Annular vane assembly for a gas turbine engine

1. An annular vane assembly for a gas turbine engine, the assembly comprising:

a vane segment, the vane segment comprising:

an arcuate rail, and

a vane that extends radially inwardly from the arcuate rail; and

a hollow cylindrical casing including an inside curved surface in which an annular groove is formed and receives the arcuate rail of the vane segment,

wherein the arcuate rail is secured in the annular groove using a resilient strip interposed between the arcuate rail and the annular groove,

wherein the resilient strip comprises a planar main body and a plurality of sprung wings that extend to either side of the main body,

wherein the plurality of sprung wings are angled with respect to a plane of the main body, and

wherein the resilient strip is circumferentially moveable between a first position in which the resilient strip exerts a force radially on the arcuate rail in order to secure the arcuate rail in the annular groove and a second position in which the plurality of sprung wings occupy a first plurality of recesses in the assembly to relieve the radial force and release the arcuate rail in the annular groove.

2. The assembly as claimed in claim 1 , wherein the resilient strip in the first position exerts a radially inward force on the arcuate rail.

3. The assembly as claimed in claim 2 ,

wherein the arcuate rail includes a plurality of flanges that run along either side of the arcuate rail,

wherein the annular groove includes a second plurality of recesses that run along either side of the annular groove,

wherein a plurality of first surfaces comprising a radially inwardly facing surface of the plurality of flanges engages with a second surface comprising a radially outwardly facing surface of the second plurality of recesses, and

wherein the resilient strip is interposed between a plurality of third surfaces comprising radially outwardly facing surfaces of the plurality of flanges and a plurality of fourth surfaces comprising radially inwardly facing surfaces of the second plurality of recesses, and

wherein in the first position the plurality of sprung wings exert a radially inward force on the plurality of third surfaces and the main body of the resilient strip exerts a radially outward force on the plurality of fourth surfaces.

4. The assembly as claimed in claim 3 ,

further comprising a further strip interposed between the resilient strip and the plurality of third surfaces,

wherein in the first position the plurality of sprung wings exerts the radially inward force on the plurality of third surfaces via the further strip,

wherein the first plurality of recesses includes a third plurality of recesses in each side of the further strip, and

wherein a circumferential movement of the resilient strip between the first position and the second position is a circumferential movement relative to the further strip.

5. The assembly as claimed in claim 4 ,

wherein the third plurality of recesses include a plurality of sides that are encountered by the plurality of sprung wings when the resilient strip is moved circumferentially relative to the further strip from the second position to the first position, and

wherein the plurality of sides subtend an angle to a circumferential direction of substantially less than 90 degrees.

6. The assembly as claimed in claim 5 , wherein a plurality of ends of the resilient strip and/or the further strip include a tooling hole whereby a tool may be attached to the resilient strip and/or the further strip to facilitate the circumferential movement of the resilient strip relative to the further strip between the first position and the second position.

7. The assembly as claimed in claim 4 , wherein a plurality of ends of the resilient strip and/or the further strip include a tooling hole whereby a tool may be attached to the resilient strip and/or the further strip to facilitate the circumferential movement of the resilient strip relative to the further strip between the first position and the second position.

8. The assembly as claimed in claim 1 , wherein the arcuate rail and the annular groove incorporate a complementary protrusion and a depression to circumferentially locate the arcuate rail within the annular groove.

9. The assembly as claimed in claim 1 , wherein each vane of the vane segment extends radially inwardly to a further arcuate rail of the vane segment.

10. The assembly as claimed in claim 1 , wherein the assembly is a compressor assembly.