Full-round compressor casing assembly in a gas turbine engine

Rotary kinetic fluid motors or pumps – Working fluid passage or distributing means associated with... – Vane or deflector

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Details

4152092, 415189, F01D 902

Patent

active

052999106

ABSTRACT:
A full-round compressor casing assembly is employed in a gas turbine engine which includes alternating axially-arranged stages of movable blades and stationary vanes, with each stage of movable blades having a row of rotor blades attached to and extending radially outwardly from a rotor and each stage of stationary vanes having a row of stator vanes. The full-round casing assembly includes a plurality of vane sectors with the vanes projecting therefrom in defining each stage of stationary vanes, an inner casing inserted over the rotor and blades, and an outer casing inserted over the inner casing and spaced radially outwardly therefrom. The inner casing includes alternating axially-arranged full-round shroud bands and mounting bands. Each shroud band encircles the outer ends of the rotor blades. Each mounting band has a circumferential guide track on an interior side mounting the vane sectors in side-by-side relation around the mounting band with the vanes extending radially inwardly. Also, each mounting band has one or more openings to allow inserting the vane sectors one at a time from an exterior side of the mounting band through the openings to the mounting track and indexing the vane sectors around the interior of the mounting band in order to assemble the vane sectors and vanes to the inner casing after the rotor blades have been assembled to the rotor and the inner casing has been inserted over the rotor blades.

REFERENCES:
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patent: 3024968 (1962-03-01), Payne et al.
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patent: 3751180 (1973-08-01), Cameron
patent: 3997280 (1976-12-01), Germain
patent: 4014627 (1977-03-01), Heurteux
patent: 4426191 (1984-01-01), Brodell et al.
patent: 4431373 (1984-02-01), Monsarrat
patent: 4543039 (1985-09-01), Ruis et al.

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