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In one embodiment, a system includes a turbine engine that includes a turbine stage including a turbine rotor having multiple blades disposed in a first annular arrangement. The turbine engine also includes multiple cover plates disposed in a second annular arrangement along interfaces between the t

In one embodiment, a system includes a turbine engine that includes a turbine stage including a turbine rotor having multiple blades disposed in a first annular arrangement. The turbine engine also includes multiple cover plates disposed in a second annular arrangement along interfaces between the turbine rotor and the blades. The turbine engine further includes multiple lugs coupled to the turbine stage and a first ring coupled to the lugs to hold the cover plates to the turbine stage.

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1. A system, comprising: a turbine engine, comprising: a turbine stage comprising a turbine rotor having a plurality of blades disposed in a first annular arrangement;a plurality of cover plates disposed in a second annular arrangement along interfaces between the turbine rotor and the blades;a plur

1. A system, comprising: a turbine engine, comprising: a turbine stage comprising a turbine rotor having a plurality of blades disposed in a first annular arrangement;a plurality of cover plates disposed in a second annular arrangement along interfaces between the turbine rotor and the blades;a plurality of lugs coupled to the turbine stage; anda first ring coupled to the plurality of lugs, wherein the first ring is configured to block axial movement of the plurality of cover plates to hold the plurality of cover plates to the turbine stage, the first ring comprises a plurality of first interlocking features, and the first ring is configured to rotate about a rotational axis of the turbine stage in a first direction until the first interlocking features at least partially capture the plurality of lugs. 2. The system of claim 1, wherein the plurality of lugs are integral with the turbine rotor. 3. The system of claim 1, wherein the plurality of lugs are integral with the blades. 4. The system of claim 1, wherein the plurality of lugs extend axially through the turbine stage between opposite axial sides, and the plurality of lugs secure cover plates on both of the opposite axial sides. 5. The system of claim 1, wherein the plurality of lugs each comprise a resilient feature configured to bias the respective lug inwardly toward the turbine stage. 6. The system of claim 1, wherein the first ring is segmented into a plurality of ring segments defining a third annular arrangement. 7. The system of claim 1, comprising a second ring having a plurality of second interlocking features, the second ring is configured to rotate about the rotational axis of the turbine stage in a second direction until the second interlocking features at least partially capture the plurality of lugs, the first and second directions are opposite from one another, and each pair of first and second interlocking features is disposed about opposite circumferential sides of each respective lug after rotation of both the first and second rings. 8. The system of claim 7, wherein the first ring is segmented into a first plurality of ring segments defining a third annular arrangement, and the second ring is segmented into a second plurality of ring segments defining a fourth annular arrangement. 9. A system, comprising: a turbine stage, comprising: a lug having a shaft and a head sized larger than the shaft, wherein the shaft and head are configured to extend through a cover plate, and the lug is configured to receive an interlocking feature between the cover plate and the head, wherein the interlocking feature is configured to block axial movement of the cover plate to hold the cover plate to the turbine stage;a first ring having the interlocking feature; anda second ring configured to interlock with the first ring, wherein the first and second rings rotate in opposite directions to capture the lug. 10. The system of claim 9, wherein the lug is integral with a turbine rotor or a turbine blade of the turbine stage. 11. The system of claim 9, wherein the shaft comprises a curved shape configured to bend to bias the head inwardly toward the turbine stage. 12. The system of claim 9, wherein the lug extends axially through the turbine stage between opposite axial sides, and the lug secures said cover plate and another cover plate located on a respective one of the opposite axial sides. 13. The system of claim 9, comprising said cover plate being one of a plurality of cover plates disposed in a first annular arrangement along interfaces between a turbine rotor and blades of the turbine stage, wherein the lug is one of a plurality of lugs disposed in a second annular arrangement, and each lug of the plurality of lugs is configured to receive a respective interlocking feature between a respective cover plate and the head of the lug. 14. A system, comprising: a turbine stage, comprising: a first ring comprising a first plurality of interlocking features configured to at least partially capture a plurality of lugs to retain a plurality of cover plates, wherein the first plurality of interlocking features comprises a plurality of hooks configured to engage and disengage the plurality of lugs via rotation of the first ring. 15. The system of claim 14, comprising a second ring having a plurality of tabs configured to extend at least partially into the plurality of hooks of the first ring, wherein the first and second rings are configured to rotate in opposite directions to substantially capture the plurality of lugs between the hooks and tabs. 16. The system of claim 15, comprising the plurality of cover plates disposed in an annular arrangement over interfaces between a turbine rotor and a plurality of turbine blades of the turbine stage, the plurality of lugs extend from the turbine rotor in an axial direction through the cover plates, and the first and second rings capture the lugs between the cover plates and enlarged heads of the lugs.