| 摘要 |
<p>1,090,721. Making bladed rotors. ROLLSROYCE Ltd. Jan. 4, 1965 [Jan. 15, 1964], No. 1887/64. Heading B3A. [Also in Divisions B5 and F1] In a method of making a bladed rotor for a gas turbine engine compressor, fibres are employed in the formation of the blades and the hub and simultaneously with the formation, or subsequently thereto, the blades and hub are united together, each blade being connected to another blade by at least one continuously curved group 16, 17 of fibres extending through the hub and being in tension during rotor rotation. The various groups 16, 17 of fibres are interwoven with each other and are of catenary shape. The fibres may be of ceramic constituted by an oxide, nitride, or carbide, or of sapphire, silica, silicon nitride, silicon carbide, graphite or boron. They are individually coated by silver, nickel, iron, titanium, platinum, columbium, aluminium, or alloy thereof, or an epoxy, polyimide, polyimidazole, polyquinoxaline or polythiazole resin. The blades and hub are formed by hot-pressing the coated fibres together. The rotor may be formed of an epoxy or high-temperature polyimide resin, reinforced by any of the coated fibres. A pair of bladed rotor discs may be interconnected by groups of fibres common to or separate from the fibres forming the blades, the interconnecting fibres restraining relative twisting between the discs about the rotation axis.</p> |
