Gas turbine engine system
AssigneeROLLS-ROYCE plc
InventorAlec G Dodd
Life of this patent
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Abstract
Tip clearance apparatus for a gas turbine engine comprises a shroud ring having curved portions so as to allow eccentric offset and hence asymmetric movement of the shroud. The shroud ring is mounted within a guide also having corresponding curved portions and movement of the shroud ring is controlled by the use of sensors.
Claims6
Rotor tip clearance apparatus for a gas turbine engine comprising an annular shroud member attached to a hollow support ring supported within a guide member, said member having an internal frustoconical face adapted to cooperate with the outer extremities of the rotor to define a clearance therewith, said support ring being controllable so as to alter the clearance between the shroud member and the outer extremities of said rotor wherein said support ring comprises curved portions adapted to cooperate with curved portions in said guide member so as to allow asymmetric movement of said shroud member.
Dependencies are inferred from the claim text.