United Technologies Corporation

William R Ulrich

Lee E Hansen

An inner shroud for a gas turbine engine is described comprising six approximately equiangular segments each segment adapted to securely contain a plurality of vane stems. The segments comprise interlocking first and second sections forming a channel having an aperture suitably sized to securely contain the vane stem. The sections when fit together form an outer recess area suitably sized to substantially accommodate the button portion of the vane stem and an inner cavity suitably sized to accommodate the inner portion of the vane stem. This results in reduced shroud curling when used in a split case compressor.

Radially constrained variable vane shroud

A one piece, welded drum rotor for a gas turbine engine is described. The drum rotor is characterized by disks having a superalloy composition which is different from the seal alloy composition. Several welding techniques are utilized to join the drum rotor components to each other.

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Lake Park, FL, United States of America

William R Ulrich