| 摘要 |
1,142,877. Compressor blades. ROLLSROYCE Ltd. May 25, 1967 [June 28, 1966], No. 28829/66. Heading F1T. A member 6 for attachment to a rotor blade of a gas turbine engine, e. g. a compressor blade, comprises at least one bundle 7 of fibres extending longitudinally of the member and having at least one end divided longitudinally into a plurality of end portions each of which is turned through substantially 90 degrees to its own length and in the opposite sense to the next adjacent end portion in order to fit into at least one slot 11 formed longitudinally in the blade flanks. Each fibre bundle 7 may be formed of a plurality of fibrous laminae 8 and a plurality of bundles may be spaced apart in a member 6 by a low density filler material, e. g. expanded polystyrene, an aluminium honeycomb, or a foamed metal or ceramic. The fibres may be aluminium coated silica fibres, coated carboniferous fibres or boron fibres. The bundles 7 and the filler material are contained inside a fibre reinforced plastics skin 15 with an erosion protective coating 16. The members 6 on opposite sides of a blade 4 are secured in the slots 11 extending through the blade by a bonding or adhesive process. Each member may extend between adjacent pairs of blades, both ends of the fibre bundles being divided, or the members extending from opposite sides of the blades may be bonded or glued together during or after assembly of a blade ring. The ends of members 6 to be joined between adjacent blades are cut irregularly across the width of the members. |
