1. Field of the Invention
This invention relates to gas turbine engines, and in particular, to the bladed compressor and turbine disc assemblies of such engines.
2. Description of Related Arts
In a typical gas turbine engine of the axial flow type there is a number of rotatable bladed compressor and rotor disc assemblies, each assembly comprising an annular array of aerofoil section blades secured to the periphery of a disc. The blades may be secured to the discs in a variety of ways such as, for example, by fashioning the root ends of the blades into "fir tree" form and then pressing them into slots broached into the periphery of the disc. In the known ways of securing the blades to discs the root ends of the blades are formed to a particular configuration and the method of securing the blades to a disc is thus essentially a mechanical one.