Composite compressor rotor with removable airfoils

Details Composite compressor rotor with removable airfoils Composite compressor rotor with removable airfoils

1992-09-14

1995-01-03

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

Support mounting, carrier or fairing structure

416230, 416299R, F03B 312

Patent

active

053781104

ABSTRACT:
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.

REFERENCES:
patent: 3679324 (1972-07-01), Stargardter
patent: 4111606 (1978-09-01), Prewo
patent: 4339229 (1982-07-01), Rossman

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