Gas turbine engine casing and rotor blade arrangement
AssigneeROLLS-ROYCE plc
InventorRichard S Booth
Life of this patent
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Abstract
An arrangement for a gas turbine engine comprises a compressor and its surrounding casing. The casing has a generally cylindrical inner surface, one cylindrical section of the inner casing being provided with a circumferential array of recesses. An axially adjacent cylindrical section of the inner casing surface is provided with an abradable lining. The tips of the rotor blades of the compressor are provided with a treated portion at least partly axially aligned with the recesses in the inner casing, the remaining untreated portion of the rotor blade tips being at least partly axially aligned with the lined section of the inner casing.
Claims11
An arrangement for a gas turbine engine, the arrangement comprising a rotor and a surrounding casing, said casing having a generally cylindrical inner surface, said inner surface having a first cylindrical section and a second, axially adjacent cylindrical section, said first section being provided with a plurality of recesses in a circumferential arrangement and said second section being provided with an abradable lining, said rotor comprising an annular array of rotor blades, each blade having an outer tip, and each of said tips comprising a treated portion and an untreated portion wherein said treated portion of said tip is at least partly located opposite said first cylindrical section of the inner surface of said casing and said untreated portion of said tip is at least partly located opposite said second cylindrical section of the inner surface of said casing.
Dependencies are inferred from the claim text.