Turbine engines
AssigneeROLLS-ROYCE plc
InventorsJohn F. Leonard, Peter J. Maggs
Life of this patent
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Abstract
A gas turbine engine having a main casing, turbine blades and a segmented cylindrical liner surrounding the tips of the blades is provided with apparatus for compensating for different radial expansions between the blades and the liner. The apparatus comprises a shroud structure, such as a platform of an axially adjacent nozzle guide vane, and a slipper element extending radially from the shroud structure to the liner and coupling one to the other. The slipper element expands circumferentially more slowly than does the shroud structure. Thermal circumferential growth of the shroud structure causes a radial displacement of the liner segments relative to the shroud structure.
Claims15
In a gas turbine engine having a main casing, turbine blades and a segmented cylindrical liner located radially of and surrounding the tips of the blades, an apparatus for compensating for differing radial expansions between the blades and the liner, the apparatus comprising a shroud structure axially adjacent the liner and including radially extending coupling means for coupling the liner to said structure in such a manner that thermal circumferential growth of said shroud structure causes a radial displacement of the liner segment relative to said adjacent shroud structure.
Dependencies are inferred from the claim text.