Patent ID: 6935836

Claim:
A gas turbine engine apparatus, comprising: a mechanical housing; a first rotor with a plurality of first blades located within said mechanical housing and rotatable about a centerline, each of said plurality of first blades including a first tip; a control ring located within and spaced from said mechanical housing; a plurality of locating members fixedly coupled with said mechanical housing and slidably coupled with said control ring, said plurality of locating members positioning said control ring relative to said mechanical housing; a non-rotatable ring with a plurality of vanes located within said mechanical housing and axially spaced from said first rotor, wherein said non-rotatable ring includes a tip shroud portion spaced from said first tips of said plurality of first blades, and wherein said non-rotatable ring is fixedly coupled with said control ring and moveable therewith; and wherein relative motion may occur between said control ring and at least one of said plurality of locating members.