Abstract: A vane for a gas turbine engine, the vane including a platform with an airfoil extending radially from the upper surface of the platform. The platform includes a joint portion which includes a circumferentially extending flange and a recessed surface both formed on either the upper or lower surface of the platform. The flange and the recessed surface extend from opposing circumferential edges of the joint portion and each include a substantially radially-extending through hole.

Abstract: A vane for a gas turbine engine, the vane including a platform with an airfoil extending radially from the upper surface of the platform. The platform includes a joint portion which includes a circumferentially extending flange and a recessed surface both formed on either the upper or lower surface of the platform. The flange and the recessed surface extend from opposing circumferential edges of the joint portion and each include a substantially radially-extending through hole.

Abstract: A seal arrangement 30 presents a barrier in the form of a combined seal and anti-fret liner 36 across a shroud ring cavity 32 in order to inhibit air leakage in the platform gap between platforms 33. It will be understood that these gaps are provided for thermal expansion and vibration of vane assemblies but create a leakage path between passage 35 and cavity 32 which can increase aerodynamic losses and therefore reduce engine compressor efficiency. By provision of a combined seal and anti-fret liner 36 such air losses are reduced whilst combining the function of an air leakage seal and an anti-fret liner to prevent abrasive degradation of the mountings 37, 39 and platform section 33 ensures that there is a reduced component count as well as cost, weight and assembly time.