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A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diame

A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.

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1. A gas turbine engine rotary assembly comprising: a first component mounted for rotation about an axis of the gas turbine engine, a second component mounted on said first component, a retaining ring received in a circumferential groove defined in a radially outer surface of the first component, th

1. A gas turbine engine rotary assembly comprising: a first component mounted for rotation about an axis of the gas turbine engine, a second component mounted on said first component, a retaining ring received in a circumferential groove defined in a radially outer surface of the first component, the retaining ring providing an axially facing shoulder for axially retaining the second component onto the first component, the retaining ring having at an inner diameter thereof a radially inner surface defining a plurality of circumferentially spaced-apart grooves for engagement with at least one anti-rotation lug projecting from one of said first and second components, thereby restraining the retaining ring against rotation relative to said one of the first and second components, the retaining ring having a split ring body which is spring-loaded radially inwardly at said inner diameter against a circumferential seat provided on a radially outer surface of one of said first and second components, and an outer sleeve surrounding the split ring body to limit radial expansion of the split ring body and thereby prevent disengagement of the anti-rotation lug from the split ring body as a result of centrifugal forces transferred to the retaining ring during gas turbine engine operation. 2. The gas turbine engine rotary assembly defined in claim 1, wherein the anti-rotation lug forms part of a set of circumferentially spaced-apart lugs extending axially from the second component into the circumferential groove defined in the radially outer surface of the first component and into the circumferentially spaced-apart grooves of the retaining ring, and wherein a radially inner facing surface of each of the circumferentially spaced-apart grooves of the retaining ring is biased in radial seating contact with a corresponding radially outer facing surface of each of said circumferentially spaced-apart lugs of the second component, thereby providing for the centralization of the retaining ring by the circumferentially spaced-apart lugs. 3. The gas turbine engine rotary assembly defined in claim 2, wherein the radially inner surface of the retaining ring between the circumferentially spaced-apart grooves is spaced radially from a bottom surface of the circumferential groove defined in the first component, thereby allowing the retaining ring to be floatingly received in the circumferential groove. 4. The gas turbine engine rotary assembly defined in claim 2, wherein the circumferentially spaced-apart grooves in the radially inner surface of the retaining ring includes centralizing grooves and at least one anti-rotation groove, the centralizing grooves and the at least one anti-rotation groove having a different profile, the centralizing grooves having larger corner radii than the at least one anti-rotation groove. 5. The gas turbine engine rotary assembly defined in claim 1, wherein the circumferential seat comprises a radially outer facing bottom surface of the circumferential groove defined in the first component, and wherein the split ring body is positively seated in radial contact with the radially outer facing bottom surface of the circumferential groove. 6. The gas turbine engine rotary assembly defined in claim 5, wherein the anti-rotation lug forms part of a set of circumferentially spaced-apart lugs extending axially from the second component, the circumferentially spaced-apart lugs being received in said circumferentially spaced-apart grooves at the inner diameter of the retaining ring, and wherein there is no radial contact between the circumferentially spaced-apart lugs and the split ring body. 7. The gas turbine engine rotary assembly defined in claim 1, wherein the first component is a turbine disc and the second component a coverplate. 8. A retaining ring arrangement for axially holding a coverplate on a turbine disc mounted for rotation about a central axis of a gas turbine engine, the retaining ring arrangement comprising: a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the turbine disc, the inner diameter of the split retaining ring being biased inwardly in radial contact with a radially outer facing seat provided on one of the coverplate and the turbine disc, an anti-rotation feature provided at said inner diameter of the split retaining ring for restraining the split retaining ring against rotation, and a sleeve surrounding the split retaining ring to limit radial expansion thereof when subject to centrifugal forces during operation of the gas turbine engine. 9. The retaining ring arrangement defined in claim 8, wherein the inner diameter of the split retaining ring is provided with an array of circumferentially spaced-apart grooves. 10. The retaining ring arrangement defined in claim 9, wherein said array of circumferentially spaced-apart grooves comprises a set of centralization grooves, the centralization grooves having a radially inwardly facing bottom biased in radial contact with the radially outer facing seat, the radially outer facing seat comprising a set of circumferentially spaced-apart centralization lugs projecting axially from the coverplate into the circumferential groove defined in the turbine disc. 11. The retaining ring arrangement defined in claim 8, wherein the anti-rotation feature includes at least one groove defined in the inner diameter of the split retaining ring, the at least one groove receiving an anti-rotation lug extending axially from one of the turbine disc and the coverplate. 12. The retaining ring arrangement defined in claim 10, wherein surface segments of the inner diameter of the split retaining ring between adjacent centralization grooves are spaced radially from a bottom surface of the circumferential groove defined in the radially outer surface of the turbine disc, thereby allowing the split retaining ring to be floatingly received in said circumferential groove. 13. The retaining ring arrangement defined in claim 11, wherein the anti-rotation lug extends axially from the coverplate into the circumferential groove defined in the turbine disc for engagement in the at least one groove defined in the inner diameter of the split retaining ring. 14. The retaining ring arrangement defined in claim 8, wherein said anti-rotation feature comprises a set of circumferentially spaced-apart grooves defined in the inner diameter of the split retaining ring, and wherein a corresponding set of anti-rotation lugs project axially from the coverplate into the circumferential groove defined in the turbine disc for engagement in said circumferentially spaced-apart grooves at the inner diameter of the split retaining ring. 15. The retaining ring arrangement defined in claim 14, wherein each of the circumferentially spaced-apart grooves has a radially inwardly facing bottom surface which is spaced radially from an associated one of the anti-rotation lugs, and wherein the radially outer facing seat is provided by a radially outer facing bottom surface of the circumferential groove defined in the turbine disc, the surface of the inner diameter of the split retaining ring between the circumferentially spaced-grooves being positively radially seated against the radially outwardly facing bottom surface of the circumferential groove.