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An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360° in length.

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1. An assembly comprising: a plurality of vanes each vane having an airfoil, a platform, and forward and aft mounting hooks; anda forward liner segment mounted on the forward mounting hooks of the plurality of vanes, wherein the forward liner segment extends around an axially forward side, an axiall

1. An assembly comprising: a plurality of vanes each vane having an airfoil, a platform, and forward and aft mounting hooks; anda forward liner segment mounted on the forward mounting hooks of the plurality of vanes, wherein the forward liner segment extends around an axially forward side, an axially aft side, a radially inner side, and a radially outer side of the forward mounting hooks, and further wherein the forward liner segment is in contact with the axially aft side of the forward mounting hook; andan aft liner segment mounted to the aft mounting hooks of the plurality of vanes, wherein the aft liner segment extends around an axially forward side, an axially aft side, a radially inner side, and a radially outer side of the aft mounting hooks, wherein the forward liner segment and the aft liner segment are arcs of less than 360°, and further wherein the aft liner segment is in contact with the axially forward side of the aft mounting hook. 2. The assembly of claim 1, wherein each liner segment comprises a single-piece segment less than a complete circular ring. 3. The assembly of claim 1, wherein the plurality of vanes are mounted adjacent one another to form a vane pack that comprises an arc that extends substantially 45° about a centerline axis of a gas turbine engine. 4. The assembly of claim 1, wherein the plurality of vanes comprise cantilevered vanes. 5. The assembly of claim 1, wherein the plurality of vanes are mounted adjacent one another to form a vane pack, and wherein the vane pack has a first end vane at a first end and a second end vane at a second end. 6. The assembly of claim 5, wherein each liner segment includes one or more slots adapted to receive one or more standups of the first end vane and/or second end vane. 7. The assembly of claim 6, wherein the one or more slots allows at least one of the first end vane or second end vane to be inserted therethrough. 8. The assembly of claim 5, wherein at least one of the forward liner segment and the aft liner segment is disposed at a distance from the first end vane and/or the second end vane. 9. The assembly of claim 1, wherein a first end vane of a first vane pack is adapted to interface with a second end vane of a second vane pack. 10. A gas turbine engine comprising: a casing with first and second receptacles therein;a plurality of vane packs mounted within the casing and forming a circumferential stage, each vane pack comprising: a plurality of vanes mounted within the first and second receptacles by first and second hooks;a first liner segment mounted to the first hooks and disposed between the first hooks and the first receptacle, wherein the first liner segment extends around an axially forward side, an axially aft side, a radially inner side, and a radially outer side of the first hooks, and further wherein the first liner segment is in contact with the axially aft side of the first hooks; anda second liner segment mounted to the second hooks and disposed between the second hooks and the second receptacle, wherein the second liner segment extends around an axially forward side, an axially aft side, a radially inner side, and a radially outer side of the second hooks, wherein the first liner segment comprises a plurality of separate arc segments arranged to extend substantially 360° about the circumference of the casing and the second liner segment comprises a plurality of separate arc segments arranged to extend substantially 360° about the circumference of the casing, and further wherein the second liner segment is in contact with the axially forward side of the second hooks. 11. The gas turbine engine of claim 10, wherein each vane pack that extends substantially 45° about a centerline axis of the gas turbine engine, and wherein each vane pack corresponds to one first liner segment and one second liner segment. 12. The gas turbine engine of claim 10, wherein the vane pack has a first end vane at a first end and a second end vane at a second end. 13. The gas turbine engine of claim 12, wherein one or both of the first and second liner segment includes one or more slots adapted to receive one or more standups of the first end vane and/or second end vane. 14. The gas turbine engine of claim 13, wherein the one or more slots allows at least one of the first end vane or second end vane to be inserted therethrough. 15. The gas turbine engine of claim 10, wherein each of the first liner segment and the second liner segment are arcs of less than 360°. 16. A method of assembling a plurality of vane segments comprising: assembling a forward liner segment and an aft liner segment with the plurality of vanes, wherein assembling a forward liner segment and an aft liner segment with the plurality of vanes further comprises: inserting a forward mounting hook of a first end vane through a slot in the forward liner segment;inserting an aft mounting hook of a first end vane through a slot in the aft liner segment;positioning the forward liner segment to extend around an axially forward side, an axially aft side, a radially inner side, and a radially outer side of the forward mounting hook, wherein the forward liner segment is in contact with the axially aft side of the forward mounting hook;positioning the aft liner segment to extend around an axially forward side, an axially aft side, a radially inner side, and a radially outer side of the aft mounting hook, wherein the aft liner segment is in contact with the axially forward side of the aft mounting hook;contacting a standup of the first end vane with a surface of the slot; andpositioning the remainder of the plurality of vanes along an arcuate length of the liner segment; andinserting the plurality of vanes, the forward liner segment, and the aft liner segment as an assembled unit into a receptacle of an engine casing of a gas turbine engine so as to mount the assembled unit to the engine casing. 17. The method of claim 16, wherein the step of assembling of the forward and aft liner segments with the plurality of vanes includes fitting a second end vane to the forward and aft liner segments at a second opposing side of the forward and aft liner segments from the first end vane. 18. The method of claim 16, further comprising disposing a plurality of assembled units circumferentially within the casing of the gas turbine engine to form a vane stage.