Axial flow gas turbine engine compressor

Details Axial flow gas turbine engine compressor Axial flow gas turbine engine compressor

1977-10-04

1979-11-27

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Rotor having flow confining or deflecting web, shroud or...

Axially extending shroud ring or casing

416244A, 416230, 416134R, 416500, F01D 522

Patent

active

041759125

ABSTRACT:
A rotor blade stage for the compressor of a gas turbine engine comprising a rotor disc having a plurality of equally spaced apart rotor blades mounted on its periphery. The spaces between the rotor blades in the region of the periphery of the rotor disc are infilled with a mixture comprising reinforcing filaments enclosed in a matrix of a cured epoxy resin and filler material. Means are provided to retain the mixture in position between the rotor blades upon rotation of the rotor disc.

REFERENCES:
patent: 2936155 (1960-05-01), Howell et al.
patent: 3008689 (1961-11-01), Morley et al.
patent: 3294364 (1966-12-01), Stanley
patent: 3494539 (1970-02-01), Littleford
patent: 3616508 (1971-11-01), Wallett
patent: 3656864 (1972-04-01), Wagle
patent: 3675294 (1972-07-01), Palfreyman et al.
patent: 3758232 (1973-09-01), Wallett
patent: 3813185 (1974-05-01), Bouiller et al.
patent: 3905722 (1975-09-01), Guy et al.

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