Blade tip clearance control apparatus
AssigneeROLLS-ROYCE plc
InventorRonald Catlow
Life of this patent
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Abstract
A blade clearance control apparatus (46) for a gas turbine engine (10) comprises a series of segments (42) which define a casing in the rotor path of high pressure shroudless turbine blades (30). The segments (42) are attached to plates (78) having surfaces co-operating with chordal lengths (74) of a number of pressure tubes (68) which are located in a frame (46). The application and release of pressure to the pressure tubes (68) causes the segments (42) to move between inner and outer positions in order to control clearance X between the tips of blades (30) and the segments (42).
Claims12
A gas turbine engine blade tip clearance control apparatus comprising a plurality of circumferentially arranged spaced wall members located adjacent a rotor path of a plurality of blades of the engine, at least one pressure tube for moving each wall member from a first radial stop to a second radial stop, the at least one pressure tube having a plurality of chordal lengths to which the wall members are operationally attached, the chordal lengths being preloaded to hold the wall members against the first radial stop, the pressure tube being pressurizable to deflect the chordal length and move the wall member against the second radial stop.
Dependencies are inferred from the claim text.