A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an annulus filler assembly. The annulus filler assembly includes at least two bodies and a brace, each of the bod
A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an annulus filler assembly. The annulus filler assembly includes at least two bodies and a brace, each of the bodies being arranged to abut respective adjacent blades and the brace is arranged to occupy a position centrally of the two bodies. The brace is mounted to the disc and each body and the brace are arranged to engage one another to form an airwash surface. The airwash surface improves aerodynamic flow of air entering the gas turbine engine.
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1. A rotor assembly for a gas turbine engine, the rotor assembly comprising: a disc supporting a plurality of radially extending blades,the blades defining passages between their circumferentially-facing surfaces and each of these passages having an annulus filler assembly; andthe annulus filler ass
1. A rotor assembly for a gas turbine engine, the rotor assembly comprising: a disc supporting a plurality of radially extending blades,the blades defining passages between their circumferentially-facing surfaces and each of these passages having an annulus filler assembly; andthe annulus filler assembly comprising at least two bodies and a brace,each of the bodies being mounted to one of adjacent said blades and the brace occupying a position centrally of the at least two bodies,each of the bodies and the brace interacting with one another to form an airwash surface,the interaction of the brace with at least one said body forming a floating and moveable seal,the seal having a lip arranged to overlap a co-operating feature, andthe feature having a radially outer opposing wall and a radially inner opposing wall to define a slot by way of a radial gap between the opposing walls and the lip being located centrally therebetween so as to be within the slot and movable relative to the opposing walls. 2. A rotor assembly for a gas turbine engine as claimed in claim 1, wherein the brace is mounted to the disc. 3. A rotor assembly for a gas turbine engine as claimed in claim 1, wherein the lip comprises at least one inward step in a radial direction of the disc and the at least one inward step forms at least one ledge on the lip. 4. A rotor assembly for a gas turbine engine as claimed in claim 1, wherein the radially inner opposing wall has a first captive ridge and the lip comprises a bulbous curve at the radially inner extremity of the lip. 5. A rotor assembly for a gas turbine engine, the rotor assembly comprising: a disc supporting a plurality of radially extending blades,the blades defining passages between their circumferentially-facing surfaces and each of these passages having an annulus filler assembly; andthe annulus filler assembly comprising at least two bodies, each of which comprises a hollow box-section constituted by walls surrounding an interior opening, and a brace,each of the bodies being mounted to one of adjacent said blades and the brace occupying a position centrally of the at least two bodies,each of the bodies and the brace interacting with one another to form an airwash surface,the interaction of the brace with at least one said body forming a floating and moveable seal,the seal having a lip arranged to overlap a co-operating feature, andthe feature having a radially outer opposing wall and a radially inner opposing wall to define a slot by way of a radial gap between the opposing walls and the lip being located centrally therebetween so as to be within the slot and movable relative to the opposing walls. 6. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip is a wedge tapering to an edge at the lip extremity. 7. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip comprises at least one inward step in a radial direction of the disc and the at least one inward step forms at least one ledge on the lip. 8. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip comprises a plurality of inward steps in a radial direction of the disc forming a plurality of ledges. 9. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the radially inner opposing wall has a first captive ridge. 10. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the radially outer opposing wall has a second captive ridge. 11. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip comprises a bulbous curve at the radially inner extremity of the lip. 12. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the lip comprises at least one knuckle at the extremity of the lip. 13. A rotor assembly for a gas turbine engine as claimed in claim 7, wherein the at least one ledge comprises a fabric section. 14. A rotor assembly for a gas turbine engine as claimed in claim 5, wherein the brace has a retention feature and is mounted to the disc by way of a complementary retention feature defined by the disc and located between the respective adjacent said blades. 15. A rotor assembly for a gas turbine engine, the rotor assembly comprising: a disc supporting a plurality of radially extending blades,the blades defining passages between their circumferentially-facing surfaces and each of these passages having an annulus filler assembly that extends from a trailing edge to a leading edge of each of the blades defining the each passage; andthe annulus filler assembly comprising at least two bodies and a brace,each of the bodies being mounted to one of adjacent said blades and the brace occupying a position centrally of the at least two bodies,each of the bodies and the brace interacting with one another to form an airwash surface,the interaction of the brace with at least one said body forming floating and moveable seal,the seal having a lip arranged to overlap a co-operating feature,the feature having a radially outer opposing wall and a radially inner opposing wall to define a slot by way of a radial gab between the opposing walls and the lip being located centrally therebetween so as to be within the slot and movable relative to the opposing walls, andthe rotor assembly being a fan assembly and the blades being fan blades.
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