| 摘要 |
In a gas compressor engine, a rotor to which turbine blades (airfoils) are mounted, is constructed of a fiber composite material. In a first zone of the rotor, a first group of fibers are oriented circumferentially, in the direction of rotor rotation. A second set of fibers are oriented off-axis along the entire longitudinal length of the rotor. The first group of fibers overlay the second group only in specific zones, creating zones in which only the off-axis fibers are located. Race-track shaped apertures are cut in these second zones between fibers and these apertures receive the compressor blades that are inserted from the interior of the rotor. The first zones also provide circumferential seals to receive the base of each compressor blade. The first zones are constructed by building up layers of the circumferential fibers in the first zones.
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