclosed a component (100,200) for a gas turbine engine (10). The component comprises first (23) and second (24) opposing aerodynamic surfaces with a trailing edge surface (36) therebetween. The trailing edge surface (36) forms a tapered trailing edge section (35) of the component. The trailing edge surface (36) is provided with one or more cooling openings (38) for ejecting a cooling fluid flow.

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 turbine disk (20) has a sealing plate (28) fixed to it by bayonet fixing features (36) and (40) formed in sealing plate flange (30) and disk flange (38). Abutments (42) and (44) are formed on the bayonet fixings, between which a multi part anti relative rotation locking member (46) is positioned in abutting relationship.

Abstract: A gas turbine engine flanged shaft (120) is provided with a plurality of anti-score plates (6a, 6b) each of which has two openings which are aligned with corresponding apertures on the flange. Bolts (4) pass through the openings and apertures to attach the anti-score plates (6a, 6b) to the flange (2). The anti-score plates (6a, 6b) have different masses to facilitate shaft balancing.

Abstract: A stress defender hole (18) in a component is provided with a countersunk portion (19). The countersunk portion (19) increases the stress concentration on to the defender hole (18), hence reducing stress elsewhere in the component.

Abstract: A gas turbine engine flanged shaft (120) is provided with a plurality of anti-score plates (6a, 6b) each of which has two openings which are aligned with corresponding apertures on the flange. Bolts (4) pass through the openings and apertures to attach the anti-score plates (6a, 6b) to the flange (2). The anti-score plates (6a, 6b) have different masses to facilitate shaft balancing.

Abstract: A locking device for use in retaining rotationally interengaged components in engagement with one another, the device comprising a body member (16) adapted to be located between adjacent interengaging formations (13, 14) on the components to prevent relative rotation of the components, and a wire retaining member (17) adapted to locate the body member in position, the retaining member comprising at least two hook-like members (18) engaged in spaced apertures (20) in the body member, each hook-like member having first and second portions (18B, 18C) extending beyond the body member into engagement with inner and outer surfaces of one of the components.