| 摘要 |
A method of making a bladed disc assembly of a kind used, for example in the turbine or compressor sections of a gas turbine engine comprises forming a peripheral groove 12 in the rim of the disc 2, positioning a plurality f bladed segments around the disc, each segment having its root portion 16 located in the groove, where it is secured, and diffusion bonding the root portions and the rim of the disc by means of isostatic hot gas pressure bonding applying pressure to the faces 7 and 8 of the disc. Initial securing of the root portion is preferably by means of electron beam welding to form circumferential seams 18 and axial seams between the root segments. Each segment may carry two or more blades 11. <IMAGE> |
